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1

Modular Countermine Payload for Small Robots  

SciTech Connect (OSTI)

Payloads for small robotic platforms have historically been designed and implemented as platform and task specific solutions. A consequence of this approach is that payloads cannot be deployed on different robotic platforms without substantial re-engineering efforts. To address this issue, we developed a modular countermine payload that is designed from the ground-up to be platform agnostic. The payload consists of the multi-mission payload controller unit (PCU) coupled with the configurable mission specific threat detection, navigation and marking payloads. The multi-mission PCU has all the common electronics to control and interface to all the payloads. It also contains the embedded processor that can be used to run the navigational and control software. The PCU has a very flexible robot interface which can be configured to interface to various robot platforms. The threat detection payload consists of a two axis sweeping arm and the detector. The navigation payload consists of several perception sensors that are used for terrain mapping, obstacle detection and navigation. Finally, the marking payload consists of a dual-color paint marking system. Through the multi-mission PCU, all these payloads are packaged in a platform agnostic way to allow deployment on multiple robotic platforms, including Talon and Packbot.

Herman Herman; Doug Few; Roelof Versteeg; Jean-Sebastien Valois; Jeff McMahill; Michael Licitra; Edward Henciak

2010-04-01T23:59:59.000Z

2

Optical Payload for the STARE Mission  

SciTech Connect (OSTI)

Space-based Telescopes for Actionable Refinement of Ephemeris (STARE) is a nano-sat based mission designed to better determine the trajectory of satellites and space debris in orbit around earth. In this paper, we give a brief overview of the mission and its place in the larger context of Space Situational Awareness (SSA). We then describe the details of the central optical payload, touching on the optical design and characterization of the on-board image sensor used in our Cubesat based prototype. Finally, we discuss the on-board star and satellite track detection algorithm central to the success of the mission.

Simms, L; Riot, V; De Vries, W; Olivier, S S; Pertica, A; Bauman, B J; Phillion, D; Nikolaev, S

2011-03-13T23:59:59.000Z

3

High payload six-axis load sensor  

DOE Patents [OSTI]

A repairable high-payload six-axis load sensor includes a table, a base, and at least three shear-pin load transducers removably mounted between the table and the base. Removable mounting permits easy replacement of damaged shear pins. Preferably, the shear-pin load transducers are responsive to shear forces imparted along the two axes perpendicular to an axis of minimum sensitivity characteristic of the transducer. Responsive to an applied shear force, each shear-pin load transducer can produce an electrical signal proportional to the reaction force. The load sensor can further include a structure for receiving the proportional electrical signals and computing the applied load corresponding to the proportional electrical signals. The computed load can be expressed in terms of a three-dimensional XYZ Cartesian coordinate system.

Jansen, John F. (Knoxville, TN); Lind, Randall F. (Knoxville, TN)

2003-01-01T23:59:59.000Z

4

Control system and method for payload control in mobile platform cranes  

DOE Patents [OSTI]

A crane control system and method provides a way to generate crane commands responsive to a desired payload motion to achieve substantially pendulation-free actual payload motion. The control system and method apply a motion compensator to maintain a payload in a defined payload configuration relative to an inertial coordinate frame. The control system and method can further comprise a pendulation damper controller to reduce an amount of pendulation between a sensed payload configuration and the defined payload configuration. The control system and method can further comprise a command shaping filter to filter out a residual payload pendulation frequency from the desired payload motion.

Robinett, III, Rush D. (Tijeras, NM); Groom, Kenneth N. (Albuquerque, NM); Feddema, John T. (Albuquerque, NM); Parker, Gordon G. (Houghton, MI)

2002-01-01T23:59:59.000Z

5

EChO Payload electronics architecture and SW design  

E-Print Network [OSTI]

EChO is a three-modules (VNIR, SWIR, MWIR), highly integrated spectrometer, covering the wavelength range from 0.55 $\\mu$m, to 11.0 $\\mu$m. The baseline design includes the goal wavelength extension to 0.4 $\\mu$m while an optional LWIR module extends the range to the goal wavelength of 16.0 $\\mu$m. An Instrument Control Unit (ICU) is foreseen as the main electronic subsystem interfacing the spacecraft and collecting data from all the payload spectrometers modules. ICU is in charge of two main tasks: the overall payload control (Instrument Control Function) and the housekeepings and scientific data digital processing (Data Processing Function), including the lossless compression prior to store the science data to the Solid State Mass Memory of the Spacecraft. These two main tasks are accomplished thanks to the Payload On Board Software (P-OBSW) running on the ICU CPUs.

Focardi, M; Farina, M; Pancrazzi, M; Ottensamer, R; Lim, T L; Pezzuto, S; Micela, G; Pace, E

2014-01-01T23:59:59.000Z

6

Expert System for Building TRU Waste Payloads - 13554  

SciTech Connect (OSTI)

The process for grouping TRU waste drums into payloads for shipment to the Waste Isolation Pilot Plant (WIPP) for disposal is a very complex process. Transportation and regulatory requirements must be met, along with striving for the goals of shipment efficiency: maximize the number of waste drums in a shipment and minimize the use of empty drums which take up precious underground storage space. The restrictions on payloads range from weight restrictions, to limitations on flammable gas in the headspace, to minimum TRU alpha activity concentration requirements. The Overpack and Payload Assistant Tool (OPAT) has been developed as a mixed-initiative intelligent system within the WIPP Waste Data System (WDS) to guide the construction of multiple acceptable payloads. OPAT saves the user time while at the same time maximizes the efficiency of shipments for the given drum population. The tool provides the user with the flexibility to tune critical factors that guide OPAT's operation based on real-time feedback concerning the results of the execution. This feedback complements the user's external knowledge of the drum population (such as location of drums, known challenges, internal shipment goals). This work demonstrates how software can be utilized to complement the unique domain knowledge of the users. The mixed-initiative approach combines the insight and intuition of the human expert with the proficiency of automated computational algorithms. The result is the ability to thoroughly and efficiently explore the search space of possible solutions and derive the best waste management decision. (authors)

Bruemmer, Heather; Slater, Bryant [Information Systems Laboratories, 2235 East 25th Street, Suite 100, Idaho Falls, ID 83404 (United States)] [Information Systems Laboratories, 2235 East 25th Street, Suite 100, Idaho Falls, ID 83404 (United States)

2013-07-01T23:59:59.000Z

7

TRU waste certification and TRUPACT-2 payload verification  

SciTech Connect (OSTI)

The Waste Isolation Pilot Plant (WIPP) established a policy that requires each waste shipper to verify that all waste shipments meet the requirements of the Waste Acceptance Criteria (WAC) prior to being shipped. This verification provides assurance that transuranic (TRU) wastes meet the criteria while still retained in a facility where discrepancies can be immediately corrected. Each Department of Energy (DOE) TRU waste facility planning to ship waste to the Waste Isolation Pilot Plant (WIPP) is required to develop and implement a specific program including Quality Assurance (QA) provisions to verify that waste is in full compliance with WIPP's WAC. This program is audited by a composite DOE and contractor audit team prior to granting the facility permission to certify waste. During interaction with the Nuclear Regulatory Commission (NRC) on payload verification for shipping in TRUPACT-II, a similar system was established by DOE. The TRUPACT-II Safety Analysis Report (SAR) contains the technical requirements and physical and chemical limits that payloads must meet (like the WAC). All shippers must plan and implement a payload control program including independent QA provisions. A similar composite audit team will conduct preshipment audits, frequent subsequent audits, and operations inspections to verify that all TRU waste shipments in TRUPACT-II meet the requirements of the Certificate of Compliance issued by the NRC which invokes the SAR requirements. 1 fig.

Hunter, E.K. (USDOE Albuquerque Operations Office, Carlsbad, NM (USA). Waste Isolation Pilot Plant Project Office); Johnson, J.E. (Westinghouse Electric Corp., Carlsbad, NM (USA). Waste Isolation Div.)

1990-01-01T23:59:59.000Z

8

Nonlinear Decelerator for Payloads in Aerial Delivery Systems. I: Design and Testing  

E-Print Network [OSTI]

We study the dynamics and the optimization of the shock deceleration supported by a payload when its airborne carrier impacts the ground. We build a nonlinear elastic model for a container prototype and an elastic suspension system for the payload. We model the dynamics of this system and extract information on maximum deceleration, energy transfer between the container and payload, and energy resonant damping. We designed the system and perform lab experiments for various terminal velocities and types of grounds (cement, grass, sand water, etc.). The results are compared with the theoretical model and results are commented, including predictions for deceleration at different types of ground impact. The results can be used for aerial delivery systems, splash-down of capsules, recoveries, weather balloons, coastal surveying systems, or the new introduced goal-line technology in sport competitions.

T. Lyons; M. Ginther; P. Mascarenas; E. Rickard; J. Robinson; J. Braeger; H. Liu; A. Ludu

2014-08-19T23:59:59.000Z

9

Quality assurance guidance for TRUPACT-II (Transuranic Package Transporter-II) payload control  

SciTech Connect (OSTI)

The Transuranic Package Transporter-II (TRUPACT-II) Safety Analysis Report for Packaging (SARP) approved by the Nuclear Regulatory Commission (NRC), discusses authorized methods for payload control in Appendix 1.3.7 and the Quality Assurance (QA) requirements in Section 9.3. Subsection 9.3.2.1 covers maintenance and use of the TRUPACT-II and the specific QA requirements are given in DOE/WIPP 89-012. Subsection 9.3.2.2 covers payload compliance, for which this document was written. 6 refs.

Not Available

1989-10-01T23:59:59.000Z

10

Boulder. DATA-CHASER is a science payload, with a primary focus on solar  

E-Print Network [OSTI]

Boulder. DATA-CHASER is a science payload, with a primary focus on solar observation. The main of the power subsystem. Science is performed using three solar observing instruments, Far Ultraviolet Spectrometer (FARUS), Soft X-ray and Extreme Ultraviolet Experiment (SXEE), and Lyman-alpha Solar Imaging

Stone, Peter

11

Boulder. DATACHASER is a science payload, with a primary focus on solar  

E-Print Network [OSTI]

Boulder. DATA­CHASER is a science payload, with a primary focus on solar observation. The main of the power subsystem. Science is performed using three solar observing instruments, Far Ultraviolet Spectrometer (FARUS), Soft X­ray and Extreme Ultraviolet Experiment (SXEE), and Lyman­alpha Solar Imaging

Stone, Peter

12

short-wood and is also character-ized by large payloads and long  

E-Print Network [OSTI]

short-wood and is also character- ized by large payloads and long distances. However, due to our- mately 90% of wood arrives at mills by truck, with 10% arriving through a combination of water and rail. Of the roundwood deliv- ery, approximately 93% is in long- wood form, with the small remain- der being short-wood

Bolding, M. Chad

13

Impact of Liquefied Natural Gas usage and payload size on Hybrid Wing Body aircraft fuel efficiency  

E-Print Network [OSTI]

This work assessed Hybrid Wing Body (HWB) aircraft in the context of Liquefied Natural Gas (LNG) fuel usage and payload/range scalability at three scales: H1 (B737), H2 (B787) and H3 (B777). The aircraft were optimized for ...

Mody, Pritesh (Pritesh Chetan)

2010-01-01T23:59:59.000Z

14

www.sea.co.uk a Cohort plc company Lunar Lander Science payload  

E-Print Network [OSTI]

www.sea.co.uk a Cohort plc company Lunar Lander ­ Science payload Capability · Instrument design-European #12;www.sea.co.uk a Cohort plc company Lunar Lander ­ IMU Capability · MEMS IMU Heritage · MEMS gyro

Anand, Mahesh

15

Design and performance of a parachute for the recovery of a 760-lb payload  

SciTech Connect (OSTI)

A 26-ft-diameter ribbon parachute deployed using a pilot parachute system has been developed at Sandia National Laboratories for the recovery of a 760-lb payload released at subsonic and transonic speeds. The wide range of deployment dynamic pressures led to the design, utilizing wind tunnel testing and computer simulation, of a unique pilot parachute system verified in full-scale flight tests. Performance data from 20 full-scale flight tests were used to evaluate system performance and structural validity. The concical ribbon parachute design chosen for this development effort follows the practice of previous Sandia National Laboratory parachute development programs for high performance airdropped payloads. The design process for this parachute system included a tradeoff study to evaluate and compare the performance between an equivalent drag area 26-foot-diameter single parachute system and a cluster system of three 14-ft-diameter parachutes. The results showed a small advantage for the cluster system in inflation and initial deceleration characteristics. However, the higher cost, higher weight, greater packing complexity and greater risk involved in the development of the cluster system outweighed the performance advantages and led to the choice of the 26-ft-diameter parachute as the baseline design for the development. This paper describes the design and performance of the 26-ft-diameter parachute which was chosen for the recovery of a 760-lb payload. The results of 20 full-scale flight test of this parachute system are summarized. 8 refs., 13 figs., 2 tabs.

Waye, D.E.

1991-01-01T23:59:59.000Z

16

Second Annual Maintenance, Inspection, and Test Report for PAS-1 Cask Certification for Shipping Payload B  

SciTech Connect (OSTI)

The Nuclear Packaging, Inc. (NuPac), PAS-1 cask is required to undergo annual maintenance and inspections to retain certification in accordance with U.S. Department of Energy (DOE) Certificate of Compliance USA/9184B(U) (Appendix A). The packaging configuration being tested and maintained is the NuPac PAS-1 cask for Payload B. The intent of the maintenance and inspections is to ensure the packaging remains in unimpaired physical condition. Two casks, serial numbers 2162-026 and 2162-027, were maintained, inspected, and tested at the 306E Development, Fabrication, and Test Laboratory, located at the Hanford Site's 300 Area. Waste Management Federal Services, Inc. (WMFS), a subsidiary of GTS Duratek, was in charge of the maintenance and testing. Cogema Engineering Corporation (Cogema) directed the operations in the test facility. The maintenance, testing, and inspections were conducted successfully with both PAS-1 casks. The work conducted on the overpacks included weighing, gasket replacement, and plastic pipe plug and foam inspections. The work conducted on the secondary containment vessel (SCV) consisted of visual inspection of the vessel and threaded parts (i.e., fasteners), visual inspection of sealing surfaces, replacement of O-ring seals, and a helium leak test. The work conducted on the primary containment vessel (PCV) consisted of visual inspection of the vessel and threaded parts (i.e., fasteners), visual inspection of sealing surfaces, replacement of O-ring seals, dimensional inspection of the vessel bottom, a helium leak test, and dye penetrant inspection of the welds. The vermiculite material used in the cask rack assembly was replaced.

KELLY, D.J.

2000-10-09T23:59:59.000Z

17

THE COSMIC INFRARED BACKGROUND EXPERIMENT (CIBER): A SOUNDING ROCKET PAYLOAD TO STUDY THE NEAR INFRARED EXTRAGALACTIC BACKGROUND LIGHT  

SciTech Connect (OSTI)

The Cosmic Infrared Background Experiment (CIBER) is a suite of four instruments designed to study the near infrared (IR) background light from above the Earth's atmosphere. The instrument package comprises two imaging telescopes designed to characterize spatial anisotropy in the extragalactic IR background caused by cosmological structure during the epoch of reionization, a low resolution spectrometer to measure the absolute spectrum of the extragalactic IR background, and a narrow band spectrometer optimized to measure the absolute brightness of the zodiacal light foreground. In this paper we describe the design and characterization of the CIBER payload. The detailed mechanical, cryogenic, and electrical design of the system are presented, including all system components common to the four instruments. We present the methods and equipment used to characterize the instruments before and after flight, and give a detailed description of CIBER's flight profile and configurations. CIBER is designed to be recoverable and has flown four times, with modifications to the payload having been informed by analysis of the first flight data. All four instruments performed to specifications during the subsequent flights, and the scientific data from these flights are currently being analyzed.

Zemcov, M.; Bock, J.; Hristov, V.; Levenson, L. R.; Mason, P. [Department of Physics, Mathematics, and Astronomy, California Institute of Technology, Pasadena, CA 91125 (United States); Arai, T.; Matsumoto, T.; Matsuura, S.; Tsumura, K.; Wada, T. [Department of Space Astronomy and Astrophysics, Institute of Space and Astronautical Science (ISAS), Japan Aerospace Exploration Agency (JAXA), Sagamihara, Kanagawa 252-5210 (Japan); Battle, J. [Jet Propulsion Laboratory (JPL), National Aeronautics and Space Administration (NASA), Pasadena, CA 91109 (United States); Cooray, A. [Center for Cosmology, University of California, Irvine, Irvine, CA 92697 (United States); Keating, B.; Renbarger, T. [Department of Physics, University of California, San Diego, San Diego, CA 92093 (United States); Kim, M. G. [Department of Physics and Astronomy, Seoul National University, Seoul 151-742 (Korea, Republic of); Lee, D. H.; Nam, U. W. [Korea Astronomy and Space Science Institute (KASI), Daejeon 305-348 (Korea, Republic of); Sullivan, I. [Department of Physics, The University of Washington, Seattle, WA 98195 (United States); Suzuki, K., E-mail: zemcov@caltech.edu [Instrument Development Group of Technical Center, Nagoya University, Nagoya, Aichi 464-8602 (Japan)

2013-08-15T23:59:59.000Z

18

Compatibility issues of potential payloads for the USA/9904/B(U)F-85 RTG transportation system (RTGTS) for the 'Pluto Express' mission  

SciTech Connect (OSTI)

The specific electric power system for the 'Pluto Express' mission has yet to be specified. However, electric power will be provided by either radioisotopic thermoelectric generators (RTG), radioisotope thermophotovoltaic systems (RTPV), alkali metal thermal to electrical conversion (AMTEC) systems, radioisotope Stirling systems, or a combination of these. The selected radioisotopic power system will also be transported using the USA/9904/B(U)F-85, Radioisotope Thermoelectric Generator (RTG) Transportation System (RTGTS). As a result, all of the potential payloads present uniquely different environmental and physical configuration requirements. This paper presents the major compatibility issues of the potential payloads for the USA/9904/B(U)F-85 RTG Transportation System for the 'Pluto Express' mission.

Miller, Roger G.; Barklay, Chadwick D.; Howell, Edwin I.; Frazier, Timothy A. [EG and G Mound Applied Technologies P.O. Box 3000 Miamisburg, Ohio 45343-3000 (United States); U.S. Department of Energy P.O. Box 66 Miamisburg, Ohio 45343-0066 (United States)

1997-01-10T23:59:59.000Z

19

G-1 Payload  

Broader source: All U.S. Department of Energy (DOE) Office Webpages (Extended Search)

AFDC Printable Version Share this resource Send a link to EERE: Alternative Fuels Data Center Home Page to someone by E-mail Share EERE: Alternative Fuels Data Center Home Page on Facebook Tweet about EERE: Alternative Fuels Data Center Home Page on Twitter Bookmark EERE:1 First Use of Energy for All Purposes (Fuel and Nonfuel),Feet) Year Jan Feb Mar Apr MayAtmospheric Optical Depth7-1D: Vegetation ProposedUsingFun with Big Sky Learning Fun with Big SkyDIII-D ExplorationsFuture25, 2010

20

Shielded Payload Containers Will Enhance the Safety and Efficiency of the DOE's Remote Handled Transuranic Waste Disposal Operations  

SciTech Connect (OSTI)

The Waste Isolation Pilot Plant (WIPP) disposal operation currently employs two different disposal methods: one for Contact Handled (CH) waste and another for Remote Handled (RH) waste. CH waste is emplaced in a variety of payload container configurations on the floor of each disposal room. In contrast, RH waste is packaged into a single type of canister and emplaced in pre-drilled holes in the walls of disposal rooms. Emplacement of the RH waste in the walls must proceed in advance of CH waste emplacement. This poses a significant logistical constraint on waste handling operations by requiring significant coordination between waste characterization and preparations for shipping among the various generators. To improve operational efficiency, the Department of Energy (DOE) is proposing a new waste emplacement process for certain RH waste streams that can be safely managed in shielded containers. RH waste with relatively low gamma-emitting activity would be packaged in lead-lined containers, shipped to WIPP in existing certified transportation packages for CH waste, and emplaced in WIPP among the stacks of CH waste containers on the floor of a disposal room. RH waste with high gamma-emitting activity would continue to be emplaced in the boreholes along the walls. The new RH container appears essentially the same as a nominal 208-liter drum, but is built with about 2.5 cm of lead, sandwiched between thick steel sheet. The top and bottom are made of very thick plate steel, for strengthening the package to meet transportation requirements, and provide similar gamma attenuation. This robust configuration provides an overpack for waste that otherwise would be remotely handled. Up to a 3:1 reduction in number of shipments is projected if RH waste were transported in the proposed shielded containers. This paper describes the container design and testing, as well as the regulatory approach used to meet the requirements that apply to WIPP and its associated transportation system. This paper describes the RH transuranic waste inventory that may be candidates for packaging and emplacement in shielded containers. DOE does not propose to use shielded containers to increase the amount of RH waste allowed at WIPP. DOE's approach to gain approval for the transportation of shielded containers and to secure regulatory approval for use of shielded containers from WIPP regulators is discussed. Finally, the paper describes how DOE proposes to count the waste packaged into shielded containers against the RH waste inventory and how this will comply with the volume and radioactivity limitations imposed in the many and sometimes overlapping regulations that apply to WIPP. (authors)

Nelson, R.A. [U. S. Department of Energy, Carlsbad, New Mexico (United States); White, D.S. [Washington Group International, Carlsbad, New Mexico (United States)

2008-07-01T23:59:59.000Z

Note: This page contains sample records for the topic "ur3 ur4 payload" from the National Library of EnergyBeta (NLEBeta).
While these samples are representative of the content of NLEBeta,
they are not comprehensive nor are they the most current set.
We encourage you to perform a real-time search of NLEBeta
to obtain the most current and comprehensive results.


21

Compatibility issues of potential payloads for the USA/9904/B(U)F-85 RTG transportation system (RTGTS) for the {open_quotes}Pluto Express{close_quotes} mission  

SciTech Connect (OSTI)

The specific electric power system for the {open_quotes}Pluto Express{close_quotes} mission has yet to be specified. However, electric power will be provided by either radioisotopic thermoelectric generators (RTG), radioisotope thermophotovoltaic systems (RTPV), alkali metal thermal to electrical conversion (AMTEC) systems, radioisotope Stirling systems, or a combination of these. The selected radioisotopic power system will also be transported using the USA/9904/B(U)F-85, Radioisotope Thermoelectric Generator (RTG) Transportation System (RTGTS). As a result, all of the potential payloads present uniquely different environmental and physical configuration requirements. This paper presents the major compatibility issues of the potential payloads for the USA/9904/B(U)F-85 RTG Transportation System for the {open_quotes}Pluto Express{close_quotes} mission. {copyright} {ital 1997 American Institute of Physics.}

Miller, R.G.; Barklay, C.D.; Howell, E.I. [EGG Mound Applied Technologies P.O. Box 3000 Miamisburg, Ohio45343-3000 (United States); Frazier, T.A. [U.S. Department of Energy P.O. Box 66 Miamisburg, Ohio45343-0066 (United States)

1997-01-01T23:59:59.000Z

22

Technology Investments Mission and Payload  

E-Print Network [OSTI]

opportunities. #12;Mission Overview · Mission Description: ­ Atmospheric gas columns for air quality forecasts) · Characterization of lab prototype of the SWIR (2.3 um) subsystem of an infrared gas filter correlation radiometer

Christian, Eric

23

Technology Investments Mission and Payload  

E-Print Network [OSTI]

opportunities. #12;3 Mission Overview · Mission Description: ­ Atmospheric gas columns for air quality forecasts of lab prototype of the SWIR (2.3 um) subsystem of an infrared gas filter correlation radiometer for GEO

Christian, Eric

24

COOPERATIVE AND SUPERVISORY CONTROL FOR PAYLOAD MANIPULATION  

E-Print Network [OSTI]

, battery information functions, path planning algorithms, and trajectory tracking control laws. A hardware demonstration was produced that showed the robot performing the desired the user communicated through patterns. v DEDICATION I would... through the central computer. Another important piece of information that can be communicated is the current battery charge and capacity of the robot. After the user commands a task to the robot through the use of a pattern, the robot measures its...

Holmstrom, Kristen

2009-06-09T23:59:59.000Z

25

IMiniature Integrated Payload Suites 2010 Phase II  

E-Print Network [OSTI]

Exchange Membrane (PEM) water-electrolysis fuel cell supplies gH2/gO2 to a simple pressure-fed thruster pointing to enable the low-cost CubeSat platform to be used to conduct high-performance missions. The Power-Isp fuel. Second, a deployable solar array that stows along the long sides of the CubeSat and deploys

26

How to lighten trucks to haul bigger payloads  

SciTech Connect (OSTI)

The paper discusses how lighter truck components can be used wisely for the highway transportation of coal, with maintenance and costs in mind, to increase the hauling capacity of trucks.

Smiely, C.H.

1981-07-01T23:59:59.000Z

27

Update on the Micro-X Sounding Rocket payload  

E-Print Network [OSTI]

The Micro-X High Resolution Microcalorimeter X-ray Imaging Rocket is a sounding rocket experiment that will combine a transition-edge-sensor X-ray-microcalorimeter array with a conical imaging mirror to obtain high- ...

Figueroa-Feliciano, Enectal

28

Shielded Payload Containers Will Enhance the Safety and  

E-Print Network [OSTI]

) · External dimensions = 55-gal drum, internal capacity for a standard 30-gallon drum · Transport in 3-pack within ICV · 6.5 inch crush of bottom end axial dunnage and aluminum honeycomb spacer equates

29

On the Limits of Payload-Oblivious Network Attack Detection  

E-Print Network [OSTI]

alarms in order to detect them consistently. Keywords: network intrusion detection, ROC curve, evaluation. 1 Introduction We address the problem of evaluating network intrusion detection systems to the form of log data, encryption or simply a high connection failure rate--methods for detecting

Reiter, Michael

30

ARM-UAV TWP-ICE Payload Instrumentation Details  

Broader source: All U.S. Department of Energy (DOE) Office Webpages (Extended Search)

AFDC Printable Version Share this resource Send a link to EERE: Alternative Fuels Data Center Home Page to someone by E-mail Share EERE: Alternative Fuels Data Center Home Page on Facebook Tweet about EERE: Alternative Fuels Data Center Home Page on Twitter Bookmark EERE:1 First Use of Energy for All Purposes (Fuel and Nonfuel),Feet) Year Jan Feb Mar Apr MayAtmospheric Optical Depth (AOD)Productssondeadjustsondeadjust DocumentationARMStreamsUS Department of

31

Contact-Handled Transuranic Waste Authorized Methods for Payload Control  

Office of Environmental Management (EM)

AFDC Printable Version Share this resource Send a link to EERE: Alternative Fuels Data Center Home Page to someone by E-mail Share EERE: Alternative Fuels Data Center Home Page on Facebook Tweet about EERE: Alternative Fuels Data Center Home Page on Twitter Bookmark EERE:1 First Use of Energy for All Purposes (Fuel and Nonfuel),Feet) Year Jan Feb Mar Apr May Jun Jul(Summary) "of Energy Power Systems EngineeringDepartmentSmart Grid RFI:FresnoM-WG Idaho,Construction(CH TRAMPAC) |

32

Globally Stable Neural Robot Control Capable of Payload Adaptation M. Jansen and R. Eckmiller  

E-Print Network [OSTI]

for all positions and loads following the training phase, as well as the application of the networks

Behnke, Sven

33

A lean safety review process for payloads on the International Space Station  

E-Print Network [OSTI]

The International Space Station has the potential to serve as a unique test platform to enable technologies for a wide array of manned and unmanned NASA missions. In order to live up to its promise, the resources required ...

Luis, Javier de

2003-01-01T23:59:59.000Z

34

Test report for PAS-1 cask certification for shipping payload B  

SciTech Connect (OSTI)

This test report documents the successful inspection and testing to certify two NuPac PAS-1 casks in accordance with US Department of Energy Certificate of Compliance (CoC) USA/9184/B(U). The primary and secondary containment vessels of each cask met the acceptance criteria defined in the CoC and the test plan.

MERCADO, J.E.

1998-10-13T23:59:59.000Z

35

Design of a Surface Albedo Modification Payload for Near Earth Asteroid (NEA) Mitigation  

E-Print Network [OSTI]

The development of the Surface Albedo Treatment System (SATS) onboard a spacecraft mission to the near earth asteroid (NEA) Apophis in 2012 is an innovative concept of deflecting NEAs from possible impact with the Earth through altering...

Ge, Shen

2011-10-21T23:59:59.000Z

36

Suitability of Shape Memory Alloys for vibration isolation with application to launch vehicle payloads  

E-Print Network [OSTI]

This work details an investigation into the suitability of Shape Memory Alloys for the task of vibration isolation based on the similarities between the Shape Memory Alloy pseudoelastic behavior and the softening response of isolators whose response...

Mayes, John Jeramy

2001-01-01T23:59:59.000Z

37

E-Print Network 3.0 - allowable trupact-ii payload Sample Search...  

Broader source: All U.S. Department of Energy (DOE) Office Webpages (Extended Search)

with > 1 wt% Special... . After defining and evaluating the container geometries, loading ... Source: Yucca Mountain Project, US EPA Collection: Environmental Sciences and...

38

Payload-envelope detection and label-detection integrated photonic circuit for asynchronous variable-length optical-packet switching with 40-Gb/s RZ payloads and 10-Gb/s NRZ labels  

E-Print Network [OSTI]

ing and Integrated Optoelectronics Laboratory, University ofinterests include optoelectronics integration and packaging,

Koch, B R; Hu, Z Y; Bowers, J E; Blumenthal, D J

2006-01-01T23:59:59.000Z

39

RADIOISOTOPE-DRIVEN DUAL-MODE PROPULSION SYSTEM FOR CUBESAT-SCALE PAYLOADS TO THE OUTER PLANETS  

SciTech Connect (OSTI)

It is apparent the cost of planetary exploration is rising as mission budgets declining. Currently small scientific beds geared to performing limited tasks are being developed and launched into low earth orbit (LEO) in the form of small-scale satellite units, i.e., CubeSats. These micro- and nano-satellites are gaining popularity among the university and science communities due to their relatively low cost and design flexibility. To date these small units have been limited to performing tasks in LEO utilizing solar-based power. If a reasonable propulsion system could be developed, these CubeSat platforms could perform exploration of various extra-terrestrial bodies within the solar system engaging a broader range of researchers. Additionally, being mindful of mass, smaller cheaper launch vehicles (approximately 1,000 kgs to LEO) can be targeted. Thus, in effect, allows for beneficial exploration to be conducted within limited budgets. Researchers at the Center for Space Nuclear Research (CSNR) are proposing a low mass, radioisotope-based, dual-mode propulsion system capable of extending the exploration realm of these CubeSats out of LEO.

N. D. Jerred; T. M. Howe; S. D. Howe; A. Rajguru

2014-02-01T23:59:59.000Z

40

Synchronized Position Hold Engage & Reorient Experimental Satellites Massachusetts Institute of Technology, Space Systems Laboratory partnered with Payload Systems, Inc.  

E-Print Network [OSTI]

multi-aperture telescope or interferometer Space based fuel depot Multi-vehicle Mars mission architectures Routine and autonomous formation flight is essential to the operation of these missions Long ranges Tethered Formation Flight Synchronized Wireless Autonomous Reconfigurable Modules (SWARM

de Weck, Olivier L.

Note: This page contains sample records for the topic "ur3 ur4 payload" from the National Library of EnergyBeta (NLEBeta).
While these samples are representative of the content of NLEBeta,
they are not comprehensive nor are they the most current set.
We encourage you to perform a real-time search of NLEBeta
to obtain the most current and comprehensive results.


41

Modeling Techniques Used to Analyze Safety of Payloads for Generic Missile Type Weapons Systems During an Indirect Lightning Strike  

SciTech Connect (OSTI)

During lightning strikes buildings and other structures can act as imperfect Faraday Cages, enabling electromagnetic fields to be developed inside the facilities. Some equipment stored inside these facilities may unfortunately act as antenna systems. It is important to have techniques developed to analyze how much voltage, current, or energy dissipation may be developed over valuable components. In this discussion we will demonstrate the modeling techniques used to accurately analyze a generic missile type weapons system as it goes through different stages of assembly. As work is performed on weapons systems detonator cables can become exposed. These cables will form different monopole and loop type antenna systems that must be analyzed to determine the voltages developed over the detonator regions. Due to the low frequencies of lightning pulses, a lumped element circuit model can be developed to help analyze the different antenna configurations. We will show an example of how numerical modeling can be used to develop the lumped element circuit models used to calculate voltage, current, or energy dissipated over the detonator region of a generic missile type weapons system.

Perkins, M P; Ong, M M; Crull, E W; Brown Jr., C G

2009-07-21T23:59:59.000Z

42

Appears in Proc. International Workshop on Planning and Scheduling for Space, Moffett Field, CA, March 2013. Onboard Mission Planning on the Intelligent Payload  

E-Print Network [OSTI]

solar panels for electrical power generation and is anticipated to have 1-1.5W powe of Technology, under a contract with the National Aeronautics and Space Administration. data rates would require

Schaffer, Steven

43

CH Packaging Operations Manual  

SciTech Connect (OSTI)

This procedure provides instructions forassembling the following CH packaging payload: Drum payload assembly Standard Waste Box (SWB) assembly Ten-Drum Overpack (TDOP)

Washington TRU Solutions LLC

2007-11-29T23:59:59.000Z

44

CH Packaging Operations for High Wattage Waste  

SciTech Connect (OSTI)

This document provides instructions for assembling the following CH packaging payload: Drum payload assembly Standard Waste Box (SWB) assembly Ten-Drum Overpack (TDOP)

Washington TRU Solutions LLC

2006-01-06T23:59:59.000Z

45

CH Packaging Operations for High Wattage Waste at LANL  

SciTech Connect (OSTI)

This procedure provides instructions for assembling the following CH packaging payload: Drum payload assembly Standard Waste Box (SWB) assembly Ten-Drum Overpack (TDOP).

Washington TRU Solutions LLC

2005-04-04T23:59:59.000Z

46

CH Packaging Operations Manual  

SciTech Connect (OSTI)

This procedure provides instructions forassembling the following CH packaging payload: Drum payload assembly Standard Waste Box (SWB) assembly Ten-Drum Overpack (TDOP)

Washington TRU Solutions LLC

2007-08-22T23:59:59.000Z

47

CH Packaging Operations for High Wattage Waste at LANL  

SciTech Connect (OSTI)

This procedure provides instructions for assembling the following CH packaging payload: Drum payload assembly Standard Waste Box (SWB) assembly Ten-Drum Overpack (TDOP).

Washington TRU Solutions LLC

2005-04-13T23:59:59.000Z

48

CH Packaging Operations Manual  

SciTech Connect (OSTI)

Introduction - This procedure provides instructions for assembling the following CH packaging payload: -Drum payload assembly -Standard Waste Box (SWB) assembly -Ten-Drum Overpack (TDOP).

Washington TRU Solutions LLC

2003-06-26T23:59:59.000Z

49

CH Packaging Operations Manual  

SciTech Connect (OSTI)

Introduction - This procedure provides instructions forassembling the following CH packaging payload: Drum payload assembly Standard Waste Box (SWB) assembly Ten-Drum Overpack (TDOP)

Washington TRU Solutions LLC

2007-05-15T23:59:59.000Z

50

CH Packaging Operations Manual  

SciTech Connect (OSTI)

Introduction - This procedure provides instructions forassembling the following CH packaging payload: Drum payload assembly Standard Waste Box (SWB) assembly Ten-Drum Overpack (TDOP)

Washington TRU Solutions LLC

2006-12-18T23:59:59.000Z

51

CH Packaging Operations Manual  

SciTech Connect (OSTI)

This document provides the user with instructions for assembling a payload. All the steps in Subsections 1.2, Preparing 55-Gallon Drum Payload Assembly; 1.3, Preparing "Short" 85-Gallon Drum Payload Assembly (TRUPACT-II and HalfPACT); 1.4, Preparing "Tall" 85-Gallon Drum Payload Assembly (HalfPACT only); 1.5, Preparing 100-Gallon Drum Payload Assembly; 1.6, Preparing SWB Payload Assembly; and 1.7, Preparing TDOP Payload Assembly, must be completed, but may be performed in any order as long as radiological control steps are not bypassed.

Washington TRU Solutions LLC

2005-02-28T23:59:59.000Z

52

Recommendations and Justifications To Remove Use Restrictions Established under the U.S. Department of Energy, National Nuclear Security Administration Nevada Field Office Federal Facility Agreement and Consent Order, Revision 0  

SciTech Connect (OSTI)

This document is part of an effort to reevaluate 37 FFACO and Administrative URs against the current Soils Risk-Based Corrective Action Evaluation Process. After reviewing 37 existing FFACO and Administrative URs, 3 URs addressed in this document have sufficient information to determine that these current URs may be removed, based on the RBCA criteria. This document presents recommendations on modifications to existing URs that will be consistent with the RBCA criteria.

Birney, Cathleen; Krauss, Mark J

2013-09-01T23:59:59.000Z

53

Mixed convection and heat management in the Mars gravity biosatellite  

E-Print Network [OSTI]

The Mars Gravity Biosatellite will house fifteen mice in a low Earth orbit satellite spinning about its longitudinal axis. The satellite's payload thermal control system will reject heat through the base of the payload ...

Marsh, Jesse B. (Jesse Benjamin)

2007-01-01T23:59:59.000Z

54

Bespoke Balloon Launched Sensorcraft for Atmospheric Research Missions  

E-Print Network [OSTI]

to input mission and payload requirements and quickly receive designs that can be 3D printed and flown the scientific payload needs to be specified. The additional hardware required for flight, such as batteries

Sóbester, András

55

A stereo vision system for support of planetary surface exploration  

E-Print Network [OSTI]

and for controlling the motion of the rover, using light emitting diodes on the payload cab of the rover

Pollefeys, Marc

56

Calibration, Terrain Reconstruction and Path Planning for a Planetary Exploration System  

E-Print Network [OSTI]

and localization of the rover. The lat- ter makes use of four Light Emitting Diodes on the rover payload cab

Pollefeys, Marc

57

A stereo vision system for support of planetary surface exploration  

E-Print Network [OSTI]

and for controlling the motion of the rover, using Light Emitting Diodes on the payload cab of the rover

Pollefeys, Marc

58

Radioisotope thermoelectric generator transportation system safety analysis report for packaging. Volumes 1 and 2  

SciTech Connect (OSTI)

This SARP describes the RTG Transportation System Package, a Type B(U) packaging system that is used to transport an RTG or similar payload. The payload, which is included in this SARP, is a generic, enveloping payload that specifically encompasses the General Purpose Heat Source (GPHS) RTG payload. The package consists of two independent containment systems mounted on a shock isolation transport skid and transported within an exclusive-use trailer.

Ferrell, P.C.

1996-04-18T23:59:59.000Z

59

Passive orientation apparatus  

DOE Patents [OSTI]

An apparatus that can return a payload to a known orientation after unknown motion, without requiring external power or complex mechanical systems. The apparatus comprises a faceted cage that causes the system to rest in a stable position and orientation after arbitrary motion. A gimbal is mounted with the faceted cage and holds the payload, allowing the payload to move relative to the stable faceted cage. The payload is thereby placed in a known orientation by the interaction of gravity with the geometry of the faceted cage, the mass of the system, and the motion of the payload and gimbal. No additional energy, control, or mechanical actuation is required. The apparatus is suitable for use in applications requiring positioning of a payload to a known orientation after arbitrary or uncontrolled motion, including remote sensing and mobile robot applications.

Spletzer, Barry L. (Albuquerque, NM); Fischer, Gary J. (Albuquerque, NM); Martinez, Michael A. (Albuquerque, NM)

2001-01-01T23:59:59.000Z

60

A serially concatenated BCH-Turbo code scheme over an Additive White Gaussion Noise channel  

E-Print Network [OSTI]

, ;q(s', s) P(sls')p(yr-Is' s) 21 DE- INTERLEA VER. e L21 Ip Y MAP DECODER I e 12 N-BIT INTERLEAVER. MAP DECODER 2. e y N-BIT INTERLEAVER. 2p y Fig. 5. Turbo code rlecoder P(uI )p(yk ur) (3. 27) where P() stands for the probability... 3 4 7 9 12 16 17 20 25 25 25 27 29 33 33 35 38 REFERENCES APPENDIX A 41 VITA LIST OF TABLES TABLE Page I Berlckamp-Massey algorithm , 'l l LIST OF FIGURES FIGURE Page Convolui, ional encoder for s, (2, 1, 2) convolutional...

Ovalekar, Sameer V.

1997-01-01T23:59:59.000Z

Note: This page contains sample records for the topic "ur3 ur4 payload" from the National Library of EnergyBeta (NLEBeta).
While these samples are representative of the content of NLEBeta,
they are not comprehensive nor are they the most current set.
We encourage you to perform a real-time search of NLEBeta
to obtain the most current and comprehensive results.


61

air force bombers: Topics by E-print Network  

Broader source: All U.S. Department of Energy (DOE) Office Webpages (Extended Search)

Engagement Effectiveness 12;Aircrew at Risk The Value of Range, Payload, Precision, and Stealth Bomb Droppers Air Escort Air Defense Suppression Tankers Total Aircrew At Risk...

62

Energy Blog | Department of Energy  

Broader source: Energy.gov (indexed) [DOE]

from Cape Canaveral with the most advanced payload of scientific gear ever used on the red planet -- made possible by nuclear space power systems developed by the Energy...

63

The Development of Instrumentation and Methods for Measurement of Air-Sea Interaction and Coastal Processes from Manned and Unmanned Aircraft /  

E-Print Network [OSTI]

NovAtel SPAN circuitry FLIR long-wave IR camera (A325)payload also includes a FLIR (Willsonville, Oregon) A325

Reineman, Benjamin D.

2013-01-01T23:59:59.000Z

64

Correspondence: Email: korpela@ssl.berkeley.edu; Telephone: (510) 643-6538; URL: http://setiathome.ssl.berkeley.edu/~korpela  

E-Print Network [OSTI]

___________________ Correspondence: Email: korpela@ssl.berkeley.edu; Telephone: (510) 643-6538; URL: http://setiathome.ssl.berkeley.edu/~korpela The SPEAR Science Payload Eric J. Korpelaa , Jerry

Korpela, Eric J.

65

E-Print Network 3.0 - atmosphere research launch Sample Search...  

Broader source: All U.S. Department of Energy (DOE) Office Webpages (Extended Search)

and development and launch payloads... components," Flynn says. "We hope to be self-sustaining," sharing the cost of future ... Source: Dong, Yingfei - Department of Electrical...

66

Discrete linear constrained multivariate optimization for power sources of mobile systems.  

E-Print Network [OSTI]

??Unmanned ground and aerial vehicles (UGVs and UAVs) have strict payload limitations, limited free space affecting on board power availability resulting in limited endurance and (more)

Ioannou, Stelios G

2008-01-01T23:59:59.000Z

67

Autonomous Realtime Threat-Hunting Robot (ARTHR  

ScienceCinema (OSTI)

Idaho National Laboratory researchers developed an intelligent plug-and-play robot payload that transforms commercial robots into effective first responders for deadly chemical, radiological and explosive threats.

INL

2009-09-01T23:59:59.000Z

68

Attack Generation for NIDS Testing Using Natural Deduction Shai Rubin, Somesh Jha and Barton P. Miller  

E-Print Network [OSTI]

Attack Generation for NIDS Testing Using Natural Deduction Shai Rubin, Somesh Jha and Barton P. Miller January 23, 2004 Abstract A common way to elude a signature-based NIDS is to transform an attack matching between the attack payload and the NIDS signature, attackers split the payload into several TCP

Miller, Barton P.

69

Attack Generation for NIDS Testing Using Natural Deduction Shai Rubin, Somesh Jha and Barton P. Miller  

E-Print Network [OSTI]

Attack Generation for NIDS Testing Using Natural Deduction Shai Rubin, Somesh Jha and Barton P. Miller January 23, 2004 Abstract A common way to elude a signature­based NIDS is to transform an attack matching between the attack payload and the NIDS signature, attackers split the payload into several TCP

Liblit, Ben

70

Internet Engineering Task Force Individual Submission INTERNETDRAFT Lennox/Schulzrinne  

E-Print Network [OSTI]

­lennox­sip­reg­payload­01.ps Columbia University October 31, 2000 Expires: April 2001 Transporting User Control Information in SIP REGISTER Payloads Status of this Memo This document is an Internet­Draft and is in full conformance with all provisions of Section 10 of RFC2026. Internet­Drafts are working documents

Lennox, Jonathan

71

Internet Engineering Task Force Individual Submission INTERNET-DRAFT Lennox/Schulzrinne  

E-Print Network [OSTI]

-lennox-sip-reg-payload-01.ps Columbia University October 31, 2000 Expires: April 2001 Transporting User Control Information in SIP REGISTER Payloads Status of this Memo This document is an Internet-Draft and is in full conformance with all provisions of Section 10 of RFC2026. Internet-Drafts are working documents

Lennox, Jonathan

72

Internet Engineering Task Force Individual Submission INTERNETDRAFT Lennox/Schulzrinne  

E-Print Network [OSTI]

­lennox­sip­reg­payload­00.ps Columbia University March 6, 2000 Expires: September 2000 Transporting User Control Information in SIP REGISTER Payloads Status of this Memo This document is an Internet­Draft and is in full conformance with all provisions of Section 10 of RFC2026. Internet­Drafts are working documents

Lennox, Jonathan

73

Water-soluble carbon nanotube compositions for drug delivery and medicinal applications  

DOE Patents [OSTI]

Compositions comprising a plurality of functionalized carbon nanotubes and at least one type of payload molecule are provided herein. The compositions are soluble in water and PBS in some embodiments. In certain embodiments, the payload molecules are insoluble in water. Methods are described for making the compositions and administering the compositions. An extended release formulation for paclitaxel utilizing functionalized carbon nanotubes is also described.

Tour, James M.; Lucente-Schultz, Rebecca; Leonard, Ashley; Kosynkin, Dmitry V.; Price, Brandi Katherine; Hudson, Jared L.; Conyers, Jr., Jodie L.; Moore, Valerie C.; Casscells, S. Ward; Myers, Jeffrey N.; Milas, Zvonimir L.; Mason, Kathy A.; Milas, Luka

2014-07-22T23:59:59.000Z

74

BLINC: Multilevel Traffic Classification in the Dark  

E-Print Network [OSTI]

the dark" ­ No port numbers ­ No payload web streaming P2P #12;3 The problem of workload characterizationBLINC: Multilevel Traffic Classification in the Dark Thomas Karagiannis, UC Riverside Konstantina ­ Why in the dark? · Traffic profiling based on TCP/UDP ports ­ Misleading · Payload

Rajamani, Sriram K.

75

A consumer panel test of Texas fortified red grapefruit juice  

E-Print Network [OSTI]

'. ?ET iCTEi TIAL FCF T"XAS FOFTIFIN R&X 38 67 CiiAPTER X B IHL IOGRAP HY AH '-'IX GiiAFEFRUIT JUICE CO', ~LUCIO". '. S. 74 80 Figure ', ''o. Page l. 2 ~ 3. Relationship between Index of Fading, Visual Color, and Lycopene and Carotene pie... of 1'58. Two taste . !-n. lo . !ere us?i' ? an oxf crt fin& non-evi srt taste 2! nel. The iix?ort fan?!1 ?nnioted ci' cix i?ricul+ur 3 an' ' ech!inicfll ollege of TeXaa SmplOyc . ;!!lc !lad OX?O"S" VO t&. at(~?" eX; erf enCe O"8 were Cap ?le Of' c...

Price, Carter

1959-01-01T23:59:59.000Z

76

Development of a Shape-Memory-Alloy Actuated Biomimetic Hydrofoil O.K. Rediniotis  

E-Print Network [OSTI]

in the device for control systems and payload. In actuator technology, active or "smart" materials have opened of SMA actuation, let us consider an underwater vehicle on the order of 2 meters in length. Suppose

77

HEV Fleet Testing - Summary Fact Sheet 2010 Ford Fusion vin#4757  

Broader source: Energy.gov (indexed) [DOE]

www.eere.energy.govinformationcenter Vehicle Specifications Engine: 2.5 L 4-cylinder Electric Motor: 60 kW Battery: NiMH Seatbelt Positions: Five Payload: 850 lbs Features:...

78

HEV Fleet Testing - Summary Fact Sheet for 2010 Ford Fusion  

Broader source: Energy.gov (indexed) [DOE]

Ford Fusion VIN 3FADP0L32AR194699 Vehicle Specifications Engine: 2.5 L 4-cylinder Electric Motor: 60 kW Battery: NiMH Seatbelt Positions: Five Payload: 850 lbs Features:...

79

HEV Fleet Testing - Summary Fact Sheet 2011 Hyundai Sonata vin...  

Broader source: Energy.gov (indexed) [DOE]

Hyundai Sonata VIN KMHEC4A47BA003539 Vehicle Specifications Engine: 2.4 L Electric Motor: 30 kW Battery: Lithium Polymer Seatbelt Positions: Five Payload: 1074 lbs Features:...

80

HEV Fleet Testing - Summary Fact Sheet 2011 Hyundai Sonata vin...  

Broader source: Energy.gov (indexed) [DOE]

2011 Hyundai Sonata VIN KMHEC4A43BA004932 Vehicle Specifications Engine: 2.4 L Electric Motor: 30 kW Battery: Lithium Polymer Seatbelt Positions: Five Payload: 1074 lbs Features:...

Note: This page contains sample records for the topic "ur3 ur4 payload" from the National Library of EnergyBeta (NLEBeta).
While these samples are representative of the content of NLEBeta,
they are not comprehensive nor are they the most current set.
We encourage you to perform a real-time search of NLEBeta
to obtain the most current and comprehensive results.


81

HEV Fleet Testing - Summary Fact Sheet 2010 Toyota Prius  

Broader source: Energy.gov (indexed) [DOE]

Toyota Prius VIN JTDKN3DU2A5010462 Vehicle Specifications Engine: 1.8 L 4-cylinder Electric Motor: 60 kW Battery: NiMH Seatbelt Positions: Five Payload: 885 lbs Features:...

82

Design and development of a high-altitude, in-flight-deployable micro-UAV  

E-Print Network [OSTI]

A micro-UAV ([mu] UAV) system was developed to provide maximum endurance for a small atmospheric sensing payload. The system, composed of a ([mu] UAV) and protective case, folds and fits into a MJU-10/B flare cartridge ...

Tao, Tony S

2012-01-01T23:59:59.000Z

83

Reconfiguration methods for on-orbit servicing, assembly, and operations with application to space telescopes  

E-Print Network [OSTI]

Reconfiguration is an important characteristic in furthering on-orbit servicing, assembly, and operations. Previous work has focused on large assemblers manipulating small payloads, where the dynamics of the assembler is ...

Mohan, Swati

2007-01-01T23:59:59.000Z

84

George F. Chapline EGG-M-88285 Lawrence Livermore National Laboratory  

Office of Scientific and Technical Information (OSTI)

payloads to the nearest star. Alpha Centauri, in about a hundred years or very rapid solar system transport. The parameters reported in this paper are based on a very...

85

Microsoft Outlook - Memo Style  

National Nuclear Security Administration (NNSA)

No Internal Volume (m3) 1.89 Payload Volume (m3) 1.89 Steel Density (kgm3) 153.5 Plastic Density (kgm3) 1.2 Lead Density (kgm3) 0 Cellulosics Density (kgm3) 0 Stored...

86

Design of an adaptive 3-dimensional display enabled by a swarm of autonomous micro air vehicles  

E-Print Network [OSTI]

This thesis is motivated by the concept of a system consisting of a swarm of small, automatically controlled air vehicles, each carrying a colour-controlled light source (payload), capable of executing coordinated maneouvres ...

Mueller, Erich, S.M. Massachusetts Institute of Technology

2012-01-01T23:59:59.000Z

87

Methods of and system for swing damping movement of suspended objects  

DOE Patents [OSTI]

A payload suspended from a gantry is swing damped in accordance with a control algorithm based on the periodic motion of the suspended mass or by servoing on the forces induced by the suspended mass. 13 figures.

Jones, J.F.; Petterson, B.J.; Strip, D.R.

1991-03-05T23:59:59.000Z

88

Virus constructed iron phosphate lithium ion batteries in unmanned aircraft systems  

E-Print Network [OSTI]

FePO? lithium ion batteries that have cathodes constructed by viruses are scaled up in size to examine potential for use as an auxiliary battery in the Raven to power the payload equipment. These batteries are assembled ...

Kolesnikov-Lindsey, Rachel

89

Comparison of heat sink and fan combinations and thermal electric coolers for use in the Mars Gravity Biosatellite  

E-Print Network [OSTI]

An experiment was conducted to help compare possible cooling methods for the payload module of the Mars Gravity Biosatellite. The Satellite will be launched into space with 15 mice on board and rotated to create a 0.38g ...

Parness, Aaron J. (Aaron Joseph), 1981-

2004-01-01T23:59:59.000Z

90

Autonomous Realtime Threat-Hunting Robot (ARTHR)  

ScienceCinema (OSTI)

Idaho National Laboratory researchers developed an intelligent plug-and-play robot payload that transforms commercial robots into effective first responders for deadly chemical, radiological and explosive threats. To learn more, visit

Idaho National Laboratory - David Bruemmer, Curtis Nielsen

2010-01-08T23:59:59.000Z

91

IAC-06-B5.7.05 CDHS DESIGN FOR A UNIVERSITY NANO-SATELLITE  

E-Print Network [OSTI]

. These payloads are: · Thin Film Solar Cells (TFSC), developed and 1 #12;provided by the Dutch company Dutch Space by the following functionality: · Processing, storage, distribution and execution of received telecommands

Kuzmanov, Georgi

92

Review Article Huygens HASI servo accelerometer: A review and lessons learned  

E-Print Network [OSTI]

Review Article Huygens HASI servo accelerometer: A review and lessons learned B. Hathi a,?, A. Techniques used for data analysis and lessons learned that may be useful for accelerometry payloads on future . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1323 2.4. Lessons learned

Withers, Paul

93

SHIELDED CONTAINER COMPLETENESS COMMENTS July 13, 2010  

E-Print Network [OSTI]

the possible dose rate changes at the surface of the package for the intended payloads to be shipped. The same concerns as outlined above apply here. Reference WTS 2008. Shielded Container Type A Evaluation Report, ECO

94

A UAV MISSION HIERARCHY C. E. NEHME  

E-Print Network [OSTI]

Surveillance Payload Delivery Electronic warfare Target Designation Static Target Dynamic Target Dynamic Target* UAV Missions Intelligence/ Reconnaissance SurveillanceInsertion Electronic Attack Electronic) and can include, for example, the rendering of facilities inoperable (electronic jamming

Cummings, Mary "Missy"

95

CH Packaging Operations Manual  

SciTech Connect (OSTI)

This procedure provides instructions for assembling the CH Packaging Drum payload assembly, Standard Waste Box (SWB) assembly, Abnormal Operations and ICV and OCV Preshipment Leakage Rate Tests on the packaging seals, using a nondestructive Helium (He) Leak Test.

Washington TRU Solutions LLC

2005-06-13T23:59:59.000Z

96

Element and system design for active and passive vibration isolation  

E-Print Network [OSTI]

This thesis focusses on broadband vibration isolation, with an emphasis on control of absolute payload motion for ultra-precision instruments such as the MIT/Caltech Laser-Interferometric Gravitational Wave Observatory ...

Zuo, Lei, 1974-

2005-01-01T23:59:59.000Z

97

An analysis of the SCEX 3 ionospheric electron beam injection experiment  

SciTech Connect (OSTI)

The SCEX 3 experiment (Several Compatible EXperiments using a rocket-borne accelerator) was carried to ionospheric altitudes (375 km) by a Black Brant 11 rocket on February 1, 1990. The experiment was launched from Poker Flat Research Range (65.1 degree N, 147.5 degree W) at 1207 UT. The payload split into two parts (hereafter forward and aft payloads) 116 seconds after launch. The aft payload carried two electron accelerators as well as several diagnostic instruments. The forward payload was ejected at an angle of 6 degree with the magnetic field in a northwesterly direction. This payload carried a multiband plasma wave receiver and various particle detectors to make in situ measurements of the Beam Plasma Interaction (BPI) region. Two Throw Away Detectors (TAD's 1 and 2) were also ejected from the aft payload in the east and west directions respectively. TAD 1 also carried a multiband plasma wave receiver. Preceding the launch an auroral arch along the southern boundary of a diffuse auroral patch suddenly brightened, split into two separate arcs and moved to a position north of the rocket's trajectory. SCEX 3 was launched into an active breakup aurora consisting of tall rays and diffuse patches. The purpose of this experiment were (1) to observe injected electrons reflected from the naturally occurring parallel electric field structures which are thought to accelerate the auroral electron, (2) to observe a variety of plasma effects caused by the artificial electron beam and the associated spacecraft charging, and (3) study the natural phenomena associated with auroral activity. This work is a summary of the interesting observations made by the SCEX 3 experiment. These observations include VHF emissions produced by the electron beam via the Beam Plasma Discharge (BPD), Diffuse resonance emissions by the hot plasma region surrounding the electron beam and auroral Z-mode emissions.

Goerke, R.T.

1992-01-01T23:59:59.000Z

98

Procurement of a fully licensed radioisotope thermoelectric generator transportation system  

SciTech Connect (OSTI)

A fully licensed transportation system for Radioisotope Thermoelectric Generators and Light-Weight Radioisotope Heater Units is currently being designed and built. The system will comply with all applicable U.S. Department of Transportation regulations without the use of a DOE Alternative.'' The U.S. Department of Transportation has special double containment'' requirements for plutonium. The system packaging uses a doubly contained bell jar'' concept. A refrigerated trailer is used for cooling the high-heat payloads. The same packaging is used for both high- and low-heat payloads. The system is scheduled to be available for use by mid-1992.

Adkins, H.E.; Bearden, T.E. (Westinghouse Hanford Company, P.O. Box 1970, N1-42, Richland, Washington 99352 (US))

1991-01-01T23:59:59.000Z

99

Procurement of a fully licensed radioisotope thermoelectric generator transportation system  

SciTech Connect (OSTI)

A fully licensed transportation system for Radioisotope Thermoelectric Generators and Light-Weight Radioisotope Heater Units is currently being designed and built. The system will comply with all applicable US Department of Transportation regulations without the use of a DOE Alternative.'' The US Department of Transportation has special double containment'' requirements for plutonium. The system packaging uses a doubly contained bell jar'' concept. A refrigerated trailer is used for cooling the high-heat payloads. The same packaging is used for both high- and low-heat payloads. The system is scheduled to be available for use by mid-1992. 4 refs., 4 figs., 2 tabs.

Adkins, H.E.; Bearden, T.E.

1990-10-01T23:59:59.000Z

100

Radiation environment along the INTEGRAL orbit measured with the IREM monitor  

E-Print Network [OSTI]

The INTEGRAL Radiation Environment Monitor (IREM) is a payload supporting instrument on board the INTEGRAL satellite. The monitor continually measures electron and proton fluxes along the orbit and provides this information to the spacecraft on board data handler. The mission alert system broadcasts it to the payload instruments enabling them to react accordingly to the current radiation level. Additionally, the IREM conducts its autonomous research mapping the Earth radiation environment for the space weather program. Its scientific data are available for further analysis almost without delay.

W. Hajdas; P. Bhler; C. Eggel; P. Favre; A. Mchedlishvili; A. Zehnder

2003-08-15T23:59:59.000Z

Note: This page contains sample records for the topic "ur3 ur4 payload" from the National Library of EnergyBeta (NLEBeta).
While these samples are representative of the content of NLEBeta,
they are not comprehensive nor are they the most current set.
We encourage you to perform a real-time search of NLEBeta
to obtain the most current and comprehensive results.


101

Container for radioactive materials  

DOE Patents [OSTI]

A container is claimed for housing a plurality of canister assemblies containing radioactive material. The several canister assemblies are stacked in a longitudinally spaced relation within a carrier to form a payload concentrically mounted within the container. The payload package includes a spacer for each canister assembly, said spacer comprising a base member longitudinally spacing adjacent canister assemblies from each other and sleeve surrounding the associated canister assembly for centering the same and conducting heat from the radioactive material in a desired flow path. 7 figures.

Fields, S.R.

1984-05-30T23:59:59.000Z

102

Design and Development of a High-Altitude, In-Flight-Deployable Micro-UAV  

E-Print Network [OSTI]

A micro-UAV system was developed to provide maximum endurance for a small atmospheric sensing payload. The system, composed of a micro-UAV and protective case, folds and fits into a MJU-10/B flare cartridge (7.1 x 2.4 ...

Tao, Tony S.

2012-06-11T23:59:59.000Z

103

System and method to improve the power output and longetivity of a radioisotope thermoelectric generator  

SciTech Connect (OSTI)

By using the helium generated by the alpha emissions of a thermoelectric generator during space travel for cooling, the thermal degradation of the thermoelectric generator can be slowed. Slowing degradation allows missions to be longer with little additional expense or payload.

Mowery, Jr., Alfred L. (Potomac, MD)

1993-01-01T23:59:59.000Z

104

System and method to improve the power output and longevity of a radioisotope thermoelectric generator  

SciTech Connect (OSTI)

By using the helium generated by the alpha emissions of a thermoelectric generator during space travel for cooling, the thermal degradation of the thermoelectric generator can be slowed. Slowing degradation allows missions to be longer with little additional expense or payload. 1 figures.

Mowery, A.L. Jr.

1993-09-21T23:59:59.000Z

105

National Aeronautics and Space Administration NASA embarks on the Tropical Composition,  

E-Print Network [OSTI]

role in determining how much solar energy is trapped in Earth's atmosphere. The TTL is the transitional capacity AC/DC electrical system, permitting it to carry a variety of payloads on a single mission Research Center Moffett Field, California, 94035 www.nasa.gov TC4 ER-2 Aircraft Platform Instruments

106

Flight Control System for a Micromechanical Flying Insect: Architecture and Implementation  

E-Print Network [OSTI]

of California at Berkeley {lusche|xinyan|sastry}@robotics.eecs.berkeley.edu Abstract This paper describes recent limited payload capacity and require still air, their unmatched maneuverability, low fab- rication cost UNIT MFI's POWER SUPPLY SOLAR CELLS BATTERIES UNIT ACTUATORS LOCOMOTORY UNIT MFI Control Trasduced

Sastry, S. Shankar

107

Sway control method and system for rotary cranes  

DOE Patents [OSTI]

Methods and apparatuses are disclosed for reducing the oscillatory motion of rotary crane payloads during operator-commanded or computer-controlled maneuvers. An Input-shaping filter receives input signals from multiple operator input devices and converts them into output signals readable by the crane controller to dampen the payload tangential and radial sway associated with rotation of the jib. The input signals are characterized by a hub rotation trajectory [gamma](t), which includes a jib angular acceleration [gamma], a trolley acceleration x, and a load-line length velocity L. The system state variables are characterized by a tangential rotation angle [theta](t) and a radial rotation angle [phi](t) of the load-line. The coupled equations of motion governing the filter are non-linear and configuration-dependent. In one embodiment, a filter is provided between the operator and the crane for filtering undesired frequencies from the angular [gamma] and trolley x velocities to suppress payload oscillation. In another embodiment, crane commands are computer generated and controlled to suppress vibration of the payload using a postulated asymmetrical shape for the acceleration profiles of the jib, which profiles are uniquely determined by a set of parameters (including the acceleration pulse amplitude and the duration and coast time between pulses), or a dynamic programming approach. 25 figs.

Robinett, R.D.; Parker, G.G.; Feddema, J.T.; Dohrmann, C.R.; Petterson, B.J.

1999-06-01T23:59:59.000Z

108

Patrick Scheuermann Center Director  

E-Print Network [OSTI]

propulsion test facilities; and ensured Stennis continued to serve as the systems engineering center at Stennis for NASA's Reusable Launch Vehicle program, a NASA-industry effort to develop a new generation of rockets to safely and cost-effectively send payloads to space. He also served as project manager

109

High Altitude Balloon Project At Penn State Wilkes-Barre  

E-Print Network [OSTI]

· Plasma Probes · Solar Cell Array · CO2 Horizon Sensor · Torque Coil Test · Viper PC104 Flight Test · Boom diameter at burst · 72 inch parachute · Payload · Multiple Pods · Student experiments · Sensors, cameras. · Magnetometer · OPT101 Light Sensors · Spectrometers · Geiger Counters · Altitude Valve Control · CUBE Sat

Lozano-Nieto, Albert

110

Applications of Robust, Radiation Hard AlGaN Optoelectronic Devices in Space Exploration and High Energy Density Physics  

SciTech Connect (OSTI)

This slide show presents: space exploration applications; high energy density physics applications; UV LED and photodiode radiation hardness; UV LED and photodiode space qualification; UV LED AC charge management; and UV LED satellite payload instruments. A UV LED satellite will be launched 2nd half 2012.

Sun, K.

2011-05-04T23:59:59.000Z

111

AlGaN UV LED and Photodiodes Radiation Hardness and Space Qualifications and Their Applications in Space Science and High Energy Density Physics  

SciTech Connect (OSTI)

This presentation provides an overview of robust, radiation hard AlGaN optoelectronic devices and their applications in space exploration & high energy density physics. Particularly, deep UV LED and deep UV photodiodes are discussed with regard to their applications, radiation hardness and space qualification. AC charge management of UV LED satellite payload instruments, which were to be launched in late 2012, is covered.

Sun, K. X.

2011-05-31T23:59:59.000Z

112

American Institute of Aeronautics and Astronautics Violet: A High-Agility Nanosatellite for Demonstrating  

E-Print Network [OSTI]

-precision sensors, such as a star tracker and a fiber-optic rate gyroscope, with high-agility kinematics: 10 o /sec ultraviolet telescope, which includes flight-spare Deep Impact CCDs and serves as a representative payload,7,11 . By providing an in-orbit testbed for steering algorithms, the Violet project is designed to uncover some

Peck, Mason A.

113

Sharif-Abadi and Joseph 1 Soft ground reaction to cyclic loading by large mobile mining equipment  

E-Print Network [OSTI]

opt for large mobile mining equipment. In the oil sand, loading and hauling of material results, truck and shovels operating on soft-ground will become less stable. Trucks in summer are frequently payloads the cycled ground after only a few passing trucks is unable to support the weight of the truck

Joseph, Tim Grain

114

P3s Public-Private Partnerships? Or Peripatetic Pain in the Pants  

E-Print Network [OSTI]

Vegas to Phoenix ! I-69 Texas to Indiana Rebuild with tolls + added capacity: ! Key long-haul truck"/shift in short-haul setting. ! Greater payloads in long-haul setting. ! Keys to trucking industry support Investment Need Is Improved Goods Movement ! Two types of toll truckway project: ! Short-haul port

Minnesota, University of

115

Introduction to special section on the Phoenix Mission: Landing Site Characterization Experiments, Mission Overviews, and  

E-Print Network [OSTI]

braking strategy. After a safe landing, twin fan-like solar panels are unfurled and provide the energy lander with a science payload inherited from MPL and 2001 instruments gives significant advantages, University of Ottawa, Ottawa, Ontario, Canada. 10 Max Planck Institute for Solar System Research, Katlenburg

Duck, Thomas J.

116

INTERNATIONAL JOURNAL OF ROBUST AND NONLINEAR CONTROL Int. J. Robust Nonlinear Control 2002; 12:207242 (DOI: 10.1002/rnc.683)  

E-Print Network [OSTI]

challenges. This paper presents fuel/time-optimal control algorithms for a co-ordination and control-line to analyse various aspects of the mission design and in real time as part of an onboard autonomous formation, and monitoring of the distributed vehicles in the cluster will be required to achieve the stringent payload

How, Jonathan P.

117

Experimental Cooperative Control of Fixed-Wing Unmanned Aerial Vehicles  

E-Print Network [OSTI]

Experimental Cooperative Control of Fixed-Wing Unmanned Aerial Vehicles Selcuk Bayraktar, Georgios architecture (Cloud cap technologies) Hybrid Modeling (of the Piccolo autopilot) Experiments Autonomous Flight - 20min #12;UAVs @ Penn Servos controlling the payload LaptopPC Dell X200 3.5HP fuel engine Deployable

Fainekos, Georgios E.

118

Fluid-Structure Interaction Simulations of a Tension-Cone Inflatable Aerodynamic Decelerator  

E-Print Network [OSTI]

Fluid-Structure Interaction Simulations of a Tension-Cone Inflatable Aerodynamic Decelerator of an aerodynamic tension-cone supersonic decelerator prototype intended for large mass payload deploy- ment. Introduction The concept of the inflatable aerodynamic decelerator (IAD) was first proposed in the 1960's

Cirak, Fehmi

119

Pg: 1 February 11, 2009 Surface Water and  

E-Print Network [OSTI]

-mesoscale and kinetic energy containing scales -- What is the small- scale (10-100 km) variability of ocean surface/C requirements: ·Payload power, mass: ~1.1KW, ~300Kg ·Stringent Pointing knowledge requirements ·High Data Rate · Use conventional Jason- class altimeter for nadir coverage and radiometer for wet-tropospheric delay

Christian, Eric

120

Safety Analysis for Packaging Steel Banded Wooden Shipping Containers  

SciTech Connect (OSTI)

This safety analysis report for packaging describes the steel banded wooden shipping containers, which are certified as Type AF packagings. The authorized payload for these containers is unirradiated, slightly enriched, uranium ingots, billets, extrusions, and scrap materials. The amount of uranium in the containers will not exceed the LSA-II material requirements as defined in 49 CFR 173.403.

FERRELL, P.C.

2000-12-05T23:59:59.000Z

Note: This page contains sample records for the topic "ur3 ur4 payload" from the National Library of EnergyBeta (NLEBeta).
While these samples are representative of the content of NLEBeta,
they are not comprehensive nor are they the most current set.
We encourage you to perform a real-time search of NLEBeta
to obtain the most current and comprehensive results.


121

Strong electric fields from positive lightning strokes in the stratosphere R. H. Holzworth,1  

E-Print Network [OSTI]

Strong electric fields from positive lightning strokes in the stratosphere R. H. Holzworth,1 M. P] A balloon payload launched in Brazil has measured vector electric fields from lightning at least an order of the electric field transient propagation. These measurements imply that lightning electric fields

Thomas, Jeremy N.

122

AlAA 92-0980 Design of Multipurpose Spacecraft BUS  

E-Print Network [OSTI]

. The spacecraft bus uses three- axis stabilization consisting of three reaction wheel system. The electric power system consists of single-axis tracking silicon solar array and Ni2 H2 batteries. The propulsion differences in orbit, yaw axis control, attitude pointing, and thermal control requirements. The AVHRR payload

123

SCIAMACHY MONITORING FACTORS: OBSERVATION AND END-TO-END CORRECTION OF INSTRUMENT PERFORMANCE DEGRADATION  

E-Print Network [OSTI]

DEGRADATION Klaus Bramstedt1 , Stefan No¨el1 , Heinrich Bovensmann1 , John P. Burrows1 , Christophe Lerot2Y) is a grating spectrometer in the UV-Vis-NIR spectral range. SCIA- MACHY is part of the ENVISAT payload-factors. Key words: SCIAMACHY; m-factors; degradation; mon- itoring. 1. INTRODUCTION SCIAMACHY [1] is now seven

Tilstra, Gijsbert

124

RISK PREDICTION OF A BEHAVIOR-BASED ADHESION CONTROL NETWORK FOR ONLINE SAFETY ANALYSIS OF  

E-Print Network [OSTI]

by default. But for wheeled driving on concrete walls via negative pressure adhesion a prediction of risks- ited payload. Also the impact of features like surface roughness, sheathing defects, porous areas is de- signed to be used for inspections of large concrete buildings as depicted in figure 1

Berns, Karsten

125

Page 1 of 2 Radiogram No. 8355u Form 24 for 02/05/2012  

E-Print Network [OSTI]

:00-14:40 FE-1 Maintenance. SM and FGB Flush Counter (), Water Supply System (SVO), POTOK Air Purification System Data Calldowns 14:35-14:40 FE-6 Payload MPC Restricted Playback Start 15:30-17:00 FE-1 Physical

Waliser, Duane E.

126

Light-induced transformation of vesicles to micelles and vesicle-gels to sols  

E-Print Network [OSTI]

molar ratios due to ionic interactions between the cationic and anionic headgroups. When irradiated of vesicles connected by polymer chains. Upon UV irradiation, the network is disrupted because and nutrients in foods, fragrances and dyes in cosmetics and textiles, etc.3­9 Payloads encapsulated in the core

Raghavan, Srinivasa

127

System and method to improve the power output and longetivity of a radioisotope thermoelectric generator  

SciTech Connect (OSTI)

By using the helium generated by the alpha emissions of a thermoelectric generator during space travel for cooling the thermal degradation of the thermoelectric generator can be slowed. Slowing degradation allows missions to be longer with little additional expense or payload.

Mowery, A.L. Jr.

1992-12-31T23:59:59.000Z

128

Analysis Framework for Cooperating Mobile Cable Robots Xiaobo Zhou, Chin Pei Tang and Venkat Krovi  

E-Print Network [OSTI]

of Mechanical and Aerospace Engineering, State University of New York at Buffalo, Buffalo, NY 14260 USA xzhou9 energy consumption, ease of assembly/disassembly and reconfiguration. Cooperative payload manipulation design and analysis of cooperative mobile cable robots, building upon knowledge base of multi

Krovi, Venkat

129

Automated Worm Fingerprinting Sumeet Singh, Cristian Estan, George Varghese and Stefan Savage  

E-Print Network [OSTI]

and the Internet's un- restricted communication model creates an ideal climate for infectious pathogens. Worse-relays and denial-of-service at- tacks to their payloads. Unfortunately, our current ability to defend against. In fact, the basic approach of detection, characterization, and containment has not changed significantly

Savage, Stefan

130

Optical logic gates and its application e-mail : slee@kist.re.kr  

E-Print Network [OSTI]

recognition system, label / payload separation system, gray code to BCD converter, binary counter, parity bit] [9] [8]* ETC Gray code to BCD converter Binary counter Parity bit checker Encryption system Flip . gray code to BCD converter, binary counter, parity bit checker, encryption system, Flip-flop memory

Park, Namkyoo

131

SPACE WEATHER, VOL. 9, S04006, doi:10.1029/2011SW000668, 2011 Small Space Weather Research Mission Designed Fully by Students  

E-Print Network [OSTI]

behind the collima- tor (pink) and the shielded housing. These detectors register incoming particles into a low-Earth polar orbit in June 2012 as a sec- ondary payload under NASA's Educational Launch of Nano: to relate the location, magnitude, and frequency of solar flares to the timing, duration, and energy

Li, Xinlin

132

Planetary and Space Science 55 (2007) 18451876 Huygens' entry and descent through Titan's atmosphere--Methodology  

E-Print Network [OSTI]

, Austria c Department of Electrical and Computer Engineering, University of Idaho, Moscow, ID 83844-1023, USA d ESA Research and Scientific Support Department, ESTEC, 2200 AG Noordwijk, The Netherlands e the scientific payload. This paper presents the methodology and discuss the results of the reconstruction effort

Atkinson, David H.

133

Michael J. Mosley1 Graduate Student  

E-Print Network [OSTI]

of SMA artificial muscles in large robotic systems has been very limited. The main reasons are the small) actuator that possesses impressive payload lifting capabilities are presented. This actuator consists of 48 SMA wires mechanically bundled in parallel forming one powerful muscle. It was designed to lift up

Mavroidis, Constantinos

134

Copyright 2000 by ASME1 Proceedings of DETC'00  

E-Print Network [OSTI]

, the design and control of a novel shape memory alloy (SMA) actuator that possesses impressive payload lifting in parallel forming one powerful artificial muscle. This new linear actuator can apply up to 100 lbf (445 N the research discussed in this paper is to develop a new generation of large-scale robotic systems

Mavroidis, Constantinos

135

Space Sci Rev DOI 10.1007/s11214-012-9952-7  

E-Print Network [OSTI]

/Public Outreach payload, Moon Knowledge Acquired by Middle-School Students (MoonKAM), in which middle school outstanding questions regarding the Moon's thermal evolution, and will be applicable more generally obtained by orbital remote sensing and surface samples, as well as experimental measurements of planetary

Zuber, Maria

136

SUPERBOTS ON THE LUNAR SURFACE: A HABITAT OPERATIONS AND MAINTENANCE SYSTEM (HOMS). S. J. Lawrence1  

E-Print Network [OSTI]

Center, Mountain View, CA; 4 Metrica, Houston, TX; 5 DigitalSpace, Santa Cruz, CA; 6 Lockheed Martin and payload mass while enhancing mission performance, reliability, and safety through the SuperBot system's ability to change shape and function as needed. SuperBots can work independently or in concert to perform

Shen, Wei-Min

137

The field of medicine is taking its first steps towards patient-specific care: personalized medicine. Our research is aimed at tailoring treatments to address each person's individualized needs and unique disease presentation. Specifically, we are  

E-Print Network [OSTI]

their payload in disease sites. The evolution of these nanoparticles into programmed nano robots, unique to specific organs. Avi Schroeder is an Assistant Professor of Chemical Engineering at the Technion Israel to Programmed Nano-robots Professor Avi Schroeder ETH Hnggerberg, HCI G 3, 02/04/14, 17.00 h Faculty

Sandoghdar, Vahid

138

NASA FactsNationalAeronautics and SpaceAdministration Goddard Space Flight Center  

E-Print Network [OSTI]

or sensors. Electrical power is abundant throughout the aircraft. Provision is made for standard 110/60 Hz AC, 110/ 400 Hz AC and 28VDC regulated power hookups, but unique power requirements are easily designed rack modules. Multiple instrument payloads are an economical way for cooperating scientists

139

Abstract--In this work, we develop a new parallel implementation of the k-means unsupervised clustering  

E-Print Network [OSTI]

in the context of remote sensing image processing applications. For instance, while the price of a next as a processing module onboard the remote sensing instruments, with critical issues that can negatively affect the mission payload (weight, power consumption, heating, maintenance, etc.). In turn, GPUs offer a much more

Plaza, Antonio J.

140

Kring/Space Sciences 2006 Lunar Exploration Initiative  

E-Print Network [OSTI]

Exploration Initiative Lunokhod 2 Powered by batteries that were recharged by a solar panel on lid of payload occasionally to recharge battery with solar panel ­ Hibernated during lunar night, remaining warm bay & a Polonium-210 radiogenic heat source Carried 3 TV cameras, one of which was high on rover

Rathbun, Julie A.

Note: This page contains sample records for the topic "ur3 ur4 payload" from the National Library of EnergyBeta (NLEBeta).
While these samples are representative of the content of NLEBeta,
they are not comprehensive nor are they the most current set.
We encourage you to perform a real-time search of NLEBeta
to obtain the most current and comprehensive results.


141

Robotics and Autonomous Systems 62 (2014) 15811596 Contents lists available at ScienceDirect  

E-Print Network [OSTI]

Moving Horizon Estimation with application to localization of Autonomous Underwater Vehicles Sen Wang of Essex, UK h i g h l i g h t s · A novel localization method for Autonomous Underwater Vehicle t Localizing small Autonomous Underwater Vehicles (AUVs) that have limited payload and perception ca- pability

Hu, Huosheng

142

On the Design of Shape Memory Alloy Wire Bundle Actuators Kathryn J. De Laurentis1  

E-Print Network [OSTI]

the use of compact, smart material based actuators to power the robot joints [1]. Smart materials alter memory alloys and polymers are examples of smart materials. The interest in these types of actuators one of the highest payload to weight ratios among "smart material" based actua- tors. Therefore, SMAs

Mavroidis, Constantinos

143

56113.Transport and integration 13.1 Transport  

E-Print Network [OSTI]

be classified according to the hazard involved: · Mirror segments. The size of each segment allows transport by laser beams. This grid defines the X-Y-Z location of each node of the structure. Each node can several light cranes with a maximum payload of 3 tons. thereby allowing for redundancy. · The structural

Liske, Jochen

144

CH-TRU Waste Content Codes (CH-TRUCON)  

SciTech Connect (OSTI)

The CH-TRU Waste Content Codes (CH-TRUCON) document describes the inventory of the U.S. Department of Energy (DOE) CH-TRU waste within the transportation parameters specified by the Contact-Handled Transuranic Waste Authorized Methods for Payload Control (CH-TRAMPAC). The CH-TRAMPAC defines the allowable payload for the Transuranic Package Transporter-II (TRUPACT-II) and HalfPACT packagings. This document is a catalog of TRUPACT-II and HalfPACT authorized contents and a description of the methods utilized to demonstrate compliance with the CH-TRAMPAC. A summary of currently approved content codes by site is presented in Table 1. The CH-TRAMPAC describes "shipping categories" that are assigned to each payload container. Multiple shipping categories may be assigned to a single content code. A summary of approved content codes and corresponding shipping categories is provided in Table 2, which consists of Tables 2A, 2B, and 2C. Table 2A provides a summary of approved content codes and corresponding shipping categories for the "General Case," which reflects the assumption of a 60-day shipping period as described in the CH-TRAMPAC and Appendix 3.4 of the CH-TRU Payload Appendices. For shipments to be completed within an approximately 1,000-mile radius, a shorter shipping period of 20 days is applicable as described in the CH-TRAMPAC and Appendix 3.5 of the CH-TRU Payload Appendices. For shipments to WIPP from Los Alamos National Laboratory (LANL), Nevada Test Site, and Rocky Flats Environmental Technology Site, a 20-day shipping period is applicable. Table 2B provides a summary of approved content codes and corresponding shipping categories for "Close-Proximity Shipments" (20-day shipping period). For shipments implementing the controls specified in the CH-TRAMPAC and Appendix 3.6 of the CH-TRU Payload Appendices, a 10-day shipping period is applicable. Table 2C provides a summary of approved content codes and corresponding shipping categories for "Controlled Shipments" (10-day shipping period).

Washington TRU Solutions LLC

2004-10-01T23:59:59.000Z

145

CH-TRU Waste Content Codes (CH-TRUCON)  

SciTech Connect (OSTI)

The CH-TRU Waste Content Codes (CH-TRUCON) document describes the inventory of the U.S. Department of Energy (DOE) CH-TRU waste within the transportation parameters specified by the Contact-Handled Transuranic Waste Authorized Methods for Payload Control (CH-TRAMPAC). The CH-TRAMPAC defines the allowable payload for the Transuranic Package Transporter-II (TRUPACT-II) and HalfPACT packagings. This document is a catalog of TRUPACT-II and HalfPACT authorized contents and a description of the methods utilized to demonstrate compliance with the CH-TRAMPAC. A summary of currently approved content codes by site is presented in Table 1. The CH-TRAMPAC describes "shipping categories" that are assigned to each payload container. Multiple shipping categories may be assigned to a single content code. A summary of approved content codes and corresponding shipping categories is provided in Table 2, which consists of Tables 2A, 2B, and 2C. Table 2A provides a summary of approved content codes and corresponding shipping categories for the "General Case," which reflects the assumption of a 60-day shipping period as described in the CH-TRAMPAC and Appendix 3.4 of the CH-TRU Payload Appendices. For shipments to be completed within an approximately 1,000-mile radius, a shorter shipping period of 20 days is applicable as described in the CH-TRAMPAC and Appendix 3.5 of the CH-TRU Payload Appendices. For shipments to WIPP from Los Alamos National Laboratory (LANL), Nevada Test Site, and Rocky Flats Environmental Technology Site, a 20-day shipping period is applicable. Table 2B provides a summary of approved content codes and corresponding shipping categories for "Close-Proximity Shipments" (20-day shipping period). For shipments implementing the controls specified in the CH-TRAMPAC and Appendix 3.6 of the CH-TRU Payload Appendices, a 10-day shipping period is applicable. Table 2C provides a summary of approved content codes and corresponding shipping categories for "Controlled Shipments" (10-day shipping period).

Washington TRU Solutions LLC

2005-03-15T23:59:59.000Z

146

CH-TRU Waste Content Codes (CH-TRUCON)  

SciTech Connect (OSTI)

The CH-TRU Waste Content Codes (CH-TRUCON) document describes the inventory of the U.S. Department of Energy (DOE) CH-TRU waste within the transportation parameters specified by the Contact-Handled Transuranic Waste Authorized Methods for Payload Control (CH-TRAMPAC). The CH-TRAMPAC defines the allowable payload for the Transuranic Package Transporter-II (TRUPACT-II) and HalfPACT packagings. This document is a catalog of TRUPACT-II and HalfPACT authorized contents and a description of the methods utilized to demonstrate compliance with the CH-TRAMPAC. A summary of currently approved content codes by site is presented in Table 1. The CH-TRAMPAC describes "shipping categories" that are assigned to each payload container. Multiple shipping categories may be assigned to a single content code. A summary of approved content codes and corresponding shipping categories is provided in Table 2, which consists of Tables 2A, 2B, and 2C. Table 2A provides a summary of approved content codes and corresponding shipping categories for the "General Case," which reflects the assumption of a 60-day shipping period as described in the CH-TRAMPAC and Appendix 3.4 of the CH-TRU Payload Appendices. For shipments to be completed within an approximately 1,000-mile radius, a shorter shipping period of 20 days is applicable as described in the CH-TRAMPAC and Appendix 3.5 of the CH-TRU Payload Appendices. For shipments to WIPP from Los Alamos National Laboratory (LANL), Nevada Test Site, and Rocky Flats Environmental Technology Site, a 20-day shipping period is applicable. Table 2B provides a summary of approved content codes and corresponding shipping categories for "Close-Proximity Shipments" (20-day shipping period). For shipments implementing the controls specified in the CH-TRAMPAC and Appendix 3.6 of the CH-TRU Payload Appendices, a 10-day shipping period is applicable. Table 2C provides a summary of approved content codes and corresponding shipping categories for "Controlled Shipments" (10-day shipping period).

Washington TRU Solutions LLC

2005-01-30T23:59:59.000Z

147

CH-TRU Waste Content Codes (CH-TRUCON)  

SciTech Connect (OSTI)

The CH-TRU Waste Content Codes (CH-TRUCON) document describes the inventory of the U.S. Department of Energy (DOE) CH-TRU waste within the transportation parameters specified by the Contact-Handled Transuranic Waste Authorized Methods for Payload Control (CH-TRAMPAC). The CH-TRAMPAC defines the allowable payload for the Transuranic Package Transporter-II (TRUPACT-II) and HalfPACT packagings. This document is a catalog of TRUPACT-II and HalfPACT authorized contents and a description of the methods utilized to demonstrate compliance with the CH-TRAMPAC. A summary of currently approved content codes by site is presented in Table 1. The CH-TRAMPAC describes "shipping categories" that are assigned to each payload container. Multiple shipping categories may be assigned to a single content code. A summary of approved content codes and corresponding shipping categories is provided in Table 2, which consists of Tables 2A, 2B, and 2C. Table 2A provides a summary of approved content codes and corresponding shipping categories for the "General Case," which reflects the assumption of a 60-day shipping period as described in the CH-TRAMPAC and Appendix 3.4 of the CH-TRU Payload Appendices. For shipments to be completed within an approximately 1,000-mile radius, a shorter shipping period of 20 days is applicable as described in the CH-TRAMPAC and Appendix 3.5 of the CH-TRU Payload Appendices. For shipments to WIPP from Los Alamos National Laboratory (LANL), Nevada Test Site, and Rocky Flats Environmental Technology Site, a 20-day shipping period is applicable. Table 2B provides a summary of approved content codes and corresponding shipping categories for "Close-Proximity Shipments" (20-day shipping period). For shipments implementing the controls specified in the CH-TRAMPAC and Appendix 3.6 of the CH-TRU Payload Appendices, a 10-day shipping period is applicable. Table 2C provides a summary of approved content codesand corresponding shipping categories for "Controlled Shipments" (10-day shipping period).

Washington TRU Solutions LLC

2005-01-15T23:59:59.000Z

148

CH-TRU Waste Content Codes (CH-TRUCON)  

SciTech Connect (OSTI)

The CH-TRU Waste Content Codes (CH-TRUCON) document describes the inventory of the U.S. Department of Energy (DOE) CH-TRU waste within the transportation parameters specified by the Contact-Handled Transuranic Waste Authorized Methods for Payload Control (CH-TRAMPAC). The CH-TRAMPAC defines the allowable payload for the Transuranic Package Transporter-II (TRUPACT-II) and HalfPACT packagings. This document is a catalog of TRUPACT-II and HalfPACT authorized contents and a description of the methods utilized to demonstrate compliance with the CH-TRAMPAC. A summary of currently approved content codes by site is presented in Table 1. The CH-TRAMPAC describes "shipping categories" that are assigned to each payload container. Multiple shipping categories may be assigned to a single content code. A summary of approved content codes and corresponding shipping categories is provided in Table 2, which consists of Tables 2A, 2B, and 2C. Table 2A provides a summary of approved content codes and corresponding shipping categories for the "General Case," which reflects the assumption of a 60-day shipping period as described in the CH-TRAMPAC and Appendix 3.4 of the CH-TRU Payload Appendices. For shipments to be completed within an approximately 1,000-mile radius, a shorter shipping period of 20 days is applicable as described in the CH-TRAMPAC and Appendix 3.5 of the CH-TRU Payload Appendices. For shipments to WIPP from Los Alamos National Laboratory (LANL), Nevada Test Site, and Rocky Flats Environmental Technology Site, a 20-day shipping period is applicable. Table 2B provides a summary of approved content codes and corresponding shipping categories for "Close-Proximity Shipments" (20-day shipping period). For shipments implementing the controls specified in the CH-TRAMPAC and Appendix 3.6 of the CH-TRU Payload Appendices, a 10-day shipping period is applicable. Table 2C provides a summary of approved content codes and corresponding shipping categories for "Controlled Shipments" (10-day shipping period).

Washington TRU Solutions LLC

2005-11-20T23:59:59.000Z

149

CH-TRU Waste Content Codes (CH-TRUCON)  

SciTech Connect (OSTI)

The CH-TRU Waste Content Codes (CH-TRUCON) document describes the inventory of the U.S. Department of Energy (DOE) CH-TRU waste within the transportation parameters specified by the Contact-Handled Transuranic Waste Authorized Methods for Payload Control (CH-TRAMPAC). The CH-TRAMPAC defines the allowable payload for the Transuranic Package Transporter-II (TRUPACT-II) and HalfPACT packagings. This document is a catalog of TRUPACT-II and HalfPACT authorized contents and a description of the methods utilized to demonstrate compliance with the CH-TRAMPAC. A summary of currently approved content codes by site is presented in Table 1. The CH-TRAMPAC describes "shipping categories" that are assigned to each payload container. Multiple shipping categories may be assigned to a single content code. A summary of approved content codes and corresponding shipping categories is provided in Table 2, which consists of Tables 2A, 2B, and 2C. Table 2A provides a summary of approved content codes and corresponding shipping categories for the "General Case," which reflects the assumption of a 60-day shipping period as described in the CH-TRAMPAC and Appendix 3.4 of the CH-TRU Payload Appendices. For shipments to be completed within an approximately 1,000-mile radius, a shorter shipping period of 20 days is applicable as described in the CH-TRAMPAC and Appendix 3.5 of the CH-TRU Payload Appendices. For shipments to WIPP from Los Alamos National Laboratory (LANL), Nevada Test Site, and Rocky Flats Environmental Technology Site, a 20-day shipping period is applicable. Table 2B provides a summary of approved content codes and corresponding shipping categories for "Close-Proximity Shipments" (20-day shipping period). For shipments implementing the controls specified in the CH-TRAMPAC and Appendix 3.6 of the CH-TRU Payload Appendices, a 10-day shipping period is applicable. Table 2C provides a summary of approved content codes and corresponding shipping categories for "Controlled Shipments" (10-day shipping period).

Washington TRU Solutions LLC

2006-08-15T23:59:59.000Z

150

CH-TRU Waste Content Codes (CH-TRUCON)  

SciTech Connect (OSTI)

The CH-TRU Waste Content Codes (CH-TRUCON) document describes the inventory of the U.S. Department of Energy (DOE) CH-TRU waste within the transportation parameters specified by the Contact-Handled Transuranic Waste Authorized Methods for Payload Control (CH-TRAMPAC). The CH-TRAMPAC defines the allowable payload for the Transuranic Package Transporter-II (TRUPACT-II) and HalfPACT packagings. This document is a catalog of TRUPACT-II and HalfPACT authorized contents and a description of the methods utilized to demonstrate compliance with the CH-TRAMPAC. A summary of currently approved content codes by site is presented in Table 1. The CH-TRAMPAC describes "shipping categories" that are assigned to each payload container. Multiple shipping categories may be assigned to a single content code. A summary of approved content codes and corresponding shipping categories is provided in Table 2, which consists of Tables 2A, 2B, and 2C. Table 2A provides a summary of approved content codes and corresponding shipping categories for the "General Case," which reflects the assumption of a 60-day shipping period as described in the CH-TRAMPAC and Appendix 3.4 of the CH-TRU Payload Appendices. For shipments to be completed within an approximately 1,000-mile radius, a shorter shipping period of 20 days is applicable as described in the CH-TRAMPAC and Appendix 3.5 of the CH-TRU Payload Appendices. For shipments to WIPP from Los Alamos National Laboratory (LANL), Nevada Test Site, and Rocky Flats Environmental Technology Site, a 20-day shipping period is applicable. Table 2B provides a summary of approved content codes and corresponding shipping categories for "Close-Proximity Shipments" (20-day shipping period). For shipments implementing the controls specified in the CH-TRAMPAC and Appendix 3.6 of the CH-TRU Payload Appendices, a 10-day shipping period is applicable. Table 2C provides a summary of approved content codes and corresponding shipping categories for "Controlled Shipments" (10-day shipping period).

Washington TRU Solutions LLC

2006-01-18T23:59:59.000Z

151

CH-TRU Waste Content Codes  

SciTech Connect (OSTI)

The CH-TRU Waste Content Codes (CH-TRUCON) document describes the inventory of the U.S. Department of Energy (DOE) CH-TRU waste within the transportation parameters specified by the Contact-Handled Transuranic Waste Authorized Methods for Payload Control (CH-TRAMPAC). The CH-TRAMPAC defines the allowable payload for the Transuranic Package Transporter-II (TRUPACT-II) and HalfPACT packagings. This document is a catalog of TRUPACT-II and HalfPACT authorized contents and a description of the methods utilized to demonstrate compliance with the CH-TRAMPAC. A summary of currently approved content codes by site is presented in Table 1. The CH-TRAMPAC describes "shipping categories" that are assigned to each payload container. Multiple shipping categories may be assigned to a single content code. A summary of approved content codes and corresponding shipping categories is provided in Table 2, which consists of Tables 2A, 2B, and 2C. Table 2A provides a summary of approved content codes and corresponding shipping categories for the "General Case," which reflects the assumption of a 60-day shipping period as described in the CH-TRAMPAC and Appendix 3.4 of the CH-TRU Payload Appendices. For shipments to be completed within an approximately 1,000-mile radius, a shorter shipping period of 20 days is applicable as described in the CH-TRAMPAC and Appendix 3.5 of the CH-TRU Payload Appendices. For shipments to WIPP from Los Alamos National Laboratory (LANL), Nevada Test Site, and Rocky Flats Environmental Technology Site, a 20-day shipping period is applicable. Table 2B provides a summary of approved content codes and corresponding shipping categories for "Close-Proximity Shipments" (20-day shipping period). For shipments implementing the controls specified in the CH-TRAMPAC and Appendix 3.6 of the CH-TRU Payload Appendices, a 10-day shipping period is applicable. Table 2C provides a summary of approved content codes and corresponding shipping categories for "Controlled Shipments" (10-day shipping period).

Washington TRU Solutions LLC

2008-01-16T23:59:59.000Z

152

CH-TRU Content Codes (CH-TRUCON)  

SciTech Connect (OSTI)

The CH-TRU Waste Content Codes (CH-TRUCON) document describes the inventory of the U.S. Department of Energy (DOE) CH-TRU waste within the transportation parameters specified by the Contact-Handled Transuranic Waste Authorized Methods for Payload Control (CH-TRAMPAC). The CH-TRAMPAC defines the allowable payload for the Transuranic Package Transporter-II (TRUPACT-II) and HalfPACT packagings. This document is a catalog of TRUPACT-II and HalfPACT authorized contents and a description of the methods utilized to demonstrate compliance with the CH-TRAMPAC. A summary of currently approved content codes by site is presented in Table 1. The CH-TRAMPAC describes "shipping categories" that are assigned to each payload container. Multiple shipping categories may be assigned to a single content code. A summary of approved content codes and corresponding shipping categories is provided in Table 2, which consists of Tables 2A, 2B, and 2C. Table 2A provides a summary of approved content codes and corresponding shipping categories for the "General Case," which reflects the assumption of a 60-day shipping period as described in the CH-TRAMPAC and Appendix 3.4 of the CH-TRU Payload Appendices. For shipments to be completed within an approximately 1,000-mile radius, a shorter shipping period of 20 days is applicable as described in the CH-TRAMPAC and Appendix 3.5 of the CH-TRU Payload Appendices. For shipments to WIPP from Los Alamos National Laboratory (LANL), Nevada Test Site, and Rocky Flats Environmental Technology Site, a 20-day shipping period is applicable. Table 2B provides a summary of approved content codes and corresponding shipping categories for "Close-Proximity Shipments" (20-day shipping period). For shipments implementing the controls specified in the CH-TRAMPAC and Appendix 3.6 of the CH-TRU Payload Appendices, a 10-day shipping period is applicable. Table 2C provides a summary of approved content codes and corresponding shipping categories for "Controlled Shipments" (10-day shipping period).

Washington TRU Solutions LLC

2005-10-15T23:59:59.000Z

153

CH-TRU Waste Content Codes (CH-TRUCON)  

SciTech Connect (OSTI)

The CH-TRU Waste Content Codes (CH-TRUCON) document describes the inventory of the U.S. Department of Energy (DOE) CH-TRU waste within the transportation parameters specified by the Contact-Handled Transuranic Waste Authorized Methods for Payload Control (CH-TRAMPAC). The CH-TRAMPAC defines the allowable payload for the Transuranic Package Transporter-II (TRUPACT-II) and HalfPACT packagings. This document is a catalog of TRUPACT-II and HalfPACT authorized contents and a description of the methods utilized to demonstrate compliance with the CH-TRAMPAC. A summary of currently approved content codes by site is presented in Table 1. The CH-TRAMPAC describes "shipping categories" that are assigned to each payload container. Multiple shipping categories may be assigned to a single content code. A summary of approved content codes and corresponding shipping categories is provided in Table 2, which consists of Tables 2A, 2B, and 2C. Table 2A provides a summary of approved content codes and corresponding shipping categories for the "General Case," which reflects the assumption of a 60-day shipping period as described in the CH-TRAMPAC and Appendix 3.4 of the CH-TRU Payload Appendices. For shipments to be completed within an approximately 1,000-mile radius, a shorter shipping period of 20 days is applicable as described in the CH-TRAMPAC and Appendix 3.5 of the CH-TRU Payload Appendices. For shipments to WIPP from Los Alamos National Laboratory (LANL), Nevada Test Site, and Rocky Flats Environmental Technology Site, a 20-day shipping period is applicable. Table 2B provides a summary of approved content codes and corresponding shipping categories for "Close-Proximity Shipments" (20-day shipping period). For shipments implementing the controls specified in the CH-TRAMPAC and Appendix 3.6 of the CH-TRU Payload Appendices, a 10-day shipping period is applicable. Table 2C provides a summary of approved content codes and corresponding shipping categories for "Controlled Shipments" (10-day shipping period).

Washington TRU Solutions LLC

2005-05-01T23:59:59.000Z

154

CH-TRU Waste Content Codes (CH-TRUCON)  

SciTech Connect (OSTI)

The CH-TRU Waste Content Codes (CH-TRUCON) document describes the inventory of the U.S. Department of Energy (DOE) CH-TRU waste within the transportation parameters specified by the Contact-Handled Transuranic Waste Authorized Methods for Payload Control (CH-TRAMPAC). The CH-TRAMPAC defines the allowable payload for the Transuranic Package Transporter-II (TRUPACT-II) and HalfPACT packagings. This document is a catalog of TRUPACT-II and HalfPACT authorized contents and a description of the methods utilized to demonstrate compliance with the CH-TRAMPAC. A summary of currently approved content codes by site is presented in Table 1. The CH-TRAMPAC describes "shipping categories" that are assigned to each payload container. Multiple shipping categories may be assigned to a single content code. A summary of approved content codes and corresponding shipping categories is provided in Table 2, which consists of Tables 2A, 2B, and 2C. Table 2A provides a summary of approved content codes and corresponding shipping categories for the "General Case," which reflects the assumption of a 60-day shipping period as described in the CH-TRAMPAC and Appendix 3.4 of the CH-TRU Payload Appendices. For shipments to be completed within an approximately 1,000-mile radius, a shorter shipping period of 20 days is applicable as described in the CH-TRAMPAC and Appendix 3.5 of the CH-TRU Payload Appendices. For shipments to WIPP from Los Alamos National Laboratory (LANL), Nevada Test Site, and Rocky Flats Environmental Technology Site, a 20-day shipping period is applicable. Table 2B provides a summary of approved content codes and corresponding shipping categories for "Close-Proximity Shipments" (20-day shipping period). For shipments implementing the controls specified in the CH-TRAMPAC and Appendix 3.6 of the CH-TRU Payload Appendices, a 10-day shipping period is applicable. Table 2C provides a summary of approved content codes and corresponding shipping categories for "Controlled Shipments" (10-day shipping period).

Washington TRU Solutions LLC

2007-09-20T23:59:59.000Z

155

CH-TRU Waste Content Codes (CH-TRUCON)  

SciTech Connect (OSTI)

The CH-TRU Waste Content Codes (CH-TRUCON) document describes the inventory of the U.S. Department of Energy (DOE) CH-TRU waste within the transportation parameters specified by the Contact-Handled Transuranic Waste Authorized Methods for Payload Control (CH-TRAMPAC). The CH-TRAMPAC defines the allowable payload for the Transuranic Package Transporter-II (TRUPACT-II) and HalfPACT packagings. This document is a catalog of TRUPACT-II and HalfPACT authorized contents and a description of the methods utilized to demonstrate compliance with the CH-TRAMPAC. A summary of currently approved content codes by site is presented in Table 1. The CH-TRAMPAC describes "shipping categories" that are assigned to each payload container. Multiple shipping categories may be assigned to a single content code. A summary of approved content codes and corresponding shipping categories is provided in Table 2, which consists of Tables 2A, 2B, and 2C. Table 2A provides a summary of approved content codes and corresponding shipping categories for the "General Case," which reflects the assumption of a 60-day shipping period as described in the CH-TRAMPAC and Appendix 3.4 of the CH-TRU Payload Appendices. For shipments to be completed within an approximately 1,000-mile radius, a shorter shipping period of 20 days is applicable as described in the CH-TRAMPAC and Appendix 3.5 of the CH-TRU Payload Appendices. For shipments to WIPP from Los Alamos National Laboratory (LANL), Nevada Test Site, and Rocky Flats Environmental Technology Site, a 20-day shipping period is applicable. Table 2B provides a summary of approved content codes and corresponding shipping categories for "Close-Proximity Shipments" (20-day shipping period). For shipments implementing the controls specified in the CH-TRAMPAC and Appendix 3.6 of the CH-TRU Payload Appendices, a 10-day shipping period is applicable. Table 2C provides a summary of approved content codes and corresponding shipping categories for "Controlled Shipments" (10-day shipping period).

Washington TRU Solutions LLC

2005-12-15T23:59:59.000Z

156

CH-TRU Waste Content Codes (CH-TRUCON)  

SciTech Connect (OSTI)

The CH-TRU Waste Content Codes (CH-TRUCON) document describes the inventory of the U.S. Department of Energy (DOE) CH-TRU waste within the transportation parameters specified by the Contact-Handled Transuranic Waste Authorized Methods for Payload Control (CH-TRAMPAC). The CH-TRAMPAC defines the allowable payload for the Transuranic Package Transporter-II (TRUPACT-II) and HalfPACT packagings. This document is a catalog of TRUPACT-II and HalfPACT authorized contents and a description of the methods utilized to demonstrate compliance with the CH-TRAMPAC. A summary of currently approved content codes by site is presented in Table 1. The CH-TRAMPAC describes "shipping categories" that are assigned to each payload container. Multiple shipping categories may be assigned to a single content code. A summary of approved content codes and corresponding shipping categories is provided in Table 2, which consists of Tables 2A, 2B, and 2C. Table 2A provides a summary of approved content codes and corresponding shipping categories for the "General Case," which reflects the assumption of a 60-day shipping period as described in the CH-TRAMPAC and Appendix 3.4 of the CH-TRU Payload Appendices. For shipments to be completed within an approximately 1,000-mile radius, a shorter shipping period of 20 days is applicable as described in the CH-TRAMPAC and Appendix 3.5 of the CH-TRU Payload Appendices. For shipments to WIPP from Los Alamos National Laboratory (LANL), Nevada Test Site, and Rocky Flats Environmental Technology Site, a 20-day shipping period is applicable. Table 2B provides a summary of approved content codes and corresponding shipping categories for "Close-Proximity Shipments" (20-day shipping period). For shipments implementing the controls specified in the CH-TRAMPAC and Appendix 3.6 of the CH-TRU Payload Appendices, a 10-day shipping period is applicable. Table 2C provides a summary of approved content codes and corresponding shipping categories for "Controlled Shipments" (10-day shipping period).

Washington TRU Solutions LLC

2006-09-15T23:59:59.000Z

157

CH-TRU Waste Content Codes (CH-TRUCON)  

SciTech Connect (OSTI)

The CH-TRU Waste Content Codes (CH-TRUCON) document describes the inventory of the U.S. Department of Energy (DOE) CH-TRU waste within the transportation parameters specified by the Contact-Handled Transuranic Waste Authorized Methods for Payload Control (CH-TRAMPAC). The CH-TRAMPAC defines the allowable payload for the Transuranic Package Transporter-II (TRUPACT-II) and HalfPACT packagings. This document is a catalog of TRUPACT-II and HalfPACT authorized contents and a description of the methods utilized to demonstrate compliance with the CH-TRAMPAC. A summary of currently approved content codes by site is presented in Table 1. The CH-TRAMPAC describes "shipping categories" that are assigned to each payload container. Multiple shipping categories may be assigned to a single content code. A summary of approved content codes and corresponding shipping categories is provided in Table 2, which consists of Tables 2A, 2B, and 2C. Table 2A provides a summary of approved content codes and corresponding shipping categories for the "General Case," which reflects the assumption of a 60-day shipping period as described in the CH-TRAMPAC and Appendix 3.4 of the CH-TRU Payload Appendices. For shipments to be completed within an approximately 1,000-mile radius, a shorter shipping period of 20 days is applicable as described in the CH-TRAMPAC and Appendix 3.5 of the CH-TRU Payload Appendices. For shipments to WIPP from Los Alamos National Laboratory (LANL), Nevada Test Site, and Rocky Flats Environmental Technology Site, a 20-day shipping period is applicable. Table 2B provides a summary of approved content codes and corresponding shipping categories for "Close-Proximity Shipments" (20-day shipping period). For shipments implementing the controls specified in the CH-TRAMPAC and Appendix 3.6 of the CH-TRU Payload Appendices, a 10-day shipping period is applicable. Table 2C provides a summary of approved content codes and corresponding shipping categories for "Controlled Shipments" (10-day shipping period).

Washington TRU Solutions LLC

2005-06-20T23:59:59.000Z

158

CH-TRU Waste Content Codes (CH-TRUCON)  

SciTech Connect (OSTI)

The CH-TRU Waste Content Codes (CH-TRUCON) document describes the inventory of the U.S. Department of Energy (DOE) CH-TRU waste within the transportation parameters specified by the Contact-Handled Transuranic Waste Authorized Methods for Payload Control (CH-TRAMPAC). The CH-TRAMPAC defines the allowable payload for the Transuranic Package Transporter-II (TRUPACT-II) and HalfPACT packagings. This document is a catalog of TRUPACT-II and HalfPACT authorized contents and a description of the methods utilized to demonstrate compliance with the CH-TRAMPAC. A summary of currently approved content codes by site is presented in Table 1. The CH-TRAMPAC describes "shipping categories" that are assigned to each payload container. Multiple shipping categories may be assigned to a single content code. A summary of approved content codes and corresponding shipping categories is provided in Table 2, which consists of Tables 2A, 2B, and 2C. Table 2A provides a summary of approved content codes and corresponding shipping categories for the "General Case," which reflects the assumption of a 60-day shipping period as described in the CH-TRAMPAC and Appendix 3.4 of the CH-TRU Payload Appendices. For shipments to be completed within an approximately 1,000-mile radius, a shorter shipping period of 20 days is applicable as described in the CH-TRAMPAC and Appendix 3.5 of the CH-TRU Payload Appendices. For shipments to WIPP from Los Alamos National Laboratory (LANL), Nevada Test Site, and Rocky Flats Environmental Technology Site, a 20-day shipping period is applicable. Table 2B provides a summary of approved content codes and corresponding shipping categories for "Close-Proximity Shipments" (20-day shipping period). For shipments implementing the controls specified in the CH-TRAMPAC and Appendix 3.6 of the CH-TRU Payload Appendices, a 10-day shipping period is applicable. Table 2C provides a summary of approved content codes and corresponding shipping categories for "Controlled Shipments" (10-day shipping period).

Washington TRU Solutions LLC

2006-06-20T23:59:59.000Z

159

CH-TRU Waste Content Codes (CH-TRUCON)  

SciTech Connect (OSTI)

The CH-TRU Waste Content Codes (CH-TRUCON) document describes the inventory of the U.S. Department of Energy (DOE) CH-TRU waste within the transportation parameters specified by the Contact-Handled Transuranic Waste Authorized Methods for Payload Control (CH-TRAMPAC). The CH-TRAMPAC defines the allowable payload for the Transuranic Package Transporter-II (TRUPACT-II) and HalfPACT packagings. This document is a catalog of TRUPACT-II and HalfPACT authorized contents and a description of the methods utilized to demonstrate compliance with the CH-TRAMPAC. A summary of currently approved content codes by site is presented in Table 1. The CH-TRAMPAC describes "shipping categories" that are assigned to each payload container. Multiple shipping categories may be assigned to a single content code. A summary of approved content codes and corresponding shipping categories is provided in Table 2, which consists of Tables 2A, 2B, and 2C. Table 2A provides a summary of approved content codes and corresponding shipping categories for the "General Case," which reflects the assumption of a 60-day shipping period as described in the CH-TRAMPAC and Appendix 3.4 of the CH-TRU Payload Appendices. For shipments to be completed within an approximately 1,000-mile radius, a shorter shipping period of 20 days is applicable as described in the CH-TRAMPAC and Appendix 3.5 of the CH-TRU Payload Appendices. For shipments to WIPP from Los Alamos National Laboratory (LANL), Nevada Test Site, and Rocky Flats Environmental Technology Site, a 20-day shipping period is applicable. Table 2B provides a summary of approved content codes and corresponding shipping categories for "Close-Proximity Shipments" (20-day shipping period). For shipments implementing the controls specified in the CH-TRAMPAC and Appendix 3.6 of the CH-TRU Payload Appendices, a 10-day shipping period is applicable. Table 2C provides a summary of approved content codes and corresponding shipping categories for "Controlled Shipments" (10-day shipping period).

Washington TRU Solutions LLC

2007-06-15T23:59:59.000Z

160

CH-TRU Waste Content Codes (CH-TRUCON)  

SciTech Connect (OSTI)

The CH-TRU Waste Content Codes (CH-TRUCON) document describes the inventory of the U.S. Department of Energy (DOE) CH-TRU waste within the transportation parameters specified by the Contact-Handled Transuranic Waste Authorized Methods for Payload Control (CH-TRAMPAC). The CH-TRAMPAC defines the allowable payload for the Transuranic Package Transporter-II (TRUPACT-II) and HalfPACT packagings. This document is a catalog of TRUPACT-II and HalfPACT authorized contents and a description of the methods utilized to demonstrate compliance with the CH-TRAMPAC. A summary of currently approved content codes by site is presented in Table 1. The CH-TRAMPAC describes "shipping categories" that are assigned to each payload container. Multiple shipping categories may be assigned to a single content code. A summary of approved content codes and corresponding shipping categories is provided in Table 2, which consists of Tables 2A, 2B, and 2C. Table 2A provides a summary of approved content codes and corresponding shipping categories for the "General Case," which reflects the assumption of a 60-day shipping period as described in the CH-TRAMPAC and Appendix 3.4 of the CH-TRU Payload Appendices. For shipments to be completed within an approximately 1,000-mile radius, a shorter shipping period of 20 days is applicable as described in the CH-TRAMPAC and Appendix 3.5 of the CH-TRU Payload Appendices. For shipments to WIPP from Los Alamos National Laboratory (LANL), Nevada Test Site, and Rocky Flats Environmental Technology Site, a 20-day shipping period is applicable. Table 2B provides a summary of approved content codes and corresponding shipping categories for "Close-Proximity Shipments" (20-day shipping period). For shipments implementing the controls specified in the CH-TRAMPAC and Appendix 3.6 of the CH-TRU Payload Appendices, a 10-day shipping period is applicable. Table 2C provides a summary of approved content codes and corresponding shipping categories for "Controlled Shipments" (10-day shipping period).

Washington TRU Solutions LLC

2006-12-20T23:59:59.000Z

Note: This page contains sample records for the topic "ur3 ur4 payload" from the National Library of EnergyBeta (NLEBeta).
While these samples are representative of the content of NLEBeta,
they are not comprehensive nor are they the most current set.
We encourage you to perform a real-time search of NLEBeta
to obtain the most current and comprehensive results.


161

CH-TRU Waste Content Codes (CH-TRUCON)  

SciTech Connect (OSTI)

The CH-TRU Waste Content Codes (CH-TRUCON) document describes the inventory of the U.S. Department of Energy (DOE) CH-TRU waste within the transportation parameters specified by the Contact-Handled Transuranic Waste Authorized Methods for Payload Control (CH-TRAMPAC). The CH-TRAMPAC defines the allowable payload for the Transuranic Package Transporter-II (TRUPACT-II) and HalfPACT packagings. This document is a catalog of TRUPACT-II and HalfPACT authorized contents and a description of the methods utilized to demonstrate compliance with the CH-TRAMPAC. A summary of currently approved content codes by site is presented in Table 1. The CH-TRAMPAC describes "shipping categories" that are assigned to each payload container. Multiple shipping categories may be assigned to a single content code. A summary of approved content codes and corresponding shipping categories is provided in Table 2, which consists of Tables 2A, 2B, and 2C. Table 2A provides a summary of approved content codes and corresponding shipping categories for the "General Case," which reflects the assumption of a 60-day shipping period as described in the CH-TRAMPAC and Appendix 3.4 of the CH-TRU Payload Appendices. For shipments to be completed within an approximately 1,000-mile radius, a shorter shipping period of 20 days is applicable as described in the CH-TRAMPAC and Appendix 3.5 of the CH-TRU Payload Appendices. For shipments to WIPP from Los Alamos National Laboratory (LANL), Nevada Test Site, and Rocky Flats Environmental Technology Site, a 20-day shipping period is applicable. Table 2B provides a summary of approved content codes and corresponding shipping categories for "Close-Proximity Shipments" (20-day shipping period). For shipments implementing the controls specified in the CH-TRAMPAC and Appendix 3.6 of the CH-TRU Payload Appendices, a 10-day shipping period is applicable. Table 2C provides a summary of approved content codes and corresponding shipping categories for "Controlled Shipments" (10-day shipping period).

Washington TRU Solutions LLC

2007-08-15T23:59:59.000Z

162

CH-TRU Waste Content Codes (CH-TRUCON)  

SciTech Connect (OSTI)

The CH-TRU Waste Content Codes (CH-TRUCON) document describes the inventory of the U.S. Department of Energy (DOE) CH-TRU waste within the transportation parameters specified by the Contact-Handled Transuranic Waste Authorized Methods for Payload Control (CH-TRAMPAC). The CH-TRAMPAC defines the allowable payload for the Transuranic Package Transporter-II (TRUPACT-II) and HalfPACT packagings. This document is a catalog of TRUPACT-II and HalfPACT authorized contents and a description of the methods utilized to demonstrate compliance with the CH-TRAMPAC. A summary of currently approved content codes by site is presented in Table 1. The CH-TRAMPAC describes "shipping categories" that are assigned to each payload container. Multiple shipping categories may be assigned to a single content code. A summary of approved content codes and corresponding shipping categories is provided in Table 2, which consists of Tables 2A, 2B, and 2C. Table 2A provides a summary of approved content codes and corresponding shipping categories for the "General Case," which reflects the assumption of a 60-day shipping period as described in the CH-TRAMPAC and Appendix 3.4 of the CH-TRU Payload Appendices. For shipments to be completed within an approximately 1,000-mile radius, a shorter shipping period of 20 days is applicable as described in the CH-TRAMPAC and Appendix 3.5 of the CH-TRU Payload Appendices. For shipments to WIPP from Los Alamos National Laboratory (LANL), Nevada Test Site, and Rocky Flats Environmental Technology Site, a 20-day shipping period is applicable. Table 2B provides a summary of approved content codes and corresponding shipping categories for "Close-Proximity Shipments" (20-day shipping period). For shipments implementing the controls specified in the CH-TRAMPAC and Appendix 3.6 of the CH-TRU Payload Appendices, a 10-day shipping period is applicable. Table 2C provides a summary of approved content codes and corresponding shipping categories for "Controlled Shipments" (10-day shipping period).

Washington TRU Solutions LLC

2005-08-15T23:59:59.000Z

163

CH-TRU Waste Content Codes (CH-TRUCON)  

SciTech Connect (OSTI)

The CH-TRU Waste Content Codes (CH-TRUCON) document describes the inventory of the U.S. Department of Energy (DOE) CH-TRU waste within the transportation parameters specified by the Contact-Handled Transuranic Waste Authorized Methods for Payload Control (CH-TRAMPAC). The CH-TRAMPAC defines the allowable payload for the Transuranic Package Transporter-II (TRUPACT-II) and HalfPACT packagings. This document is a catalog of TRUPACT-II and HalfPACT authorized contents and a description of the methods utilized to demonstrate compliance with the CH-TRAMPAC. A summary of currently approved content codes by site is presented in Table 1. The CH-TRAMPAC describes "shipping categories" that are assigned to each payload container. Multiple shipping categories may be assigned to a single content code. A summary of approved content codes and corresponding shipping categories is provided in Table 2, which consists of Tables 2A, 2B, and 2C. Table 2A provides a summary of approved content codes and corresponding shipping categories for the "General Case," which reflects the assumption of a 60-day shipping period as described in the CH-TRAMPAC and Appendix 3.4 of the CH-TRU Payload Appendices. For shipments to be completed within an approximately 1,000-mile radius, a shorter shipping period of 20 days is applicable as described in the CH-TRAMPAC and Appendix 3.5 of the CH-TRU Payload Appendices. For shipments to WIPP from Los Alamos National Laboratory (LANL), Nevada Test Site, and Rocky Flats Environmental Technology Site, a 20-day shipping period is applicable. Table 2B provides a summary of approved content codes and corresponding shipping categories for "Close-Proximity Shipments" (20-day shipping period). For shipments implementing the controls specified in the CH-TRAMPAC and Appendix 3.6 of the CH-TRU Payload Appendices, a 10-day shipping period is applicable. Table 2C provides a summary of approved content codes and corresponding shipping categories for "Controlled Shipments" (10-day shipping period).

Washington TRU Solutions LLC

2007-02-15T23:59:59.000Z

164

CH-TRU Waste Content Codes (CH TRUCON)  

SciTech Connect (OSTI)

The CH-TRU Waste Content Codes (CH-TRUCON) document describes the inventory of the U.S. Department of Energy (DOE) CH-TRU waste within the transportation parameters specified by the Contact-Handled Transuranic Waste Authorized Methods for Payload Control (CH-TRAMPAC). The CH-TRAMPAC defines the allowable payload for the Transuranic Package Transporter-II (TRUPACT-II) and HalfPACT packagings. This document is a catalog of TRUPACT-II and HalfPACT authorized contents and a description of the methods utilized to demonstrate compliance with the CH-TRAMPAC. A summary of currently approved content codes by site is presented in Table 1. The CH-TRAMPAC describes "shipping categories" that are assigned to each payload container. Multiple shipping categories may be assigned to a single content code. A summary of approved content codes and corresponding shipping categories is provided in Table 2, which consists of Tables 2A, 2B, and 2C. Table 2A provides a summary of approved content codes and corresponding shipping categories for the "General Case," which reflects the assumption of a 60-day shipping period as described in the CH-TRAMPAC and Appendix 3.4 of the CH-TRU Payload Appendices. For shipments to be completed within an approximately 1,000-mile radius, a shorter shipping period of 20 days is applicable as described in the CH-TRAMPAC and Appendix 3.5 of the CH-TRU Payload Appendices. For shipments to WIPP from Los Alamos National Laboratory (LANL), Nevada Test Site, and Rocky Flats Environmental Technology Site, a 20-day shipping period is applicable. Table 2B provides a summary of approved content codes and corresponding shipping categories for "Close-Proximity Shipments" (20-day shipping period). For shipments implementing the controls specified in the CH-TRAMPAC and Appendix 3.6 of the CH-TRU Payload Appendices, a 10-day shipping period is applicable. Table 2C provides a summary of approved content codes and corresponding shipping categories for "Controlled Shipments" (10-day shipping period).

Washington TRU Solutions LLC

2004-12-01T23:59:59.000Z

165

Design and construction of a carbon fiber gondola for the SPIDER balloon-borne telescope  

E-Print Network [OSTI]

We introduce the light-weight carbon fiber and aluminum gondola designed for the SPIDER balloon-borne telescope. SPIDER is designed to measure the polarization of the Cosmic Microwave Background radiation with unprecedented sensitivity and control of systematics in search of the imprint of inflation: a period of exponential expansion in the early Universe. The requirements of this balloon-borne instrument put tight constrains on the mass budget of the payload. The SPIDER gondola is designed to house the experiment and guarantee its operational and structural integrity during its balloon-borne flight, while using less than 10% of the total mass of the payload. We present a construction method for the gondola based on carbon fiber reinforced polymer tubes with aluminum inserts and aluminum multi-tube joints. We describe the validation of the model through Finite Element Analysis and mechanical tests.

Soler, J D; Amiri, M; Benton, S J; Bock, J J; Bond, J R; Bryan, S A; Chiang, C; Contaldi, C C; Crill, B P; Dor, O P; Farhang, M; Filippini, J P; Fissel, L M; Fraisse, A A; Gambrel, A E; Gandilo, N N; Golwala, S; Gudmundsson, J E; Halpern, M; Hasselfield, M; Hilton, G C; Holmes, W A; Hristov, V V; Irwin, K D; Jones, W C; Kermish, Z D; Kuo, C L; MacTavish, C J; Mason, P V; Megerian, K G; Moncelsi, L; Nagy, J M; Netterfield, C B; O'Brient, R; Rahlin, A S; Reintsema, C D; Ruhl, J E; Runyan, M C; Shariff, J A; Trangsrud, A; Tucker, C; Tucker, R S; Turner, A D; Weber, A C; Wiebe, D V; Young, E Y

2014-01-01T23:59:59.000Z

166

Network topology analysis.  

SciTech Connect (OSTI)

Emerging high-bandwidth, low-latency network technology has made network-based architectures both feasible and potentially desirable for use in satellite payload architectures. The selection of network topology is a critical component when developing these multi-node or multi-point architectures. This study examines network topologies and their effect on overall network performance. Numerous topologies were reviewed against a number of performance, reliability, and cost metrics. This document identifies a handful of good network topologies for satellite applications and the metrics used to justify them as such. Since often multiple topologies will meet the requirements of the satellite payload architecture under development, the choice of network topology is not easy, and in the end the choice of topology is influenced by both the design characteristics and requirements of the overall system and the experience of the developer.

Kalb, Jeffrey L.; Lee, David S.

2008-01-01T23:59:59.000Z

167

Experimental Satellite Quantum Communications  

E-Print Network [OSTI]

Quantum Communications on planetary scale require complementary channels including ground and satellite links. The former have progressed up to commercial stage using fiber-cables, while for satellite links, the absence of terminals in orbit has impaired theirs development. However, the demonstration of the feasibility of such links is crucial for designing space payloads and to eventually enable the realization of protocols such as quantum-key-distribution (QKD) and quantum teleportation along satellite-to-ground or intersatellite links. We demonstrated the faithful transmission of qubits from space to ground by exploiting satellite corner cube retroreflectors acting as transmitter in orbit, obtaining a low error rate suitable for QKD. We also propose a two-way QKD protocol exploiting modulated retroreflectors that necessitates a minimal payload on satellite, thus facilitating the expansion of Space Quantum Communications.

Giuseppe Vallone; Davide Bacco; Daniele Dequal; Simone Gaiarin; Vincenza Luceri; Giuseppe Bianco; Paolo Villoresi

2014-06-16T23:59:59.000Z

168

Vertical sampling flights in support of the 1981 ASCOT cooling tower experiments: field effort and data  

SciTech Connect (OSTI)

During the month of August 1981, three nights of experimental sampling of tracers released into the cooling tower plume of a geothermal power plant were conducted. In these experiments a tethered balloon was used to lift a payload so as to obtain vertical profiles of the cooling tower plume and the entrained tracers. A description of the equipment used, the field effort and the data acquired are presented here.

Gay, G.T.

1982-03-01T23:59:59.000Z

169

Improving haul truck productivity  

SciTech Connect (OSTI)

The paper reviews developments in payload management and cycle times. These were discussed at a roundtable held at the Haulage and Loading 2007 conference held in May in Phoenix, AZ, USA. Several original equipment manufacturers (OEMs) explaind what their companies were doing to improve cycle times for trucks, shovels and excavators used in surface coal mining. Quotations are given from Dion Domaschenz of Liebherr and Steve Plott of Cat Global Mining. 4 figs.

Fiscor, S.

2007-06-15T23:59:59.000Z

170

Rocket borne solar eclipse experiment to measure the temperature structure of the solar corona via lyman-. cap alpha. line profile observations  

SciTech Connect (OSTI)

A rocket borne experiment to measure the temperature structure of the inner solar corona via the doppler broadening of the resonance hydrogen Lyman-..cap alpha.. (lambda1216A) radiation scattered by ambient neutral hydrogen atoms was attempted during the 16 Feb 1980 solar eclipse. Two Nike-Black Brant V sounding rockets carrying instrumented payloads were launched into the path of the advancing eclipse umbra from the San Marco satellite launch platform 3 miles off the east coast of Kenya.

Argo, H.V.

1981-01-01T23:59:59.000Z

171

Structural design of a lunar lander spacecraft for the Texas space grant regolith oxygen production experiment  

E-Print Network [OSTI]

jet firings, pyrotechnic firings, and landing on the lunar surface. Thermal Loads ? Thermal isolation of electronics and payload must be provided along with thermal control of the propellant lines to prevent freezing. Space vehicles commonly...'ran@(r - Steady-state thruster accelerations, transient loads during pointing maneuvers and attitude control burns, pyrotechnic shock from separation events, and vibrations due to antenna and solar panel deployments all contribute to the loading environment...

Baccus, Ronald Kregg

1996-01-01T23:59:59.000Z

172

Experimental verification of active control in a microgravity environment  

E-Print Network [OSTI]

of the proposed Space Station. Although this location eliminates accelerations induced by rotation of the Space Station, the experiment must be isolated from structural vibrations that may be caused by rotating machinery and crew push off. In order to isolate... response of the payload to various initial conditions. Results from these tests indicate a favorable comparison between the experiment and the analytical model for all controllers and free vibration. Of the three controllers, combinational control...

Cordera, Joseph Frank

1990-01-01T23:59:59.000Z

173

Missile sizing for ascent-phase intercept  

SciTech Connect (OSTI)

A computer code has been developed to determine the size of a ground-launched, multistage missile which can intercept a theater ballistic missile before it leaves the atmosphere. Typical final conditions for the inteceptor are 450 km range, 60 km altitude, and 80 sec flight time. Given the payload mass (35 kg), which includes a kinetic kill vehicle, and achievable values for the stage mass fractions (0.85), the stage specific impulses (290 sec), and the vehicle density (60 lb/ft{sup 3}), the launch mass is minimized with respect to the stage payload mass ratios, the stage burn times, and the missile angle of attack history subject to limits on the angle of attack (10 deg), the dynamic pressure (60,000 psf), and the maneuver load (200,000 psf deg). For a conical body, the minimum launch mass is approximately 1900 kg. The missile has three stages, and the payload coasts for 57 sec. A trade study has been performed by varying the flight time, the range, and the dynamic pressure Emits. With the results of a sizing study for a 70 lb payload and q{sub max} = 35,000 psf, a more detailed design has been carried out to determine heat shield mass, tabular aerodynamics, and altitude dependent thrust. The resulting missile has approximately 100 km less range than the sizing program predicted primarily because of the additional mass required for heat protection. On the other hand, launching the same missile from an aircraft increases its range by approximately 100 km. Sizing the interceptor for air launch with the same final conditions as the ground-launched missile reduces its launch mass to approximately 1000 kg.

Hull, D.G. [Univ. of Texas, Austin, TX (United States). Dept. of Aerospace Engineering and Engineering Mechanics; Salguero, D.E. [Sandia National Labs., Albuquerque, NM (United States)

1994-11-01T23:59:59.000Z

174

Integration of Radioisotope Heat Source with Stirling Engine and Cooler for Venus Internal-Structure Mission  

SciTech Connect (OSTI)

The primary mission goal is to perform long-term seismic measurements on Venus, to study its largely unknown internal structure. The principal problem is that most payload components cannot long survive Venus's harsh environment, 90 bars at 500 degrees C. To meet the mission life goal, such components must be protected by a refrigerated payload bay. JPL Investigators have proposed a mission concept employing a lander with a spherical payload bay cooled to 25 degrees C by a Stirling cooler powered by a radioisotope-heated Sitrling engine. To support JPL's mission study, NASA/Lewis and MTI have proposed a conceptual design for a hydraulically coupled Stirling engine and cooler, and Fairchild Space - with support of the Department of Energy - has proposed a design and integration scheme for a suitable radioisotope heat source. The key integration problem is to devise a simple, light-weight, and reliable scheme for forcing the radioisotope decay heat to flow through the Stirling engine during operation on Venus, but to reject that heat to the external environment when the Stirling engine and cooler are not operating (e.g., during the cruise phase, when the landers are surrounded by heat shields needed for protection during subsequent entry into the Venusian atmosphere.) A design and integration scheme for achieving these goals, together with results of detailed thermal analyses, are described in this paper. There are 7 copies in the file.

Schock, Alfred

1993-10-01T23:59:59.000Z

175

A Cheap Levitating Gas/Load Pipeline  

E-Print Network [OSTI]

Design of new cheap aerial pipelines, a large flexible tube deployed at high altitude, for delivery of natural (fuel) gas, water and other payload over a long distance is delineated. The main component of the natural gas is methane which has a specific weight less than air. A lift force of one cubic meter of methane equals approximately 0.5 kg (1 pound). The lightweight film flexible pipeline can be located in air at high altitude and, as such, does not damage the environment. Using the lift force of this pipeline and wing devices payloads of oil, water, or other fluids, or even solids such as coal, cargo, passengers can be delivered cheaply at long distance. This aerial pipeline dramatically decreases the cost and the time of construction relative to conventional pipelines of steel which saves energy and greatly lowers the capital cost of construction. The article contains a computed project for delivery 24 billion cubic meters of gas and tens of million tons of oil, water or other payload per year.

Alexander Bolonkin

2008-12-02T23:59:59.000Z

176

Prospect for UV observations from the Moon  

E-Print Network [OSTI]

Space astronomy in the last 40 years has largely been done from spacecraft in low Earth orbit (LEO) for which the technology is proven and delivery mechanisms are readily available. However, new opportunities are arising with the surge in commercial aerospace missions. We describe here one such possibility: deploying a small instrument on the Moon. This can be accomplished by flying onboard the Indian entry to the Google Lunar X PRIZE competition, Team Indus mission, which is expected to deliver a nearly 30 kgs of payloads to the Moon, with a rover as its primary payload. We propose to mount a wide-field far-UV (130--180 nm) imaging telescope as a payload on the Team Indus lander. Our baseline operation is a fixed zenith pointing but with the option of a mechanism to allow observations of different attitudes. Pointing towards intermediate ecliptic latitude (50 deg or above) ensures that the Sun is at least 40 deg off the line of sight at all times. In this position, the telescope can cover higher galactic lat...

Safonova, Margarita; Mohan, Rekhesh; Sreejith, A G; Murthy, Jayant; Brosch, Noah; Kappelmann, Norbert; Sharma, Arpit; Narayan, Rahul

2014-01-01T23:59:59.000Z

177

Sandia Multispectral Airborne Lidar for UAV Deployment  

SciTech Connect (OSTI)

Sandia National Laboratories has initiated the development of an airborne system for W laser remote sensing measurements. System applications include the detection of effluents associated with the proliferation of weapons of mass destruction and the detection of biological weapon aerosols. This paper discusses the status of the conceptual design development and plans for both the airborne payload (pointing and tracking, laser transmitter, and telescope receiver) and the Altus unmanned aerospace vehicle platform. Hardware design constraints necessary to maintain system weight, power, and volume limitations of the flight platform are identified.

Daniels, J.W.; Hargis,Jr. P.J.; Henson, T.D.; Jordan, J.D.; Lang, A.R.; Schmitt, R.L.

1998-10-23T23:59:59.000Z

178

UAVs in climate research: The ARM Unmanned Aerospace Vehicle Program  

SciTech Connect (OSTI)

In the last year, a Department of Energy/Strategic Environmental Research and Development Program project known as ``ARM-UAV`` has made important progress in developing and demonstrating the utility of unmanned aerospace vehicles as platforms for scientific measurements. Recent accomplishments include a series of flights using an atmospheric research payload carried by a General Atomics Gnat UAV at Edwards AFB, California, and over ground instruments located in north-central Oklahoma. The reminder of this discussion will provide background on the program and describe the recent flights.

Bolton, W.R.

1994-05-01T23:59:59.000Z

179

Work plan for the fabrication of the radioisotope thermoelectric generator transportation system package mounting  

SciTech Connect (OSTI)

The Radioisotope Thermoelectric Generator (RTG) has available a dedicated system for the transportation of RTG payloads. The RTG Transportation System (System 100) is comprised of four systems; the Package (System 120), the Semi-trailer (System 140), the Gas Management (System 160), and the Facility Transport (System 180). This document provides guidelines on the fabrication, technical requirements, and quality assurance of the Package Mounting (Subsystem 145), part of System 140. The description follows the Development Control Requirements of WHC-CM-6-1, EP 2.4, Rev. 3.

Satoh, J.A.

1994-11-09T23:59:59.000Z

180

1 Thermonuclear Operation Space Lift  

E-Print Network [OSTI]

The Project Orion small fission bomb propulsion concept proposed the one-stage launching of large payloads into low earth orbit, but it was abandoned because of the radioactive fallout into the earth atmosphere. The idea is here revived by the replacement of the small fission bombs with pure deuterium-tritium fusion bombs, and the pusher plate of the Project Orion with a large magnetic mirror. The ignition of the thermonuclear fusion reaction is done by the transient formation of keV super-explosives under the high pressure of a convergent shock wave launched into liquid hydrogen propellant by a conventional high explosive. 1.

F. Winterberg

Note: This page contains sample records for the topic "ur3 ur4 payload" from the National Library of EnergyBeta (NLEBeta).
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to obtain the most current and comprehensive results.


181

Hypersonic airbreathing vehicle visions and enhancing technologies  

SciTech Connect (OSTI)

This paper addresses the visions for hypersonic airbreathing vehicles and the advanced technologies that forge and enhance the designs. The matrix includes space access vehicles (single-stage-to-orbit (SSTO), two-stage-to-orbit (2STO) and three-stage-to-orbit (3STO)) and endoatmospheric vehicles (airplanes{emdash}missiles are omitted). The characteristics, the performance potential, the technologies and the synergies will be discussed. A common design constraint is that all vehicles (space access and endoatmospheric) have enclosed payload bays. {copyright} {ital 1997 American Institute of Physics.}

Hunt, J.L.; Lockwood, M.K.; Petley, D.H.; Pegg, R.J. [NASA Langley Research Center (LaRC) Hampton, Virginia (United States)

1997-01-01T23:59:59.000Z

182

Analytical modeling of balloon launch dynamics  

E-Print Network [OSTI]

NOMENCLATURE (continued) s = gore length, ft T = thickness, mil t = time, secs t = material density constant, lbs/ft /mil 2 U = velocity, ft/sec V = volume, ft 3 W = weight, lbs w = weight per unit surface area, lbs/ft 2 x = horizontal position, ft y... configuration t/ =p T t/=s ti t/ =. os ty pre-payload release t/ ? t. ti Fig. 2 I schematic of the balloon launch sequence. order of I mil thick, must be handled in addition to the other flight hardware. As an example, weights, lengths, and other...

Strganac, Thomas W

1980-01-01T23:59:59.000Z

183

Proposal for development of a resource and commodity highway system. Research report  

SciTech Connect (OSTI)

In 1986, the Kentucky General Assembly established the Extended Weight Coal and Coal By-Products Haul Road System. The system includes approximately 3,200 miles of the most significant coal-haul roads in the state and permits coal trucks to carry much larger payloads than trucks with other commodities. In many ways, the extended-weight system has been very successful. Coal-transportation productivity has been substantially increased, and Kentucky coal continues to remain competitive in the marketplace. The study, conducted by the Kentucky Transportation Center, concluded that development of a statewide trucking network, herein named the Resource and Commodity Highway System, was both feasibile and desirable.

Deacon, J.A.; Allen, D.L.; Crabtree, J.D.; Agent, K.R.; Pigman, J.G.

1994-01-01T23:59:59.000Z

184

On-orbit calibration of soft X-ray detector on Chang'E-2 satellite  

E-Print Network [OSTI]

X-ray spectrometer is one of the satellite payloads on Chang'E-2 satellite. The soft X-ray detector is one of the device on X-ray spectrometer which is designed to detect the major rock-forming elements within 0.5-10keV range on lunar surface. In this paper, energy linearity and energy resolution calibration is done using a weak Fe55 source, while temperature and time effect is considered not take big error. The total uncertainty is estimated to be within 5% after correction.

Hong Xiao; Wenxi Penga; Huanyu Wang; Xingzhu Cui; Dongya Guo

2015-02-02T23:59:59.000Z

185

On-orbit calibration of soft X-ray detector on Chang'E-2 satellite  

E-Print Network [OSTI]

X-ray spectrometer is one of the satellite payloads on Chang'E-2 satellite. The soft X-ray detector is one of the device on X-ray spectrometer which is designed to detect the major rock-forming elements within 0.5-10keV range on lunar surface. In this paper, energy linearity and energy resolution calibration is done using a weak Fe55 source, while temperature and time effect is considered not take big error. The total uncertainty is estimated to be within 5% after correction.

Xiao, Hong; Wang, Huanyu; Cui, Xingzhu; Guo, Dongya

2015-01-01T23:59:59.000Z

186

De-wrinkling of pre-tensioned membranes  

E-Print Network [OSTI]

-length. In Cunliffe (2003), trimming simulations are performed for a right-angled, isosceles membrane behaving as a biaxially-loaded quarter panel in a solar sail and, by trial and error, it is found that compressive stresses mostly disappear when all edges... % of the total area (Stamper et al.,1. Introduction Gossamer structures are thin-wa favoured in the design, construction spacecraft, such as solar-propelled sa telescopes and, more recently, de- inside restricted payload volumes, th ratios of any deployable...

Bonin, A. S.; Seffen, K. A.

2014-06-17T23:59:59.000Z

187

Remote-Handled Transuranic Content Codes  

SciTech Connect (OSTI)

The Remote-Handled Transuranic (RH-TRU) Content Codes (RH-TRUCON) document representsthe development of a uniform content code system for RH-TRU waste to be transported in the 72-Bcask. It will be used to convert existing waste form numbers, content codes, and site-specificidentification codes into a system that is uniform across the U.S. Department of Energy (DOE) sites.The existing waste codes at the sites can be grouped under uniform content codes without any lossof waste characterization information. The RH-TRUCON document provides an all-encompassing|description for each content code and compiles this information for all DOE sites. Compliance withwaste generation, processing, and certification procedures at the sites (outlined in this document foreach content code) ensures that prohibited waste forms are not present in the waste. The contentcode gives an overall description of the RH-TRU waste material in terms of processes and|packaging, as well as the generation location. This helps to provide cradle-to-grave traceability ofthe waste material so that the various actions required to assess its qualification as payload for the72-B cask can be performed. The content codes also impose restrictions and requirements on themanner in which a payload can be assembled.The RH-TRU Waste Authorized Methods for Payload Control (RH-TRAMPAC), Appendix 1.3.7of the 72-B Cask Safety Analysis Report (SAR), describes the current governing procedures|applicable for the qualification of waste as payload for the 72-B cask. The logic for this|classification is presented in the 72-B Cask SAR. Together, these documents (RH-TRUCON,|RH-TRAMPAC, and relevant sections of the 72-B Cask SAR) present the foundation and|justification for classifying RH-TRU waste into content codes. Only content codes described in thisdocument can be considered for transport in the 72-B cask. Revisions to this document will be madeas additional waste qualifies for transport. |Each content code uniquely identifies the generated waste and provides a system for tracking theprocess and packaging history. Each content code begins with a two-letter site abbreviation thatindicates the shipper of the RH-TRU waste. The site-specific letter designations for each of the|DOE sites are provided in Table 1. Not all of the sites listed in Table 1 have generated/stored RH-|TRU waste.

Washington TRU Solutions

2001-08-01T23:59:59.000Z

188

Space-QUEST: Experiments with quantum entanglement in space  

E-Print Network [OSTI]

The European Space Agency (ESA) has supported a range of studies in the field of quantum physics and quantum information science in space for several years, and consequently we have submitted the mission proposal Space-QUEST (Quantum Entanglement for Space Experiments) to the European Life and Physical Sciences in Space Program. We propose to perform space-to-ground quantum communication tests from the International Space Station (ISS). We present the proposed experiments in space as well as the design of a space based quantum communication payload.

Rupert Ursin; Thomas Jennewein; Johannes Kofler; Josep M. Perdigues; Luigi Cacciapuoti; Clovis J. de Matos; Markus Aspelmeyer; Alejandra Valencia; Thomas Scheidl; Alessandro Fedrizzi; Antonio Acin; Cesare Barbieri; Giuseppe Bianco; Caslav Brukner; Jose Capmany; Sergio Cova; Dirk Giggenbach; Walter Leeb; Robert H. Hadfield; Raymond Laflamme; Norbert Lutkenhaus; Gerard Milburn; Momtchil Peev; Timothy Ralph; John Rarity; Renato Renner; Etienne Samain; Nikolaos Solomos; Wolfgang Tittel; Juan P. Torres; Morio Toyoshima; Arturo Ortigosa-Blanch; Valerio Pruneri; Paolo Villoresi; Ian Walmsley; Gregor Weihs; Harald Weinfurter; Marek Zukowski; Anton Zeilinger

2008-06-05T23:59:59.000Z

189

A Measurement of the Flux of Cosmic Ray Iron at 5 x 10^13 eV  

E-Print Network [OSTI]

We present results from the initial flight of our Balloon Air CHerenkov (BACH) payload. BACH detects air Cherenkov radiation from cosmic ray nuclei as coincident flashes in two optical modules. The flight (dubbed PDQ BACH) took place on April 22, 1998 from Ft. Sumner, New Mexico. During an exposure of 2.75 hours, with a typical threshold energy for iron nuclei of 2.2$\\times10^{13}$ eV, we observed several events cleanly identifiable as iron group nuclei. Analysis of the data yields a new flux measurement that is fully consistent with that reported by other investigations.

J. Clem; W. Droege; P. A. Evenson; H. Fischer; G. Green; D. Huber; H. Kunow; D. Seckel

2001-03-23T23:59:59.000Z

190

RH-TRU Waste Content Codes (RH-TRUCON)  

SciTech Connect (OSTI)

The Remote-Handled Transuranic (RH-TRU) Content Codes (RH-TRUCON) document describes the inventory of RH-TRU waste within the transportation parameters specified by the Remote-Handled Transuranic Waste Authorized Methods for Payload Control (RH-TRAMPAC).1 The RH-TRAMPAC defines the allowable payload for the RH-TRU 72-B. This document is a catalog of RH-TRU 72-B authorized contents by site. A content code is defined by the following components: A two-letter site abbreviation that designates the physical location of the generated/stored waste (e.g., ID for Idaho National Laboratory [INL]). The site-specific letter designations for each of the sites are provided in Table 1. A three-digit code that designates the physical and chemical form of the waste (e.g., content code 317 denotes TRU Metal Waste). For RH-TRU waste to be transported in the RH-TRU 72-B, the first number of this three-digit code is 3. The second and third numbers of the three-digit code describe the physical and chemical form of the waste. Table 2 provides a brief description of each generic code. Content codes are further defined as subcodes by an alpha trailer after the three-digit code to allow segregation of wastes that differ in one or more parameter(s). For example, the alpha trailers of the subcodes ID 322A and ID 322B may be used to differentiate between waste packaging configurations. As detailed in the RH-TRAMPAC, compliance with flammable gas limits may be demonstrated through the evaluation of compliance with either a decay heat limit or flammable gas generation rate (FGGR) limit per container specified in approved content codes. As applicable, if a container meets the watt*year criteria specified by the RH-TRAMPAC, the decay heat limits based on the dose-dependent G value may be used as specified in an approved content code. If a site implements the administrative controls outlined in the RH-TRAMPAC and Appendix 2.4 of the RH-TRU Payload Appendices, the decay heat or FGGR limits based on a 10-day shipping period (rather than the standard 60-day shipping period) may be used as specified in an approved content code. Requests for new or revised content codes may be submitted to the WIPP RH-TRU Payload Engineer for review and approval, provided all RH-TRAMPAC requirements are met.

Washington TRU Solutions LLC

2007-08-01T23:59:59.000Z

191

RH-TRU Waste Content Codes  

SciTech Connect (OSTI)

The Remote-Handled Transuranic (RH-TRU) Content Codes (RH-TRUCON) document describes the inventory of RH-TRU waste within the transportation parameters specified by the Remote-Handled Transuranic Waste Authorized Methods for Payload Control (RH-TRAMPAC).1 The RH-TRAMPAC defines the allowable payload for the RH-TRU 72-B. This document is a catalog of RH-TRU 72-B authorized contents by site. A content code is defined by the following components: A two-letter site abbreviation that designates the physical location of the generated/stored waste (e.g., ID for Idaho National Laboratory [INL]). The site-specific letter designations for each of the sites are provided in Table 1. A three-digit code that designates the physical and chemical form of the waste (e.g., content code 317 denotes TRU Metal Waste). For RH-TRU waste to be transported in the RH-TRU 72-B, the first number of this three-digit code is 3. The second and third numbers of the three-digit code describe the physical and chemical form of the waste. Table 2 provides a brief description of each generic code. Content codes are further defined as subcodes by an alpha trailer after the three-digit code to allow segregation of wastes that differ in one or more parameter(s). For example, the alpha trailers of the subcodes ID 322A and ID 322B may be used to differentiate between waste packaging configurations. As detailed in the RH-TRAMPAC, compliance with flammable gas limits may be demonstrated through the evaluation of compliance with either a decay heat limit or flammable gas generation rate (FGGR) limit per container specified in approved content codes. As applicable, if a container meets the watt*year criteria specified by the RH-TRAMPAC, the decay heat limits based on the dose-dependent G value may be used as specified in an approved content code. If a site implements the administrative controls outlined in the RH-TRAMPAC and Appendix 2.4 of the RH-TRU Payload Appendices, the decay heat or FGGR limits based on a 10-day shipping period (rather than the standard 60-day shipping period) may be used as specified in an approved content code. Requests for new or revised content codes may be submitted to the WIPP RH-TRU Payload Engineer for review and approval, provided all RH-TRAMPAC requirements are met.

Washington TRU Solutions

2007-07-01T23:59:59.000Z

192

RH-TRU Waste Content Codes (RH-TRUCON)  

SciTech Connect (OSTI)

The Remote-Handled Transuranic (RH-TRU) Content Codes (RH-TRUCON) document describes the inventory of RH-TRU waste within the transportation parameters specified by the Remote-Handled Transuranic Waste Authorized Methods for Payload Control (RH-TRAMPAC).1 The RH-TRAMPAC defines the allowable payload for the RH-TRU 72-B. This document is a catalog of RH-TRU 72-B authorized contents by site. A content code is defined by the following components: A two-letter site abbreviation that designates the physical location of the generated/stored waste (e.g., ID for Idaho National Laboratory [INL]). The site-specific letter designations for each of the sites are provided in Table 1. A three-digit code that designates the physical and chemical form of the waste (e.g., content code 317 denotes TRU Metal Waste). For RH-TRU waste to be transported in the RH-TRU 72-B, the first number of this three-digit code is 3. The second and third numbers of the three-digit code describe the physical and chemical form of the waste. Table 2 provides a brief description of each generic code. Content codes are further defined as subcodes by an alpha trailer after the three-digit code to allow segregation of wastes that differ in one or more parameter(s). For example, the alpha trailers of the subcodes ID 322A and ID 322B may be used to differentiate between waste packaging configurations. As detailed in the RH-TRAMPAC, compliance with flammable gas limits may be demonstrated through the evaluation of compliance with either a decay heat limit or flammable gas generation rate (FGGR) limit per container specified in approved content codes. As applicable, if a container meets the watt*year criteria specified by the RH-TRAMPAC, the decay heat limits based on the dose-dependent G value may be used as specified in an approved content code. If a site implements the administrative controls outlined in the RH-TRAMPAC and Appendix 2.4 of the RH-TRU Payload Appendices, the decay heat or FGGR limits based on a 10-day shipping period (rather than the standard 60-day shipping period) may be used as specified in an approved content code. Requests for new or revised content codes may be submitted to the WIPP RH-TRU Payload Engineer for review and approval, provided all RH-TRAMPAC requirements are met.

Washington TRU Solutions

2007-05-30T23:59:59.000Z

193

Safety analysis report for the TRUPACT-II shipping package (condensed version). Volume 1, Rev. 14  

SciTech Connect (OSTI)

The condensed version of the TRUPACT-II Contact Handled Transuranic Waste Safety Analysis Report for Packaging (SARP) contains essential material required by TRUPACT-II users, plus additional contents (payload) information previously submitted to the U.S. Nuclear Regulatory Commission. All or part of the following sections, which are not required by users of the TRUPACT-II, are deleted from the condensed version: (i) structural analysis, (ii) thermal analysis, (iii) containment analysis, (iv) criticality analysis, (v) shielding analysis, and (vi) hypothetical accident test results.

NONE

1994-10-01T23:59:59.000Z

194

SP-100 planetary mission/system preliminary design study. Final report, technical information report  

SciTech Connect (OSTI)

This report contains a discussion on many aspects of a nuclear electric propulsion planetary science mission and spacecraft using the proposed SP-100 nuclear power subsystem. A review of the science rationale for such missions is included. A summary of eleven nuclear electric propulsion planetary missions is presented. A conceptual science payload, mission design, and spacecraft design is included for the Saturn Ring Rendezvous mission. Spacecraft and mission costs have been estimated for two potential sequences of nuclear electric propulsion planetary missions. The integration issues and requirements on the proposed SP-100 power subsystems are identified.

Jones, R.M. [ed.

1986-02-01T23:59:59.000Z

195

Unmanned Aerial Vehicle Instrumentation for Rapid Aerial Photo System  

E-Print Network [OSTI]

This research will proposed a new kind of relatively low cost autonomous UAV that will enable farmers to make just in time mosaics of aerial photo of their crop. These mosaics of aerial photo should be able to be produced with relatively low cost and within the 24 hours of acquisition constraint. The autonomous UAV will be equipped with payload management system specifically developed for rapid aerial mapping. As mentioned before turn around time is the key factor, so accuracy is not the main focus (not orthorectified aerial mapping). This system will also be equipped with special software to post process the aerial photos to produce the mosaic aerial photo map

Adiprawita, Widyawardana; Semibiring, Jaka

2008-01-01T23:59:59.000Z

196

Pure Nuclear Fusion Bomb Propulsion  

E-Print Network [OSTI]

Recent progress towards the non-fission ignition of thermonuclear micro-explosions raises the prospect for a revival of the nuclear bomb propulsion idea, both for the fast transport of large payloads within the solar system and the launch into earth orbit without the release of fission products into the atmosphere. To reach this goal three areas of research are of importance: 1)Compact thermonuclear ignition drivers. 2)Fast ignition and deuterium burn. 3)Space-craft architecture involving magnetic insulation and GeV electrostatic potentials

Winterberg, F

2008-01-01T23:59:59.000Z

197

Sharp and the Jules Verne Launcher  

SciTech Connect (OSTI)

Lawrence Livermore National Laboratory (LLNL) has built the worlds largest hydrogen gas gun called SHARP, (Super High Altitude Research Project). Originally designed to launch 5 kg to a 450 km altitude, SHARP is configured horizontally at Site 300 in Tracy, California. SHARP is successfully delivering 5 kg scramjets at Mach 9 in aerophysics tests. Some of the results of the scramjet tests are enlightening and are presented insofar as they are relevant to future launches into space. Using a light gas gun to launch payloads into orbit has been analyzed. We look at LEO (Low Earth Orbit), GEO (Geosynchronous Earth Orbit), and LO (Lunar Orbit). We present a conceptual design for a large light gas gun called the Jules Verne Launcher (JVL). The JVL can deliver 3.3 metric tons to a 500 km low earth orbit. We anticipate one launch per day. We present the history of light gas guns, the SHARP design and performance, and the JVL design. Another section is devoted to the vehicle environment and resultant design. Lastly, we present a cost analysis. Our results indicated that the JVL will be able to deliver 1000 metric tons of payload to LEO yearly. The cost will be 5{percent} of the best US rocket delivery cost. This technology will enable the next phase of man{close_quote}s exploration of space. {copyright} {ital 1996 American Institute of Physics.}

Hunter, J.; Cartland, H. [Lawrence Livermore National Laboratory, Imaging and Detection Program, P.O. Box 808, L-495, Livermore, California 94551 (United States)

1996-03-01T23:59:59.000Z

198

Design of the magnetic diagnostics unit onboard LISA Pathfinder  

E-Print Network [OSTI]

LISA (Laser Interferometer Space Antenna) is a joint mission of ESA and NASA which aims to be the first space-borne gravita- tional wave observatory. Due to the high complexity and technological challenges that LISA will face, ESA decided to launch a technological demonstrator, LISA Pathfinder. The payload of LISA Pathfinder is the so-called LISA Technology Package, and will be the highest sensitivity geodesic explorer flown to date. The LISA Technology Package is designed to measure relative accelerations between two test masses in nominal free fall (geodesic motion). The magnetic, thermal and radiation disturbances affecting the payload are monitored and dealt by the diagnostics subsystem. The diagnostics subsystem consists of several modules, and one of these is the magnetic diagnostics unit. Its main function is the assessment of differential acceleration noise between test masses due to the magnetic effects. To do so, it has to determine the magnetic characteristics of the test masses, namely their magnetic remanences and susceptibilities. In this paper we show how this can be achieved to the desired accuracy.

Marc Diaz-Aguil; Ignacio Mateos; Juan Ramos-Castro; Alberto Lobo; Enrique Garca-Berro

2012-02-13T23:59:59.000Z

199

A Low-Cost Natural Gas/Freshwater Aerial Pipeline  

E-Print Network [OSTI]

Offered is a new type of low-cost aerial pipeline for delivery of natural gas, an important industrial and residential fuel, and freshwater as well as other payloads over long distances. The offered pipeline dramatically decreases the construction and operation costs and the time necessary for pipeline construction. A dual-use type of freight pipeline can improve an arid rural environment landscape and provide a reliable energy supply for cities. Our aerial pipeline is a large, self-lofting flexible tube disposed at high altitude. Presently, the term "natural gas" lacks a precise technical definition, but the main components of natural gas are methane, which has a specific weight less than air. A lift force of one cubic meter of methane equals approximately 0.5 kg. The lightweight film flexible pipeline can be located in the Earth-atmosphere at high altitude and poses no threat to airplanes or the local environment. The authors also suggest using lift force of this pipeline in tandem with wing devices for cheap shipment of a various payloads (oil, coal and water) over long distances. The article contains a computed macroproject in northwest China for delivery of 24 billion cubic meter of gas and 23 millions tonnes of water annually.

Alexander Bolonkin; Richard Cathcart

2007-01-05T23:59:59.000Z

200

Optical Manipulation of Vesicles for Optofluidic Applications  

SciTech Connect (OSTI)

In this report, we review our recent results in the optical micromanipulation of vesicles. Traditionally, vesicle manipulation has been possible by employing photon momentum and optical trapping, giving rise to unique observations of vesicle shape changes and soft matter mechanics. Contrary to these attempts, we employ photon energy rather than momentum, by sensitizing vesicles with an oxidizing moiety. The later converts incident photons to reactive oxygen species, which in turn attack and compromise the stability of the vesicle membrane. Both coherent and incoherent radiation was employed. Polymersome re-organization into smaller diameter vesicles was possible by focusing the excitation beam in the vicinity of the polymersomes. Extended vesicle illumination with a collimated beam lead to their complete destabilization and micelle formation. Single particle analysis revealed that payload release takes place within seconds of illumination in an explosive burst. We will discuss the destabilization and payload release kinetics, as revealed by high resolution microscopy at the single particle level, as well as potential applications in single cell biomodulation.

Vasdekis, Andreas E.; Scott, E. A.; O'Neil, C. P.; Psaltis, D.; Hubbell, J. A.

2013-09-12T23:59:59.000Z

Note: This page contains sample records for the topic "ur3 ur4 payload" from the National Library of EnergyBeta (NLEBeta).
While these samples are representative of the content of NLEBeta,
they are not comprehensive nor are they the most current set.
We encourage you to perform a real-time search of NLEBeta
to obtain the most current and comprehensive results.


201

Improving ISR Radar Utilization (How I quit blaming the user and made the radar easier to use).  

SciTech Connect (OSTI)

In modern multi - sensor multi - mode Intelligence, Surveillance, and Reconnaissance ( ISR ) platforms, the plethora of options available to a sensor/payload operator are quite large, leading to an over - worked operator often down - selecting to favorite sensors an d modes. For example, Full Motion Video (FMV) is justifiably a favorite sensor at the expense of radar modes, even if radar modes can offer unique and advantageous information. The challenge is then to increase the utilization of the radar modes in a man ner attractive to the sensor/payload operator. We propose that this is best accomplished by combining sensor modes and displays into 'super - modes'. - 4 - Acknowledgements This report is the result of a n unfunded research and development activity . Sandia Natio nal Laboratories is a multi - program laboratory managed and operated by Sandia Corporation, a wholly owned subsidiary of Lockheed Martin Corporation, for the U.S. Department of Energy's National Nuclear Security Administration under contract DE - AC04 - 94AL850 00.

Doerry, Armin W.

2014-08-01T23:59:59.000Z

202

Monolithic ballasted penetrator  

DOE Patents [OSTI]

The present invention is a monolithic ballasted penetrator capable of delivering a working payload to a hardened target, such as reinforced concrete. The invention includes a ballast made from a dense heavy material insert and a monolithic case extending along an axis and consisting of a high-strength steel alloy. The case includes a nose end containing a hollow portion in which the ballast is nearly completely surrounded so that no movement of the ballast relative to the case is possible during impact with a hard target. The case is cast around the ballast, joining the two parts together. The ballast may contain concentric grooves or protrusions that improve joint strength between the case and ballast. The case further includes a second hollow portion; between the ballast and base, which has a payload fastened within this portion. The penetrator can be used to carry instrumentation to measure the geologic character of the earth, or properties of arctic ice, as they pass through it.

Hickerson, Jr., James P. (Cedar Crest, NM); Zanner, Frank J. (Sandia Park, NM); Baldwin, Michael D. (Albuquerque, NM); Maguire, Michael C. (Worcester, MA)

2001-01-01T23:59:59.000Z

203

RH-TRU Waste Content Codes (RH TRUCON)  

SciTech Connect (OSTI)

The Remote-Handled Transuranic (RH-TRU) Content Codes (RH-TRUCON) document describes the inventory of RH-TRU waste within the transportation parameters specified by the Remote-Handled Transuranic Waste Authorized Methods for Payload Control (RH-TRAMPAC).1 The RH-TRAMPAC defines the allowable payload for the RH-TRU 72-B. This document is a catalog of RH-TRU 72-B authorized contents by site. A content code is defined by the following components: A two-letter site abbreviation that designates the physical location of the generated/stored waste (e.g., ID for Idaho National Laboratory [INL]). The site-specific letter designations for each of the sites are provided in Table 1. A three-digit code that designates the physical and chemical form of the waste (e.g., content code 317 denotes TRU Metal Waste). For RH-TRU waste to be transported in the RH-TRU 72-B, the first number of this three-digit code is 3. The second and third numbers of the three-digit code describe the physical and chemical form of the waste. Table 2 provides a brief description of each generic code. Content codes are further defined as subcodes by an alpha trailer after the three-digit code to allow segregation of wastes that differ in one or more parameter(s). For example, the alpha trailers of the subcodes ID 322A and ID 322B may be used to differentiate between waste packaging configurations. As detailed in the RH-TRAMPAC, compliance with flammable gas limits may be demonstrated through the evaluation of compliance with either a decay heat limit or flammable gas generation rate (FGGR) limit per container specified in approved content codes. As applicable, if a container meets the watt*year criteria specified by the RH-TRAMPAC, the decay heat limits based on the dose-dependent G value may be used as specified in an approved content code. If a site implements the administrative controls outlined in the RH-TRAMPAC and Appendix 2.4 of the RH-TRU Payload Appendices, the decay heat or FGGR limits based on a 10-day shipping period (rather than the standard 60-day shipping period) may be used as specified in an approved content code.

Washington TRU Solutions

2007-05-01T23:59:59.000Z

204

Remote-Handled Transuranic Content Codes  

SciTech Connect (OSTI)

The Remote-Handled Transuranic (RH-TRU) Content Codes (RH-TRUCON) document describes the inventory of RH-TRU waste within the transportation parameters specified by the Remote-Handled Transuranic Waste Authorized Methods for Payload Control (RH-TRAMPAC).1 The RH-TRAMPAC defines the allowable payload for the RH-TRU 72-B. This document is a catalog of RH-TRU 72-B authorized contents by site. A content code is defined by the following components: A two-letter site abbreviation that designates the physical location of the generated/stored waste (e.g., ID for Idaho National Laboratory [INL]). The site-specific letter designations for each of the sites are provided in Table 1. A three-digit code that designates the physical and chemical form of the waste (e.g., content code 317 denotes TRU Metal Waste). For RH-TRU waste to be transported in the RH-TRU 72-B, the first number of this three-digit code is 3. The second and third numbers of the three-digit code describe the physical and chemical form of the waste. Table 2 provides a brief description of each generic code. Content codes are further defined as subcodes by an alpha trailer after the three-digit code to allow segregation of wastes that differ in one or more parameter(s). For example, the alpha trailers of the subcodes ID 322A and ID 322B may be used to differentiate between waste packaging configurations. As detailed in the RH-TRAMPAC, compliance with flammable gas limits may be demonstrated through the evaluation of compliance with either a decay heat limit or flammable gas generation rate (FGGR) limit per container specified in approved content codes. As applicable, if a container meets the watt*year criteria specified by the RH-TRAMPAC, the decay heat limits based on the dose-dependent G value may be used as specified in an approved content code. If a site implements the administrative controls outlined in the RH-TRAMPAC and Appendix 2.4 of the RH-TRU Payload Appendices, the decay heat or FGGR limits based on a 10-day shipping period (rather than the standard 60-day shipping period) may be used as specified in an approved content code.

Washington TRU Solutions

2006-12-01T23:59:59.000Z

205

Field Operations Program, Toyota PRIUS Hybrid Electric Vehicle Performance Characterization Report  

SciTech Connect (OSTI)

The U.S. Department of Energys Field Operations Program evaluates advanced technology vehicles in real-world applications and environments. Advanced technology vehicles include pure electric, hybrid electric, hydrogen, and other vehicles that use emerging technologies such as fuel cells. Information generated by the Program is targeted to fleet managers and others considering the deployment of advanced technology vehicles. As part of the above activities, the Field Operations Program has initiated the testing of the Toyota Prius hybrid electric vehicle (HEV), a technology increasingly being considered for use in fleet applications. This report describes the Pomona Loop testing of the Prius, providing not only initial operational and performance information, but also a better understanding of HEV testing issues. The Pomona Loop testing includes both Urban and Freeway drive cycles, each conducted at four operating scenarios that mix minimum and maximum payloads with different auxiliary (e.g., lights, air conditioning) load levels.

Francfort, James Edward; Nguyen, N.; Phung, J.; Smith, J.; Wehrey, M.

2001-12-01T23:59:59.000Z

206

Infrared source test  

SciTech Connect (OSTI)

The purpose of the Infrared Source Test (IRST) is to demonstrate the ability to track a ground target with an infrared sensor from an airplane. The system is being developed within the Advance Technology Program`s Theater Missile Defense/Unmanned Aerial Vehicle (UAV) section. The IRST payload consists of an Amber Radiance 1 infrared camera system, a computer, a gimbaled mirror, and a hard disk. The processor is a custom R3000 CPU board made by Risq Modular Systems, Inc. for LLNL. The board has ethernet, SCSI, parallel I/O, and serial ports, a DMA channel, a video (frame buffer) interface, and eight MBytes of main memory. The real-time operating system VxWorks has been ported to the processor. The application code is written in C on a host SUN 4 UNIX workstation. The IRST is the result of a combined effort by physicists, electrical and mechanical engineers, and computer scientists.

Ott, L.

1994-11-15T23:59:59.000Z

207

Implementation of an Onboard Visual Tracking System with Small Unmanned Aerial Vehicle (UAV)  

E-Print Network [OSTI]

This paper presents a visual tracking system that is capable or running real time on-board a small UAV (Unmanned Aerial Vehicle). The tracking system is computationally efficient and invariant to lighting changes and rotation of the object or the camera. Detection and tracking is autonomously carried out on the payload computer and there are two different methods for creation of the image patches. The first method starts detecting and tracking using a stored image patch created prior to flight with previous flight data. The second method allows the operator on the ground to select the interest object for the UAV to track. The tracking system is capable of re-detecting the object of interest in the events of tracking failure. Performance of the tracking system was verified both in the lab and during actual flights of the UAV. Results show that the system can run on-board and track a diverse set of objects in real time.

Qadir, Ashraf; Neubert, Jeremiah

2012-01-01T23:59:59.000Z

208

Non-nuclear power sources for deep space  

SciTech Connect (OSTI)

Electric propulsion and non-nuclear power can be used in tandem as a replacement for the current chemical booster and radioisotope thermoelectric generators now in use for deep space applications (i.e., to the asteroid belt and beyond). In current generation systems, electric propulsion is usually considered to be impractical because of the lack of high power for deep space, and non-nuclear power is thought to be impractical partly due to its high mass. However, when taken in combination, a solar powered electric upper stage can provide ample power and propulsion capability for use in deep space. Radioisotope thermoelectric generator (RTG) systems have generally been selected for missions only when other systems are absolutely unavailable. The disadvantages of radioisotopes include the need for nuclear safety as another dimension of concern in payload integration; the lack of assured availability of plutonium in the post-cold-war world; the enormous cost of plutonium-238; and the system complexity introduced by the need to continuously cool the system during the pre-launch phase. A conservative estimate for the total power for the solar array at beginning of life (BOL) may be in the range of 25 kW in order to provide 500 W continuous power at Jupiter. The availability of {approximately} 25 kW(e) in earth orbit raises the interesting possibility of coupling electric propulsion units to this free electric power. If electric propulsion is used to raise the probe from low-earth-orbit to an earth-escape trajectory, the system could actually save on low-earth orbit mass. Electric propulsion could be used by itself in a spiral trajectory orbit raising maneuver to earth escape velocity, or it could be used in conjunction with a chemical upper stage (either solid rocket or liquid), which would boost the payload to an elliptical orbit. The concept is to begin the Earth-Jupiter trip with a swing-by near the Sun close to the orbit of Venus and perhaps even closer if thermal loads can be tolerated. During the solar swing-by, much more power will be produced by the solar panels, allowing the spacecraft's velocity to be increased significantly. The outbound leg of the journey can, therefore, be made much more quickly than with the classical trajectory. For the purposes of a Jupiter mission, it is assumed that 20 km/sec total delta-v would be required. For a payload envelope of 17,304 kg, a 1,900 sec Isp capability means that 11,386 kg of propellant would have to be consumed, leaving 5,917 kg for the mass of the probe plus dry mass of the upper stage. The thruster subsystem would require 765 kg of thruster subsystem mass, and probably less. Assuming tanks, regulators and valves amount to 10% of the propellant mass (very likely a pessimistic assumption), it is possible to assign a mass of 1,150 kg for the tankage subsystem. This results in a mass allowance of at least 4,000 kg for the probe. This compares favorably with the dry mass of 1,637 kg for Galileo, for example, and suggests that more than adequate margin exists. If the payload margin is used for battery storage, flyby missions to the outer planets may be possible.

Kennel, E.B.; Tang, C.; Santarius, J.F.

1998-07-01T23:59:59.000Z

209

TRUPACT-II 157 Examination Report  

SciTech Connect (OSTI)

This report presents the results of examination and recovery activities performed on the TRUPACT-II 157 shipping container. The container was part of a contact-handled transuranic waste shipment being transported on a truck to the Waste Isolation Pilot Plant in New Mexico when an accident occurred. Although the transport vehicle sustained only minor damage, airborne transuranic contamination was detected in air samples extracted from inside TRUPACT-II 157 at the Waste Isolation Pilot Plant. Consequently, the shipping container was rejected, resealed, and returned to the Idaho National Engineering and Environmental Laboratory where the payload was disassembled, examined, and recovered for subsequent reshipment to the Waste Isolation Pilot Plant. This report documents the results of those activities.

Barry H. O'Brien; Jeffrey M. Lacy; Kip E. Archibald

2003-12-01T23:59:59.000Z

210

The PACSAT Communications Experiment (PCE)  

SciTech Connect (OSTI)

While VITA (Volunteers in Technical Assistance) is the recognized world leader in low earth orbiting (LEO) satellite technology (below 1 GHz), its involvement in communications technologies is to facilitate renewable energy technology transfer to developing countries. A communications payload was incorporated into the UoSat 2 satellite (Surrey Univ., UK), launched in 1984; a prototype satellite (PCE) was also launched Jan 1990. US DOE awarded a second grant to VITA to design and test the prototype ground stations (command and field), install field ground stations in several developing country sites, pursue the operational licensing process, and transfer the evaluation results to the design of an operating system. This report covers the principal tasks of this grant.

Not Available

1993-02-12T23:59:59.000Z

211

The PACSAT Communications Experiment (PCE). Final report, August 13, 1990--February 12, 1992  

SciTech Connect (OSTI)

While VITA (Volunteers in Technical Assistance) is the recognized world leader in low earth orbiting (LEO) satellite technology (below 1 GHz), its involvement in communications technologies is to facilitate renewable energy technology transfer to developing countries. A communications payload was incorporated into the UoSat 2 satellite (Surrey Univ., UK), launched in 1984; a prototype satellite (PCE) was also launched Jan 1990. US DOE awarded a second grant to VITA to design and test the prototype ground stations (command and field), install field ground stations in several developing country sites, pursue the operational licensing process, and transfer the evaluation results to the design of an operating system. This report covers the principal tasks of this grant.

Not Available

1993-02-12T23:59:59.000Z

212

CMMAD Usability Case Study in Support of Countermine and Hazard Sensing  

SciTech Connect (OSTI)

During field trials, operator usability data were collected in support of lane clearing missions and hazard sensing for two robot platforms with Robot Intelligence Kernel (RIK) software and sensor scanning payloads onboard. The tests featured autonomous and shared robot autonomy levels where tasking of the robot used a graphical interface featuring mine location and sensor readings. The goal of this work was to provide insights that could be used to further technology development. The efficacy of countermine systems in terms of mobility, search, path planning, detection, and localization were assessed. Findings from objective and subjective operator interaction measures are reviewed along with commentary from soldiers having taken part in the study who strongly endorse the system.

Victor G. Walker; David I. Gertman

2010-04-01T23:59:59.000Z

213

Survivable pulse power space radiator  

DOE Patents [OSTI]

A thermal radiator system is described for use on an outer space vehicle, which must survive a long period of nonuse and then radiate large amounts of heat for a limited period of time. The radiator includes groups of radiator panels that are pivotally connected in tandem, so that they can be moved to deployed configuration wherein the panels lie largely coplanar, and to a stowed configuration wherein the panels lie in a stack to resist micrometerorite damage. The panels are mounted on a boom which separates a hot power source from a payload. While the panels are stowed, warm fluid passes through their arteries to keep them warm enough to maintain the coolant in a liquid state and avoid embrittlement of material. The panels can be stored in a largely cylindrical shell, with panels progressively further from the boom being of progressively shorter length. 5 figs.

Mims, J.; Buden, D.; Williams, K.

1988-03-11T23:59:59.000Z

214

PAT-1 safety analysis report addendum author responses to request for additional information.  

SciTech Connect (OSTI)

The Plutonium Air Transportable Package, Model PAT-1, is certified under Title 10, Code of Federal Regulations Part 71 by the U.S. Nuclear Regulatory Commission (NRC) per Certificate of Compliance (CoC) USA/0361B(U)F-96 (currently Revision 9). The National Nuclear Security Administration (NNSA) submitted SAND Report SAND2009-5822 to NRC that documented the incorporation of plutonium (Pu) metal as a new payload for the PAT-1 package. NRC responded with a Request for Additional Information (RAI), identifying information needed in connection with its review of the application. The purpose of this SAND report is to provide the authors responses to each RAI. SAND Report SAND2010-6106 containing the proposed changes to the Addendum is provided separately.

Weiner, Ruth F.; Schmale, David T.; Kalan, Robert J.; Akin, Lili A.; Miller, David Russell; Knorovsky, Gerald Albert; Yoshimura, Richard Hiroyuki; Lopez, Carlos; Harding, David Cameron; Jones, Perry L.; Morrow, Charles W.

2010-09-01T23:59:59.000Z

215

An automated miniature robotic vehicle inspection system  

SciTech Connect (OSTI)

A novel, autonomous reconfigurable robotic inspection system for quantitative NDE mapping is presented. The system consists of a fleet of wireless (802.11g) miniature robotic vehicles, each approximately 175 125 85 mm with magnetic wheels that enable them to inspect industrial structures such as storage tanks, chimneys and large diameter pipe work. The robots carry one of a number of payloads including a two channel MFL sensor, a 5 MHz dry coupled UT thickness wheel probe and a machine vision camera that images the surface. The system creates an NDE map of the structure overlaying results onto a 3D model in real time. The authors provide an overview of the robot design, data fusion algorithms (positioning and NDE) and visualization software.

Dobie, Gordon; Summan, Rahul; MacLeod, Charles; Pierce, Gareth; Galbraith, Walter [Centre for Ultrasonic Engineering, University of Strathclyde, 204 George Street, Glasgow, G1 1XW (United Kingdom)

2014-02-18T23:59:59.000Z

216

Completion processing for data communications instructions  

DOE Patents [OSTI]

Completion processing of data communications instructions in a distributed computing environment, including receiving, in an active messaging interface (`AMI`) data communications instructions, at least one instruction specifying a callback function; injecting into an injection FIFO buffer of a data communication adapter, an injection descriptor, each slot in the injection FIFO buffer having a corresponding slot in a pending callback list; listing in the pending callback list any callback function specified by an instruction, incrementing a pending callback counter for each listed callback function; transferring payload data as per each injection descriptor, incrementing a transfer counter upon completion of each transfer; determining from counter values whether the pending callback list presently includes callback functions whose data transfers have been completed; calling by the AMI any such callback functions from the pending callback list, decrementing the pending callback counter for each callback function called.

Blocksome, Michael A; Kumar, Sameer; Parker, Jeffrey J

2014-05-20T23:59:59.000Z

217

Solar sail propulsion: enabling new capabilities for heliophysics  

E-Print Network [OSTI]

Solar sails can play a critical role in enabling solar and heliophysics missions. Solar sail technology within NASA is currently at 80% of TRL-6, suitable for an in-flight technology demonstration. It is conceivable that an initial demonstration could carry scientific payloads that, depending on the type of mission, are commensurate with the goals of the three study panels of the 2010 Heliophysics Survey. Follow-on solar sail missions, leveraging advances in solar sail technology to support Heliophysics Survey goals, would then be feasible. This white paper reports on a sampling of missions enabled by solar sails, the current state of the technology, and what funding is required to advance the current state of technology such that solar sails can enable these missions.

Johnson, L; Alhorn, D; Heaton, A; Vansant, T; Campbell, B; Pappa, R; Keats, W; Liewer, P C; Alexander, D; Ayon, J; Wawrzyniak, G; Burton, R; Carroll, D; Matloff, G; Kezerashvili, R Ya

2010-01-01T23:59:59.000Z

218

Status of Magnetic Nozzle and Plasma Detachment Experiment  

SciTech Connect (OSTI)

High power plasma propulsion can move large payloads for orbit transfer, lunar missions, and beyond with large savings in fuel consumption owing to the high specific impulse. At high power, lifetime of the thruster becomes an issue. Electrodeless devices with magnetically guided plasma offer the advantage of long life since magnetic fields confine the plasma radially and keep it from impacting the material surfaces. For decades, concerns have been raised about the plasma remaining attached to the magnetic field and returning to the vehicle along the closed magnetic field lines. Recent analysis suggests that this may not be an issue if the magnetic field is properly shaped in the nozzle region and the plasma has sufficient energy density to stretch the magnetic field downstream. An experiment is being performed to test the theory regarding the MHD detachment scenario. The status of that experiment will be discussed in this paper.

Chavers, D. Gregory; Dobson, Chris; Jones, Jonathan; Lee, Michael; Martin, Adam; Gregory, Judith; Cecil, Jim [Propulsion Research Center, MSFC NASA, Huntsville, AL 35812 (United States); Bengtson, Roger D.; Breizman, Boris; Arefiev, Alexey [Department of Physics, University of Texas at Austin, TX 78712 (United States); Institute of Fusion Studies, University of Texas at Austin, TX 78712 (United States); Chang-Diaz, Franklin; Squire, Jared; Glover, Tim; McCaskill, Greg [Ad Astra Rocket Company, 2101 NASA Parkway, Houston, TX 77058 (United States); Cassibry, Jason; Li Zhongmin [University of Alabama in Huntsville, Huntsville, AL 35899 (United States)

2006-01-20T23:59:59.000Z

219

Capacitance probe for detection of anomalies in non-metallic plastic pipe  

DOE Patents [OSTI]

The disclosure relates to analysis of materials using a capacitive sensor to detect anomalies through comparison of measured capacitances. The capacitive sensor is used in conjunction with a capacitance measurement device, a location device, and a processor in order to generate a capacitance versus location output which may be inspected for the detection and localization of anomalies within the material under test. The components may be carried as payload on an inspection vehicle which may traverse through a pipe interior, allowing evaluation of nonmetallic or plastic pipes when the piping exterior is not accessible. In an embodiment, supporting components are solid-state devices powered by a low voltage on-board power supply, providing for use in environments where voltage levels may be restricted.

Mathur, Mahendra P. (Pittsburgh, PA); Spenik, James L. (Morgantown, WV); Condon, Christopher M. (Morgantown, WV); Anderson, Rodney (Grafton, WV); Driscoll, Daniel J. (Morgantown, WV); Fincham, Jr., William L. (Fairmont, WV); Monazam, Esmail R. (Morgantown, WV)

2010-11-23T23:59:59.000Z

220

RH Packaging Operations Manual  

SciTech Connect (OSTI)

This procedure provides operating instructions for the RH-TRU 72-B Road Cask, Waste Shipping Package. In this document, ''Packaging'' refers to the assembly of components necessary to ensure compliance with the packaging requirements (not loaded with a payload). ''Package'' refers to a Type B packaging that, with its radioactive contents, is designed to retain the integrity of its containment and shielding when subject to the normal conditions of transport and hypothetical accident test conditions set forth in 10 CFR Part 71. Loading of the RH 72-B cask can be done two ways, on the RH cask trailer in the vertical position or by removing the cask from the trailer and loading it in a facility designed for remote-handling (RH). Before loading the 72-B cask, loading procedures and changes to the loading procedures for the 72-B cask must be sent to CBFO at sitedocuments@wipp.ws for approval.

Washington TRU Solutions LLC

2003-09-17T23:59:59.000Z

Note: This page contains sample records for the topic "ur3 ur4 payload" from the National Library of EnergyBeta (NLEBeta).
While these samples are representative of the content of NLEBeta,
they are not comprehensive nor are they the most current set.
We encourage you to perform a real-time search of NLEBeta
to obtain the most current and comprehensive results.


221

Application of advanced composites for efficient on-board storage of fuel in natural gas vehicles  

SciTech Connect (OSTI)

The following outlines the performance requirements for high pressure containers for on-board storage of fuel in Natural Gas Vehicles. The construction of state-of-the-art carbon-fiber reinforced all-composite cylinders is described and the validation testing and key advantages are discussed. Carbon-fiber reinforced advanced composite technology offers a number of key advantages to the NGV industry, by providing: improved range, including up to 30% more fuel storage for a given storage envelope and up to 300% more fuel storage for a given weight allowance; life-cycle cost advantages, including savings in non-recurring costs (installation), savings in recurring costs (fuel and maintenance), and increased revenues from more passengers/payload; and uncompromising safety, namely, superior resistance to degradation from fatigue or stress rupture and inherent resistance to corrosion; proven toughness/impact resistance.

Sirosh, S.N. [EDO Canada Ltd., Calgary, Alberta (Canada)

1995-11-01T23:59:59.000Z

222

Main chain acid-degradable polymers for the delivery of bioactive materials  

DOE Patents [OSTI]

Novel main chain acid degradable polymer backbones and drug delivery systems comprised of materials capable of delivering bioactive materials to cells for use as vaccines or other therapeutic agents are described. The polymers are synthesized using monomers that contain acid-degradable linkages cleavable under mild acidic conditions. The main chain of the resulting polymers readily degrade into many small molecules at low pH, but remain relatively stable and intact at physiological pH. The new materials have the common characteristic of being able to degrade by acid hydrolysis under conditions commonly found within the endosomal or lysosomal compartments of cells thereby releasing their payload within the cell. The materials can also be used for the delivery of therapeutics to the acidic regions of tumors and other sites of inflammation.

Frechet, Jean M. J. (Oakland, CA); Standley, Stephany M. (Evanston, IL); Jain, Rachna (Milpitas, CA); Lee, Cameron C. (Cambridge, MA)

2012-03-20T23:59:59.000Z

223

Mission analysis for hybrid thermionic nuclear reactor LEO-to-GEO transfer applications  

SciTech Connect (OSTI)

This paper details the results of mission analyses concerning a hybrid STAR-C based system, which is based on a safe solid fuel form for high-temperature reactor core operation and a rugged planar thermionic energy converter for long-life steady-state electric power production. Hybrid power/propulsion system concepts are shown to offer superior performance capabilities for Low-Earth-Orbit (LEO) to Geosynchronous-Earth-Orbit (GEO) orbital transfer applications over chemical propulsion systems. A key feature of the hybrid power/propulsion system is that the propulsion system uses the on-board payload power system. Mission results for hybrid concepts using Nuclear Thermal Propulsion (NTP), Nuclear Electric Propulsion (NEP), and combination of NTP and NEP are discussed.

Widman, F.W. Jr.; North, D.M. (Rockwell International/Rocketdyne Division, 6633 Canoga Avenue, Canoga Park, California 91303 (United States)); Choong, P.T.; Teofilo, V.L. (Lockheed Missiles and Space Company, Inc., 1111 Lockheed Way, Synnyvale, California 94088 (United States))

1993-01-10T23:59:59.000Z

224

Final report on evaluation of cyclocraft support of oil and gas operations in wetland areas  

SciTech Connect (OSTI)

The cyclocraft is a proven hybrid aircraft, capable of VTOL, lifting heavy and bulky loads, highly controllable, having high safety characteristics and low operating costs. Mission Research Corporation (MRC), under Department of Energy sponsorship, is evaluating the potential use of cyclocraft in the transport of drill rigs, mud, pipes and other materials and equipment, in a cost effective and environmentally safe manner, to support oil and gas drilling, production, and transportation operations in wetland areas. Based upon the results of an earlier parametric study, a cyclocraft design, having a payload capacity of 45 tons and designated H.1 Cyclocraft, was selected for further study, including the preparation of a preliminary design and a development plan, and the determination of operating costs. This report contains all of the results derived from the program to evaluate the use of cyclocraft in the support of oil and gas drilling and production operations in wetland areas.

Eggington, W.J.; Stevens, P.M.; John, C.J.; Harder, B.J.; Lindstedt, D.M.

1994-10-01T23:59:59.000Z

225

Research of advanced techniques for x-ray detectors and telescopes with applications to rockets and the LAMAR facility. Semiannual Report, 1 Jul. 1984 - 30 Jun. 1985  

SciTech Connect (OSTI)

A program for the development of high throughput instrumentation for x-ray astronomy based upon focusing optics is being carried out by the Smithsonian Astrophysical Observatory. The instrumentation is applicable to investigations requiring large area focusing optics for direct imaging or dispersive spectroscopy. The long range goals of this program are the development of telescopes and gratings for future major X-ray astronomy facilities, including additions to the LAMAR OSS-2/SHEAL experiment after the initial flights. Tests of the devices and their more immediate utilization in scientific investigations can be carried out with SPARTAN payloads deployed and retrieved by the Space Shuttle. However, the present backlog of approved SPARTAN missions is longer than the three-year duration of the program described in this program. Laboratory studies and breadboarding of instrumentation are discussed.

Gorenstein, P.

1985-08-01T23:59:59.000Z

226

PAMELA's Measurements of Magnetospheric Effects on High Energy Solar Particles  

E-Print Network [OSTI]

The nature of particle acceleration at the Sun, whether through flare reconnection processes or through shocks driven by coronal mass ejections (CMEs), is still under scrutiny despite decades of research. The measured properties of solar energetic particles (SEPs) have long been modeled in different particle-acceleration scenarios. The challenge has been to disentangle to the effects of transport from those of acceleration. The Payload for Antimatter Matter Exploration and Light-nuclei Astrophysics (PAMELA) instrument, enables unique observations of SEPs including composition and the angular distribution of the particles about the magnetic field, i.e. pitch angle distribution, over a broad energy range (>80 MeV) -- bridging a critical gap between space-based measurements and ground-based. We present high-energy SEP data from PAMELA acquired during the 2012 May 17 SEP event. These data exhibit differential anisotropies and thus transport features over the instrument rigidity range. SEP protons exhibit two dist...

Adriani, O; Bazilevskaya, G A; Bellotti, R; Boezio, M; Bogomolov, E A; Bongi, M; Bonvicini, V; Bottai, S; Bravar, U; Bruno, A; Cafagna, F; Campana, D; Carbone, R; Carlson, P; Casolino, M; Castellini, G; Christian, E C; De Donato, C; de Nolfo, G A; De Santis, C; De Simone, N; Di Felice, V; Formato, V; Galper, A M; Karelin, A V; Koldashov, S V; Koldobskiy, S; Krutkov, S Y; Kvashnin, A N; Lee, M; Leonov, A; Malakhov, V; Marcelli, L; Martucci, M; Mayorov, A G; Menn, W; Merg, M; Mikhailov, V V; Mocchiutti, E; Monaco, A; Mori, N; Munini, R; Osteria, G; Palma, F; Panico, B; Papini, P; Pearce, M; Picozza, P; Ricci, M; Ricciarini, S B; Ryan, J M; Sarkar, R; Scotti, V; Simon, M; Sparvoli, R; Spillantini, P; Stochaj, S; Stozhkov, Y I; Thakur, N; Vacchi, A; Vannuccini, E; Vasilyev, G I; Voronov, S A; Yurkin, Y T; Zampa, G; Zampa, N

2015-01-01T23:59:59.000Z

227

Implementation of Revision 19 of the TRUPACT-II Safety Analysis Report at Rocky Flats Environmental Technology Site  

SciTech Connect (OSTI)

The U.S. Nuclear Regulatory Commission on July 27, 2001 approved Revision 19 of the TRUPACT-II Safety Analysis Report (SAR) and the associated TRUPACT-II Authorized Methods for Payload Control (TRAMPAC). Key initiatives in Revision 19 included matrix depletion, unlimited mixing of shipping categories, a flammability assessment methodology, and an alternative methodology for the determination of flammable gas generation rates. All U.S. Department of Energy (DOE) sites shipping transuranic (TRU) waste to the Waste Isolation Pilot Plant (WIPP) were required to implement Revision 19 methodology into their characterization and waste transportation programs by May 20, 2002. An implementation process was demonstrated by the Rocky Flats Environmental Technology Site (RFETS) in Golden, Colorado. The three-part process used by RFETS included revision of the site-specific TRAMPAC, an evaluation of the contact-handled TRU waste inventory against the regulations in Revision 19, and design and development of software to facilitate future inventory analyses.

D'Amico, E.; O'Leary, J.; Bell, S.; Djordjevic, S.; Givens, C,; Shokes, T.; Thompson, S.; Stahl, S.

2003-02-25T23:59:59.000Z

228

Quality Assurance Program Plan for TRUPACT-II Gas Generation Test Program  

SciTech Connect (OSTI)

The Gas Generation Test Program (GGTP), referred to as the Program, is designed to establish the concentration of flammable gases and/or gas generation rates in a test category waste container intended for shipment in the Transuranic Package Transporter-II (TRUPACT-II). The phrase "gas generationtesting" shall refer to any activity that establishes the flammable gas concentration or the flammable gas generation rate. This includes, but is not limited to, measurements performed directly on waste containers or during tests performed on waste containers. This Quality Assurance Program Plan (QAPP) documents the quality assurance (QA) and quality control (QC) requirements that apply to the Program. The TRUPACT-II requirements and technical bases for allowable flammable gas concentration and gas generation rates are described in the TRUPACT-II Authorized Methods for Payload Control (TRAMPAC).

Carlsbad Field Office

2002-03-01T23:59:59.000Z

229

SAFETY ANALYSIS REPORT FOR PACKAGING, MODEL 9977, ADDENDUM 3, JUSTIFICATION FOR SMALL GRAM QUANTITY CONTENTS  

SciTech Connect (OSTI)

This Addendum establishes a new family of content envelopes consisting of small quantities of radioactive materials. These content envelopes and specific packing configurations are shown to be subcritical. However, the dose rates of some payloads must be measured and shown to comply with applicable radiation limits. Authorization for shipment of the content envelop requires acceptance of this Addendum by the DOE-HQ certifying official as a supplement to the 9977 SARP Revision 2 and DOE-HQ?s subsequent revision of the CoC Revision 10 (which is based on SARP Addendum 2 and SARP Addendum 4) to authorize the additional content envelope. The Small Gram Quantity Content Envelopes and packing configurations will be incorporated in the next revision of the 9977 SARP.

Abramczyk, G.

2011-10-31T23:59:59.000Z

230

Comparison of M46 broad-band visible data with ELF data from the Sprites `96 campaign  

SciTech Connect (OSTI)

Lightning data, recorded with satellite optical sensors, are compared with extremely low frequency (ELF) and Schumann resonance (SR) data from the Sprites `96 Campaign. The satellite data are broad-band visible events recorded by the M46 satellite payload. Full width at half maximum and optical tail durations from the satellite data are compared with ELF slow tail features and Schumann resonance spectral color. In addition, continuing current estimates were computed for several positive cloud-to-ground (PCG) strokes. These estimates were derived using relative optical intensities from the satellite data and a peak current measurement from National Lightning Detection Network (NLDN) data. This assessment of M46 lightning data supports correlations between visible and ELF signatures. More data must be studied for compelling proof.

Mitchell, E.A.

1997-10-01T23:59:59.000Z

231

A Comet on Earth: Results from the Stardust Mission  

SciTech Connect (OSTI)

The Stardust mission returned from a 6-year voyage in January of 2006. During the mission it swept through the tail of comet Wild 2 (pronounced Vilt), collecting the microscopic particles streaming from it. These particles were collected in a very low density material called aerogel. The satellite then took 2 years to return to Earth. The payload, jettisoned from the satellite, re-entered the atmosphere and gently landed in the Utah desert. Since January researchers have started the process of extracting the particles from the aerogel and using an extensive array of techniques to measure such things as elemental and isotopic abundance, mineralogy and petrology. We at SLAC have been using an X-ray Microprobe to determine the amount of different elements that are present in these particles. Please join us for a preliminary look at the results of the Stardust mission.

Brennan, Sean

2006-08-29T23:59:59.000Z

232

FORTE spacecraft vibration mitigation. Final report  

SciTech Connect (OSTI)

This report documents work that was performed by CSA Engineering, Inc., for Los Alamos National Laboratory (LANL), to reduce vibrations of the FORTE spacecraft by retrofitting damped structural components into the spacecraft structure. The technical objective of the work was reduction of response at the location of payload components when the structure is subjected to the dynamic loading associated with launch and proto-qualification testing. FORTE is a small satellite that will be placed in orbit in 1996. The structure weighs approximately 425 lb, and is roughly 80 inches high and 40 inches in diameter. It was developed and built by LANL in conjunction with Sandia National Laboratories Albuquerque for the United States Department of Energy. The FORTE primary structure was fabricated primarily with graphite epoxy, using aluminum honeycomb core material for equipment decks and solar panel substrates. Equipment decks were bonded and bolted through aluminum mounting blocks to adjoining structure.

Maly, J.R.

1996-02-01T23:59:59.000Z

233

Unmanned Aerial Vehicle (UAV) Dynamic-Tracking Directional Wireless Antennas for Low Powered Applications that Require Reliable Extended Range Operations in Time Critical Scenarios  

SciTech Connect (OSTI)

The proven value of DOD Unmanned Aerial Vehicles (UAVs) will ultimately transition to National and Homeland Security missions that require real-time aerial surveillance, situation awareness, force protection, and sensor placement. Public services first responders who routinely risk personal safety to assess and report a situation for emergency actions will likely be the first to benefit from these new unmanned technologies. Packable or Portable small class UAVs will be particularly useful to the first responder. They require the least amount of training, no fixed infrastructure, and are capable of being launched and recovered from the point of emergency. All UAVs require wireless communication technologies for real- time applications. Typically on a small UAV, a low bandwidth telemetry link is required for command and control (C2), and systems health monitoring. If the UAV is equipped with a real-time Electro-Optical or Infrared (EO/Ir) video camera payload, a dedicated high bandwidth analog/digital link is usually required for reliable high-resolution imagery. In most cases, both the wireless telemetry and real-time video links will be integrated into the UAV with unity gain omni-directional antennas. With limited on-board power and payload capacity, a small UAV will be limited with the amount of radio-frequency (RF) energy it transmits to the users. Therefore, packable and portable UAVs will have limited useful operational ranges for first responders. This paper will discuss the limitations of small UAV wireless communications. The discussion will present an approach of utilizing a dynamic ground based real-time tracking high gain directional antenna to provide extend range stand-off operation, potential RF channel reuse, and assured telemetry and data communications from low-powered UAV deployed wireless assets.

Scott G. Bauer; Matthew O. Anderson; James R. Hanneman

2005-10-01T23:59:59.000Z

234

DUAL-MODE PROPULSION SYSTEM ENABLING CUBESAT EXPLORATION OF THE SOLAR SYSTEM NASA Innovative Advanced Concepts (NIAC) Phase I Final Report  

SciTech Connect (OSTI)

It is apparent the cost of planetary exploration is rising as mission budgets declining. Currently small scientific beds geared to performing limited tasks are being developed and launched into low earth orbit (LEO) in the form of small-scale satellite units, i.e., CubeSats. These micro- and nano-satellites are gaining popularity among the university and science communities due to their relatively low cost and design flexibility. To date these small units have been limited to performing tasks in LEO utilizing solar-based power. If a reasonable propulsion system could be developed, these CubeSat platforms could perform exploration of various extra-terrestrial bodies within the solar system engaging a broader range of researchers. Additionally, being mindful of mass, smaller cheaper launch vehicles (~1,000 kgs to LEO) can be targeted. This, in effect, allows for beneficial explora-tion to be conducted within limited budgets. Researchers at the Center for Space Nuclear Re-search (CSNR) are proposing a low mass, radioisotope-based, dual-mode propulsion system capable of extending the exploration realm of these CubeSats out of LEO. The proposed radioisotope-based system would leverage the high specific energies [J/kg] associated with radioisotope materials and enhance their inherent low specific powers [W/g]. This is accomplished by accumulating thermal energy from nuclear decay within a central core over time. This allows for significant amounts of power to be transferred to a flowing gas over short periods of time. In the proposed configuration the stored energy can be utilized in two ways: (1) with direct propellant injection to the core, the energy can be converted into thrust through the use of a converging-diverging nozzle and (2) by flowing a working fluid through the core and subsequent Brayton engine, energy within the core can be converted to electrical energy. The first scenario achieves moderate ranges of thrust, but at a higher Isp than traditional chemical-based systems. The second scenario allows for the production of electrical power, which is then available for electric-based propulsion. Additionally, once at location the production of electrical power can be dedicated to the payloads communication system for data transfer. Ultimately, the proposed dual-mode propulsion platform capitalizes on the benefits of two types of propulsion methods the thrust of thermal propulsion ideal for quick orbital maneuvers and the specific impulse of electric propulsion ideal for efficient inter-planetary travel. Previous versions of this RTR-based concept have been studied for various applications [NETS 1-3]. The current version of this concept is being matured through a NASA Innovative Advanced Concepts (NIAC) Phase I grant, awarded for FY 2014. In this study the RTR concept is being developed to deliver a 6U CubeSat payload to the orbit of the Saturnian moon - Enceladus. Additionally, this study will develop an entire mission architecture for Enceladus targeting a total allowable launch mass of 1,000 kg.

Nathan Jerred; Troy Howe; Adarsh Rajguru; Dr. Steven Howe

2014-06-01T23:59:59.000Z

235

TRUPACT-II Operating and Maintenance Instructions  

SciTech Connect (OSTI)

The purpose of this document is to provide the technical requirements for preparation for use, operation, inspection, and maintenance of a Transuranic Package Transporter Model II (TRUPACT-II) Shipping Package and directly related components. This document complies with the minimum requirements as specified in the TRUPACT-II Safety Analysis Report for Packaging (SARP) and Nuclear Regulatory Commission (NRC) Certificate of Compliance (C of C) 9218. In the event there is a conflict between this document and the TRUPACT-II SARP, the TRUPACT-II SARP shall govern. TRUPACT-II C of C number 9218 states, ''... each package must be prepared for shipment and operated in accordance with the procedures described in Chapter 7.0, Operating Procedures, of the application.'' It further states, ''... each package must be tested and maintained in accordance with the procedures described in Chapter 8.0, Acceptance Tests and Maintenance Program of the application.'' Chapter 9 of the TRUPACT-II SARP charges the Westinghouse Electric Corporation Waste Isolation Division (WID) with assuring that the TRUPACT-II is used in accordance with the requirements of the C of C. To meet this requirement and verify consistency of operations when loading and unloading the TRUPACT-II on the trailer, placing a payload in the packaging, unloading the payload from the packaging, or performing maintenance, the U.S. Department of Energy Carlsbad Area Office (U.S. DOE/CAO) finds it necessary to implement the changes that follow. This TRUPACT-II maintenance document represents a change to previous philosophy regarding site specific procedures for the use of the TRUPACT-II. This document details the instructions to be followed to consistently operate and maintain the TRUPACT-II. The intent of these instructions is to ensure that all users of the TRUPACT-II follow the same or equivalent instructions. Users may achieve this intent by any of the following methods: (1) Utilizing these instructions as is, or (2) Attaching a site-specific cover page/letter to this document stating that these are the instructions to be used at their location, or (3) Sites may prepare their own document using the steps in this document word-for-word, in-sequence, including Notes and Cautions. Site specific information may be included as deemed necessary. Submit the document to WID National TRU Programs for approval. Any revision made subsequent to WID TRU Program's approval shall be reviewed and approved by WID TRU Programs. A copy of the approval letter from WID National TRU Programs should be available for audit purposes. Users shall develop site-specific procedures addressing leak testing, preoperational activities, quality assurance, hoisting and rigging, and radiation health physics to be used in conjunction with the instructions contained in this document. Users desiring to recommend changes to this document may submit their recommendations to the WID National TRU Programs for evaluation. If approved, the change(s) will be incorporated into this document for use by all TRUPACT-II users. User sites will be audited to this document to ensure compliance within one year from the effective date of this revision. This document discusses operating instructions, required inspections and maintenance for the following: TRUPACT-II packaging, and Miscellaneous packaging, special tools, and equipment. Packaging and payload handling equipment and transport trailers have been specifically designed for use with the TRUPACT-II Packaging. This document discusses the required instructions for use of the following equipment in conjunction with the TRUPACT-II Packaging: TRUPACT-II Mobile Loading Unit (MLU), Adjustable Center-of-Gravity Lift Fixture (ACGLF), and TRUPACT-II Transport Trailer. Attachment E contains the various TRUPACT-II packaging interface control drawings, leak-test and vent-port tool drawings, ACGLF drawings, and tie-down drawings that identify the various system components.

Westinghouse Electric Corporation, Waste Isolation Division

1999-12-31T23:59:59.000Z

236

NEP for a Kuiper Belt Object Rendezvous Mission  

SciTech Connect (OSTI)

Kuiper Belt Objects (KBOs) are a recently-discovered set of solar system bodies which lie at about the orbit of Pluto (40 AU) out to about 100 astronomical units (AU). There are estimated to be about 100,000 KBOS with a diameter greater than 100 km. KBOS are postulated to be composed of the pristine material which formed our solar system and may even have organic materials in them. A detailed study of KBO size, orbit distribution, structure, and surface composition could shed light on the origins of the solar system and perhaps even on the origin of life in our solar system. A rendezvous mission including a lander would be needed to perform chemical analysis of the surface and sub-surface composition of KBOS. These requirements set the size of the science probe at around a ton. Mission analyses show that a fission-powered system with an electric thruster could rendezvous at 40 AU in about 13.0 years with a total {Delta}V of 46 krnk. It would deliver a 1000-kg science payload while providing ample onboard power for relaying data back to earth. The launch mass of the entire system (power, thrusters, propellant, navigation, communication, structure, science payload, etc.) would be 7984 kg if it were placed into an earth-escape trajectory (C=O). Alternatively, the system could be placed into a 700-km earth orbit with more propellant,yielding a total mass in LEO of 8618 kg, and then spiral out of earth orbit to arrive at the KBO in 14.3 years. To achieve this performance, a fission power system with 100 kW of electrical power and a total mass (reactor, shield, conversion, and radiator) of about 2350 kg. Three possible configurations are proposed: (1) a UZrH-fueled, NaK-cooled reactor with a steam Rankine conversion system, (2) a UN-fueled gas-cooled reactor with a recuperated Brayton conversion system, and (3) a UN-fueled heatpipe-cooled reactor with a recuperated Brayton conversion system. (Boiling and condensation in the Rankine system is a technical risk at present.) All three of these systems have the potential to meet the weight requirement for the trip and to be built in the near term.

HOUTS,MICHAEL G.; LENARD,ROGER X.; LIPINSKI,RONALD J.; PATTON,BRUCE; POSTON,DAVID I.; WRIGHT,STEVEN A.

1999-11-03T23:59:59.000Z

237

Shielding and criticality analyses of phase I reference truck and rail cask designs for spent nuclear fuel  

SciTech Connect (OSTI)

Results are presented herein to determine the adequacy with respect to shielding regulations of reference designs for a truck cask containing 2 PWR or 5 BWR assemblies of standard burnup (45 GWd/MTU for PWR, 40 GWd/MTU for BWR) and 1 PWR assembly with extended burnup (55 GWd/MTU). The study also includes reference and modified rail cask designs with projected payloads of 8, 10, or 12 PWR assemblies. The burnup/age trends are analyzed in one dimension for both Pb and depleted uranium (DU) gamma-ray shields. The results of the two-dimensional shielding analysis uphold the one-dimensional results as being an appropriate means of studying the burnup/age trends for the truck cask. These results show that the reference design for the Pb-shield truck cask is inadequate for all cases considered, while the DU-shield truck cask is capable of carrying the desired payloads. The one-dimensional shielding analysis results for the reference Pb and DU rail casks indicate substantial margins exist in the side doses for reasonable burnup/age combinations. For a Pb-cask configuration, margins exist primarily for long-cooled (15 years) fuel. For the modified Pb and DU rail casks, the 2-m dose rates offer substantial margins below the regulatory limits for all burnup values considered provided the spent fuel has cooled for {>=}10 years. The modified Pb and DU casks yield essentially identical results and, hence, could be considered equivalent from a shielding perspective. The criticality analyses that were performed indicate that a truck basket can be designed to provide an adequate subcritical margin for 2 PWR assemblies enriched to 5 wt%. While the 10- and 12- assembly rail cask designs are very close to the regulatory limit of 0.95 for k{sub eff}, after accounting for a 0.01 {Delta}k bias and 2 standard deviations, the limit is exceeded by about 3%. It is believed that a combination of decreased enrichments and/or increased water gaps should allow these baskets to be acceptable.

Broadhead, B.L.; Childs, R.L.; Parks, C.V.

1996-03-01T23:59:59.000Z

238

Spent Nuclear Fuel (SNF) Project Cold Vacuum Drying (CVD) Facility Operations Manual  

SciTech Connect (OSTI)

The mission of the Spent Nuclear Fuel (SNF) Project Cold Vacuum Drying Facility (CVDF) is to achieve the earliest possible removal of free water from Multi-Canister Overpacks (MCOs). The MCOs contain metallic uranium SNF that have been removed from the 100K Area fuel storage water basins (i.e., the K East and K West Basins) at the US. Department of Energy Hanford Site in Southeastern Washington state. Removal of free water is necessary to halt water-induced corrosion of exposed uranium surfaces and to allow the MCOs and their SNF payloads to be safely transported to the Hanford Site 200 East Area and stored within the SNF Project Canister Storage Building (CSB). The CVDF is located within a few hundred yards of the basins, southwest of the 165KW Power Control Building and the 105KW Reactor Building. The site area required for the facility and vehicle circulation is approximately 2 acres. Access and egress is provided by the main entrance to the 100K inner area using existing roadways. The CVDF will remove free. water from the MCOs to reduce the potential for continued fuel-water corrosion reactions. The cold vacuum drying process involves the draining of bulk water from the MCO and subsequent vacuum drying. The MCO will be evacuated to a pressure of 8 torr or less and backfilled with an inert gas (helium). The MCO will be sealed, leak tested, and then transported to the CSB within a sealed shipping cask. (The MCO remains within the same shipping Cask from the time it enters the basin to receive its SNF payload until it is removed from the Cask by the CSB MCO handling machine.) The CVDF subproject acquired the required process systems, supporting equipment, and facilities. The cold vacuum drying operations result in an MCO containing dried fuel that is prepared for shipment to the CSB by the Cask transportation system. The CVDF subproject also provides equipment to dispose of solid wastes generated by the cold vacuum drying process and transfer process water removed from the MCO back to the K Basins.

IRWIN, J.J.

2000-11-18T23:59:59.000Z

239

Feasibility Study for an Autonomous UAV -Magnetometer System -- Final Report on SERDP SEED 1509:2206  

SciTech Connect (OSTI)

Large areas across the United States are potentially contaminated with UXO, with some ranges encompassing tens to hundreds of thousands of acres. Technologies are needed which will allow for cost effective wide area scanning with 1) near 100 % coverage and 2) near 100 % detection of subsurface ordnance or features indicative of subsurface ordnance. The current approach to wide area scanning is a multi-level one, in which medium altitude fixed wing optical imaging is used for an initial site assessment. This assessment is followed with low altitude manned helicopter based magnetometry followed by surface investigations using either towed geophysical sensor arrays or man portable sensors. In order to be effective for small UXO detection, the sensing altitude for magnetic site investigations needs to be on the order of 1 3 meters. These altitude requirements means that manned helicopter surveys will generally only be feasible in large, open and relatively flat terrains. While such surveys are effective in mapping large areas relatively fast there are substantial mobilization/demobilization, staffing and equipment costs associated with these surveys (resulting in costs of approximately $100-$150/acre). Surface towed arrays provide high resolution maps but have other limitations, e.g. in their ability to navigate rough terrain effectively. Thus, other systems are needed allowing for effective data collection. An UAV (Unmanned Aerial Vehicle) magnetometer platform is an obvious alternative. The motivation behind such a system is that it would be safer for the operators, cheaper in initial and O&M costs, and more effective in terms of site characterization. However, while UAV data acquisition from fixed wing platforms for large (> 200 feet) stand off distances is relatively straight forward, a host of challenges exist for low stand-off distance (~ 6 feet) UAV geophysical data acquisition. The objective of SERDP SEED 1509:2006 was to identify the primary challenges associated with a low stand off distance autonomous UAV magnetometer platform and to investigate whether these challenges can be resolved successfully such that a successful UAV magnetometer platform can be constructed. The primary challenges which were identified and investigated include: 1. The feasibility of assembling a payload package which integrates magnetometers, accurate positioning systems (DGPS, height above ground measurement), obstacle avoidance systems, power infrastructure, communications and data storage as well as auxiliary flight controls 2. The availability of commercial UAV platforms with autonomous flight capability which can accommodate this payload package 3. The feasibility of integrating obstacle avoidance controls in UAV platform control 4. The feasibility of collecting high quality magnetic data in the vicinity of an UAV.

Roelof Versteeg; Mark McKay; Matt Anderson; Ross Johnson; Bob Selfridge; Jay Bennett

2007-09-01T23:59:59.000Z

240

Unmanned airships for near earth remote sensing missions  

SciTech Connect (OSTI)

In recent years the study of Earth processes has increased significantly. Conventional aircraft have been employed to a large extent in gathering much of this information. However, with this expansion of research has come the need to investigate and measure phenomena that occur beyond the performance capabilities of conventional aircraft. Where long dwell times or observations at very low attitudes are required there are few platforms that can operate safely, efficiently, and cost-effectively. One type of aircraft that meets all three parameters is the unmanned, autonomously operated airship. The UAV airship is smaller than manned airships but has similar performance characteristics. It`s low speed stability permits high resolution observations and provides a low vibration environment for motion sensitive instruments. Maximum airspeed is usually 30mph to 35mph and endurance can be as high as 36 hours. With scientific payload capacities of 100 kilos and more, the UAV airship offers a unique opportunity for carrying significant instrument loads for protracted periods at the air/surface interface. The US Army has operated UAV airships for several years conducting border surveillance and monitoring, environmental surveys, and detection and mapping of unexploded ordinance. The technical details of UAV airships, their performance, and the potential of such platforms for more advanced research roles will be presented. 3 refs., 5 figs.

Hochstetler, R.D. [Research Adventures,Inc., Kensington, MD (United States)

1996-10-01T23:59:59.000Z

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241

Atmospheric Radiation Measurement Program facilities newsletter, January 2000  

SciTech Connect (OSTI)

The subject of this newsletter is the ARM unmanned aerospace vehicle program. The ARM Program's focus is on climate research, specifically research related to solar radiation and its interaction with clouds. The SGP CART site contains highly sophisticated surface instrumentation, but even these instruments cannot gather some crucial climate data from high in the atmosphere. The Department of Energy and the Department of Defense joined together to use a high-tech, high-altitude, long-endurance class of unmanned aircraft known as the unmanned aerospace vehicle (UAV). A UAV is a small, lightweight airplane that is controlled remotely from the ground. A pilot sits in a ground-based cockpit and flies the aircraft as if he were actually on board. The UAV can also fly completely on its own through the use of preprogrammed computer flight routines. The ARM UAV is fitted with payload instruments developed to make highly accurate measurements of atmospheric flux, radiance, and clouds. Using a UAV is beneficial to climate research in many ways. The UAV puts the instrumentation within the environment being studied and gives scientists direct measurements, in contrast to indirect measurements from satellites orbiting high above Earth. The data collected by UAVs can be used to verify and calibrate measurements and calculated values from satellites, therefore making satellite data more useful and valuable to researchers.

Sisterson, D.L.

2000-02-16T23:59:59.000Z

242

Solar-powered unmanned aerial vehicles  

SciTech Connect (OSTI)

An analysis was performed to determine the impact of various power system components and mission requirements on the size of solar-powered high altitude long endurance (HALE)-type aircraft. The HALE unmanned aerial vehicle (UAV) has good potential for use in many military and civil applications. The primary power system components considered in this study were photovoltaic (PV) modules for power generation and regenerative fuel cells for energy storage. The impact of relevant component performance on UAV size and capability were considered; including PV module efficiency and mass, power electronics efficiency, and fuel cell specific energy. Mission parameters such as time of year, flight altitude, flight latitude, and payload mass and power were also varied to determine impact on UAV size. The aircraft analysis method used determines the required aircraft wing aspect ratio, wing area, and total mass based on maximum endurance or minimum required power calculations. The results indicate that the capacity of the energy storage system employed, fuel cells in this analysis, greatly impacts aircraft size, whereas the impact of PV module efficiency and mass is much less important. It was concluded that an energy storage specific energy (total system) of 250--500 Whr/kg is required to enable most useful missions, and that PV cells with efficiencies greater than {approximately} 12% are suitable for use.

Reinhardt, K.C.; Lamp, T.R.; Geis, J.W. [Wright Lab., Wright Patterson AFB, OH (United States). Aero Propulsion and Power Directorate; Colozza, A.J. [NYMA Corp., Brookpark, OH (United States). Aerospace Technology Development

1996-12-31T23:59:59.000Z

243

Power system requirements and selection for the space exploration initiative  

SciTech Connect (OSTI)

The Space Exploration Initiative (SEI) seeks to reestablish a US program of manned and unmanned space exploration. The President has called for a program which includes a space station element, a manned habitation of the moon, and a human exploration of Mars. The NASA Synthesis Group has developed four significantly different architectures for the SEI program. One key element of a space exploration effort is the power required to support the missions. The Power Speciality Team of the Synthesis Group was tasked with assessing and evaluating the power requirements and candidate power technologies for such missions. Inputs to the effort came from existing NASA studies as well as other governments agency inputs such as those from DOD and DOE. In addition, there were industry and university briefings and results of solicitations from the AIAA and the general public as part of the NASA outreach effort. Because of the variety of power needs in the SEI program, there will be a need for multiple power system technologies including solar, nuclear and electrochemical. Due to the high rocket masses required to propel payloads to the moon and beyond to Mars, there is great emphasis placed on the need for high power density and high energy density systems. Power system technology development work is needed results will determine the ultimate technology selections. 23 refs., 10 figs.

Biringer, K.L. (Sandia National Labs., Albuquerque, NM (United States)); Bartine, D.E. (Oak Ridge National Lab., TN (United States)); Buden, D. (Idaho National Engineering Lab., Idaho Falls, ID (United States)); Foreman, J. (Naval Research Lab., Washington, DC (United States)); Harrison, S. (Strategic Defense Initiative Organization, Washington, DC (United States))

1991-01-01T23:59:59.000Z

244

The Use of the Hanford Onsite Packaging and Transportation Safety Program to Meet Cleanup Milestones Under the Hanford Site Cleanup 2015 Vision and the American Recovery and Reinvestment Act of 2009 - 12403  

SciTech Connect (OSTI)

The Hanford Site presents unique challenges in meeting the U.S. Department of Energy Richland Operations Office (DOE-RL) 2015 Cleanup Vision. CH2M Hill Plateau Remediation Company (CHPRC), its subcontractors, and DOE-RL were challenged to retrieve, transport and remediate a wide range of waste materials. Through a collaborative effort by all Hanford Onsite Central Plateau Cleanup Team Members, disposition pathways for diverse and seemingly impossible to ship wastes were developed under a DOE Order 460.1C-compliant Hanford Onsite Transportation Safety Program. The team determined an effective method for transporting oversized compliant waste payloads to processing and disposition facilities. The use of the onsite TSD packaging authorizations proved to be vital to safely transporting these materials for processing and eventual final disposition. The American Recovery and Reinvestment Act of 2009 (ARRA) provided additional resources to expedite planning and execution of these important cleanup milestones. Through the innovative and creative use of the TSD, the Hanford Onsite Central Plateau Cleanup Team Members have developed and are executing an integrated project plan that enables the safe and compliant transport of a wide variety of difficult-to-transport waste items, accelerating previous cleanup schedules to meet cleanup milestones. (authors)

Lavender, John C. [CH2M HILL Plateau Remediation Company, Richland, WA 99354 (United States); Edwards, W. Scott [Areva Federal Services, Richland, WA 99354 (United States); Macbeth, Paul J.; Self, Richard J. [U.S. Department of Energy Richland Operations Office, Richland, WA 99352 (United States); West, Lori D. [Materials and Energy Corporation, Richland, WA 99354 (United States)

2012-07-01T23:59:59.000Z

245

Environmental study of the National Aerospace Plane. Final report, 1 December 1991-30 December 1992  

SciTech Connect (OSTI)

The overall objective of the United States (US) National Aero-Space Plane (NASP) Program is to develop hypersonic technologies required for future military and Civilian aerospace plane systems to reduce payload cost to orbit and provide for flexible-responsive space operations. If successful, the NASP Program will be the stimulus for developing a whole new class of airbreathing hypersonic aircraft powered by clean-burning scramjet engines using liquid hydrogen as the primary fuel. As part of this development, the potential to cause environmental impacts from these type of vehicles must be considered and analyzed. This process has been initiated using the NASP Program's proposed X-30 flight research vehicle and flight test program as a basis for analysis. Environmental issues addressed include noise and sonic booms, stratospheric ozone depletion, public health and safety, hazardous materials/waste, air quality, biological and cultural resources, geology and soils, and water use. Although this study is not yet complete, preliminary analysis has determined that the X-30 vehicle and flight test program would have minimal environmental impact.

Brown, C.; Wierzbanowski, T.; Reda, H.; Duecker, G.T.

1992-12-01T23:59:59.000Z

246

Opportunities to increase the productivity of spent fuel shipping casks in the United States  

SciTech Connect (OSTI)

Trends indicate that future transportation requirements for spent fuel will be different from those anticipated when the current generation of casks and vehicles was designed. Increased storage capacity at most reactors will increase the average post irradiation age of the spent fuel to be transported. A scenario is presented which shows the 18 casks currently available should be sufficient until approximately 1983. Beyond this time, it appears that an adequate transportation system can be maintained by acquiring, as needed, casks of current designs and new casks currently under development. Spent fuel transportation requirements in the post-1990 period can be met by a new generation of casks specifically designed to transport long-cooled fuel. In terms of the number of casks needed, productivity may be increased by 19% if rail cask turnaround time is reduced to 4 days from the current range of 6.5 to 8.5 days. Productivity defined as payloads per cask year could be increased 62% if the turnaround time for legal weight truck casks were reduced from 12 hours to 4 hours. On a similar basis, overweight truck casks show a 28% increase in productivity.

Winsor, G.H.; Faletti, D.W.; DeSteese, J.G.

1980-03-01T23:59:59.000Z

247

Spider Optimization: Probing the Systematics of a Large Scale B-Mode Experiment  

E-Print Network [OSTI]

Spider is a long-duration, balloon-borne polarimeter designed to measure large scale Cosmic Microwave Background (CMB) polarization with very high sensitivity and control of systematics. The instrument will map over half the sky with degree angular resolution in I, Q and U Stokes parameters, in four frequency bands from 96 to 275 GHz. Spider's ultimate goal is to detect the primordial gravity wave signal imprinted on the CMB B-mode polarization. One of the challenges in achieving this goal is the minimization of the contamination of B-modes by systematic effects. This paper explores a number of instrument systematics and observing strategies in order to optimize B-mode sensitivity. This is done by injecting realistic-amplitude, time-varying systematics in a set of simulated time-streams. Tests of the impact of detector noise characteristics, pointing jitter, payload pendulations, polarization angle offsets, beam systematics and receiver gain drifts are shown. Spider's default observing strategy is to spin continuously in azimuth, with polarization modulation achieved by either a rapidly spinning half-wave plate or a rapidly spinning gondola and a slowly stepped half-wave plate. Although the latter is more susceptible to systematics, results shown here indicate that either mode of operation can be used by Spider.

C. J. MacTavish; P. A. R. Ade; E. S. Battistelli; S. Benton; R. Bihary; J. J. Bock; J. R. Bond; J. Brevik; S. Bryan; C. R. Contaldi; B. P. Crill; O. Dor; L. Fissel; S. R. Golwala; M. Halpern; G. Hilton; W. Holmes; V. V. Hristov; K. Irwin; W. C. Jones; C. L. Kuo; A. E. Lange; C. Lawrie; T. G. Martin; P. Mason; T. E. Montroy; C. B. Netterfield; D. Riley; J. E. Ruhl; A. Trangsrud; C. Tucker; A. Turner; M. Viero; D. Wiebe

2007-10-01T23:59:59.000Z

248

The BEAR program NRL plasma physics instrumentation measurements  

SciTech Connect (OSTI)

The BEAR program was a joint effort to launch, and demonstrate the feasibility of operating, a 1 MeV 10 ma Neutral Particle Beam (NPB) accelerator from a space platform. The accelerator design and manufacture were the responsibility of Los Alamos National Lab (LANL); diagnostics associated with accelerator operation and beam-plasma effects were also to be undertaken by LANL and NRL. Payload Integration and Telemetry was provided by the Air Force Geophysical Lab (AFGL) and Northeastern University (NEU). Beam effects on the local plasma in addition to accelerator produced vehicle effects (e.g., charging) were the responsibility of NRL as outlined herein. The BEAR rocket was launched successfully during the early morning hours of July 13 from White Sands Missile Range, White Sands, N.M. The NRL contribution to this effort included three instrument packages designed to diagnose beam-plasma and vehicle-plasma interactions. The instruments included: (1) Langmuir probe (LP) design consisting of 4 separate sensors; (2) High voltage (HIV) Langmuir Probe designed to monitor vehicle charging through current polarity changes; and (3) Plasma Wave Receive (PWR) designed to characterize the plasma wave emissions covering a broad frequency range from near DC to 50 MHz.

Walker, D.N.; Baumback, M.M.; Haas, D.G.; Rodriguez, P.; Siefring, C.L.; Doggett, R.A. [Naval Research Lab., Washington, DC (United States)

1989-11-15T23:59:59.000Z

249

Uniform Fin Sizes versus Uniform Fin Root Temperatures for Unsymmetrically Obstructed Solar Probe RTGs  

SciTech Connect (OSTI)

Paper presented at the 26th IECEC, August 4-9, 1991 in Boston, MA. The Solar Probe will approach the sun within four solar radii or 0.02 AU. Because of that proximity, the spacecraft must be protected by a thermal shield. The protected umbra is a cone of 4 m diameter and 7.5 m height, and all temperature-sensitive flight components must fit within that cone. Therefore, the RTGs which power the Solar probe cannot be separated from each other and from other payload components by deploying them on long booms. They must be located near and thermally isolated from the spacecraft's paylod. This paper compares the performance of such variable-fin RTGs with that of uniform-fin RTGs. It derives the fin dimensions required for circumferential isothermicity, identifies a design that maximizes the RTGs specific power, and proves the practicality of that design option. However, detailed thermal and electrical analyses led to the somewhat surprising conclusion that (for a given thermal power) the non-uniform-fin design results in the same power output, at a higher maximum hot-junction temperature, as the standard uniform-fin design, despite the latter's nonuniform cold-junction temperatures. There are three copies in the file.

Schock, Alfred; Or, Chuen T; Noravian, Heros

1991-08-01T23:59:59.000Z

250

THERMAL EVALUATION OF ALTERNATE SHIPPING CASK FOR GTRI EXPERIMENTS  

SciTech Connect (OSTI)

The Global Threat Reduction Initiative (GTRI) has many experiments yet to be irradiated in support of the High Performance Research Reactor fuels development program. Most of the experiments will be irradiated in the Advanced Test Reactor (ATR) at Idaho National Laboratory (INL), then later shipped to the Hot Fuel Examination Facility (HFEF) located at the Materials and Fuels Complex for post irradiation examination. To date, the General Electric (GE)-2000 cask has been used to transport GTRI experiments between these facilities. However, the availability of the GE-2000 cask to support future GTRI experiments is at risk. In addition, the internal cavity of the GE-2000 cask is too short to accommodate shipping the larger GTRI experiments. Therefore, an alternate shipping capability is being pursued. The Battelle Energy Alliance, LLC, Research Reactor (BRR) cask has been determined to be the best alternative to the GE-2000 cask. An evaluation of the thermal performance of the BRR cask is necessary before proceeding with fabrication of the newly designed cask hardware and the development of handling, shipping, and transport procedures. This paper presents the results of the thermal evaluation of the BRR cask loaded with a representative set of fueled and non-fueled experiments. When analyzed with identical payloads, experiment temperatures were found to be lower with the BRR cask than with the GE-2000 cask. From a thermal standpoint, the BRR cask was found to be a suitable alternate to the GE-2000 cask.

Donna Post Guillen

2014-06-01T23:59:59.000Z

251

PAT-1 safety analysis report addendum.  

SciTech Connect (OSTI)

The Plutonium Air Transportable Package, Model PAT-1, is certified under Title 10, Code of Federal Regulations Part 71 by the U.S. Nuclear Regulatory Commission (NRC) per Certificate of Compliance (CoC) USA/0361B(U)F-96 (currently Revision 9). The purpose of this SAR Addendum is to incorporate plutonium (Pu) metal as a new payload for the PAT-1 package. The Pu metal is packed in an inner container (designated the T-Ampoule) that replaces the PC-1 inner container. The documentation and results from analysis contained in this addendum demonstrate that the replacement of the PC-1 and associated packaging material with the T-Ampoule and associated packaging with the addition of the plutonium metal content are not significant with respect to the design, operating characteristics, or safe performance of the containment system and prevention of criticality when the package is subjected to the tests specified in 10 CFR 71.71, 71.73 and 71.74.

Weiner, Ruth F.; Schmale, David T.; Kalan, Robert J.; Akin, Lili A.; Miller, David Russell; Knorovsky, Gerald Albert; Yoshimura, Richard Hiroyuki; Lopez, Carlos; Harding, David Cameron; Jones, Perry L.; Morrow, Charles W.

2010-09-01T23:59:59.000Z

252

Remotely deployable aerial inspection using tactile sensors  

SciTech Connect (OSTI)

For structural monitoring applications, the use of remotely deployable Non-Destructive Evaluation (NDE) inspection platforms offer many advantages, including improved accessibility, greater safety and reduced cost, when compared to traditional manual inspection techniques. The use of such platforms, previously reported by researchers at the University Strathclyde facilitates the potential for rapid scanning of large areas and volumes in hazardous locations. A common problem for both manual and remote deployment approaches lies in the intrinsic stand-off and surface coupling issues of typical NDE probes. The associated complications of these requirements are obviously significantly exacerbated when considering aerial based remote inspection and deployment, resulting in simple visual techniques being the preferred sensor payload. Researchers at Bristol Robotics Laboratory have developed biomimetic tactile sensors modelled on the facial whiskers (vibrissae) of animals such as rats and mice, with the latest sensors actively sweeping their tips across the surface in a back and forth motion. The current work reports on the design and performance of an aerial inspection platform and the suitability of tactile whisking sensors to aerial based surface monitoring applications.

MacLeod, C. N.; Cao, J.; Pierce, S. G.; Dobie, G.; Summan, R. [Centre for Ultrasonic Engineering, University of Strathclyde, Glasgow, G1 1XW (United Kingdom); Sullivan, J. C.; Pipe, A. G. [Bristol Robotics Laboratory, University of the West of England, Bristol, BS16 1QY (United Kingdom)

2014-02-18T23:59:59.000Z

253

Heat pump augmented radiator for low-temperature space applications  

SciTech Connect (OSTI)

Closed-cycle, space-based heat rejection systems depend solely on radiation to achieve their heat dissipation function. Since the payload heat rejection temperature is typically 50 K above that of the radiation sink in near earth orbit, the size and mass of these systems can be appreciable. Size (and potentially mass) reductions are achievable by increasing the rejection temperature via a heat pump. Two heat pump concept were examined to determine if radiator area reductions could be realized without increasing the mass of the heat rejection system. The first was a conventional, electrically-driven vapor compression system. The second is an innovative concept using a solid-vapor adsorption system driven by reject heat from the prime power system. The mass and radiator area of the heat pumpradiator systems were compared to that of a radiator only system to determine the merit of the heat pump concepts. Results for the compressor system indicated that the mass minimum occured at a temperature lift of about 50 K and radiator area reductions of 35% were realized. With a radiator specific mass of 10 kgm/sup 2/, the heat pump system is 15% higher than the radiator only baseline system. The complex compound chemisorption systems showed more promising results. Using water vapor as the working fluid in a single stage heat amplifier resulted in optimal temperature lifts exceeding 150 K. This resulted in a radiator area reduction of 83% with a mass reduction of 64%. 7 refs., 9 figs.

Olszewski, M.; Rockenfeller, U.

1988-01-01T23:59:59.000Z

254

Operator control systems and methods for swing-free gantry-style cranes  

DOE Patents [OSTI]

A system and method are disclosed for eliminating swing motions in gantry-style cranes while subject to operator control. The present invention comprises an infinite impulse response (IIR) filter and a proportional-integral (PI) feedback controller. The IIR filter receives input signals (commanded velocity or acceleration) from an operator input device and transforms them into output signals in such a fashion that the resulting motion is swing free (i.e., end-point swinging prevented). The parameters of the IIR filter are updated in real time using measurements from a hoist cable length encoder. The PI feedback controller compensates for modeling errors and external disturbances, such as wind or perturbations caused by collision with objects. The PI feedback controller operates on cable swing angle measurements provided by a cable angle sensor. The present invention adjusts acceleration and deceleration to eliminate oscillations. An especially important feature of the present invention is that it compensates for variable-length cable motions from multiple cables attached to a suspended payload. 10 figs.

Feddema, J.T.; Petterson, B.J.; Robinett, R.D. III

1998-07-28T23:59:59.000Z

255

Operator control systems and methods for swing-free gantry-style cranes  

DOE Patents [OSTI]

A system and method for eliminating swing motions in gantry-style cranes while subject to operator control is presented. The present invention comprises an infinite impulse response ("IIR") filter and a proportional-integral ("PI") feedback controller (50). The IIR filter receives input signals (46) (commanded velocity or acceleration) from an operator input device (45) and transforms them into output signals (47) in such a fashion that the resulting motion is swing free (i.e., end-point swinging prevented). The parameters of the IIR filter are updated in real time using measurements from a hoist cable length encoder (25). The PI feedback controller compensates for modeling errors and external disturbances, such as wind or perturbations caused by collision with objects. The PI feedback controller operates on cable swing angle measurements provided by a cable angle sensor (27). The present invention adjusts acceleration and deceleration to eliminate oscillations. An especially important feature of the present invention is that it compensates for variable-length cable motions from multiple cables attached to a suspended payload.

Feddema, John T. (Albuquerque, NM); Petterson, Ben J. (Albuquerque, NM); Robinett, III, Rush D. (Albuquerque, NM)

1998-01-01T23:59:59.000Z

256

POET: POlarimeters for Energetic Transients  

E-Print Network [OSTI]

POET (Polarimeters for Energetic Transients) is a Small Explorer mission concept proposed to NASA in January 2008. The principal scientific goal of POET is to measure GRB polarization between 2 and 500 keV. The payload consists of two wide FoV instruments: a Low Energy Polarimeter (LEP) capable of polarization measurements in the energy range from 2-15 keV and a high energy polarimeter (Gamma-Ray Polarimeter Experiment -- GRAPE) that will measure polarization in the 60-500 keV energy range. Spectra will be measured from 2 keV up to 1 MeV. The POET spacecraft provides a zenith-pointed platform for maximizing the exposure to deep space. Spacecraft rotation will provide a means of effectively dealing with systematics in the polarization response. POET will provide sufficient sensitivity and sky coverage to measure statistically significant polarization for up to 100 GRBs in a two-year mission. Polarization data will also be obtained for solar flares, pulsars and other sources of astronomical interest.

J. E. Hill; M. L. McConnell; P. Bloser; J. Legere; J. Macri; J. Ryan; S. Barthelmy; L. Angelini; T. Sakamoto; J. K. Black; D. H. Hartmann; P. Kaaret; B. Zhang; K. Ioka; T. Nakamura; K. Toma; R. Yamazaki; X. Wu

2008-10-14T23:59:59.000Z

257

POET: POlarimeters for Energetic Transients  

E-Print Network [OSTI]

POET (Polarimeters for Energetic Transients) is a Small Explorer mission concept proposed to NASA in January 2008. The principal scientific goal of POET is to measure GRB polarization between 2 and 500 keV. The payload consists of two wide FoV instruments: a Low Energy Polarimeter (LEP) capable of polarization measurements in the energy range from 2-15 keV and a high energy polarimeter (Gamma-Ray Polarimeter Experiment -- GRAPE) that will measure polarization in the 60-500 keV energy range. Spectra will be measured from 2 keV up to 1 MeV. The POET spacecraft provides a zenith-pointed platform for maximizing the exposure to deep space. Spacecraft rotation will provide a means of effectively dealing with systematics in the polarization response. POET will provide sufficient sensitivity and sky coverage to measure statistically significant polarization for up to 100 GRBs in a two-year mission. Polarization data will also be obtained for solar flares, pulsars and other sources of astronomical interest.

Hill, J E; Bloser, P; Legere, J; Macri, J; Ryan, J; Barthelmy, S; Angelini, L; Sakamoto, T; Black, J K; Hartmann, D H; Kaaret, Philip; Zhang, B; Ioka, K; Nakamura, T; Toma, K; Yamazaki, R; Wu, X

2008-01-01T23:59:59.000Z

258

Advanced robot locomotion.  

SciTech Connect (OSTI)

This report contains the results of a research effort on advanced robot locomotion. The majority of this work focuses on walking robots. Walking robot applications include delivery of special payloads to unique locations that require human locomotion to exo-skeleton human assistance applications. A walking robot could step over obstacles and move through narrow openings that a wheeled or tracked vehicle could not overcome. It could pick up and manipulate objects in ways that a standard robot gripper could not. Most importantly, a walking robot would be able to rapidly perform these tasks through an intuitive user interface that mimics natural human motion. The largest obstacle arises in emulating stability and balance control naturally present in humans but needed for bipedal locomotion in a robot. A tracked robot is bulky and limited, but a wide wheel base assures passive stability. Human bipedal motion is so common that it is taken for granted, but bipedal motion requires active balance and stability control for which the analysis is non-trivial. This report contains an extensive literature study on the state-of-the-art of legged robotics, and it additionally provides the analysis, simulation, and hardware verification of two variants of a proto-type leg design.

Neely, Jason C.; Sturgis, Beverly Rainwater; Byrne, Raymond Harry; Feddema, John Todd; Spletzer, Barry Louis; Rose, Scott E.; Novick, David Keith; Wilson, David Gerald; Buerger, Stephen P.

2007-01-01T23:59:59.000Z

259

On the effects of solar storms to the decaying orbital space debris  

SciTech Connect (OSTI)

Any man-made object in Earth's orbit that no longer serves a useful purpose is classified as orbital debris. Debris objects come from a variety of sources. The majority is related to satellite fragmentation. Other major sources of debris are propulsion systems, and fragmentation of spent upper stages, payload and mission related debris. Serious concern about orbital debris has been growing. Knowledge of the future debris environment is important to both satellite designers, and mission planners, who need to know what hazards a satellite might encounter during the course of its mission. Therefore, it is important to know how much debris is in orbit, where it is located, and when it will decay. The debris environment is complex and dynamically evolving. Objects of different shape and size behave differently in orbit. The geoeffectiveness space environments include solar flux at 10.7 cm, solar energetic particles flux or speed, solar wind flow pressure, electric field, and geomagnetic indices. We study the decaying orbital debris from Tracking and Impact Prediction (TIP) messages in conjuction with geoeffectiveness space environments through time epoch correlation. We found that the decaying and reentry orbital debris are triggered by space environment enhancement within at least one week before reentry. It is not necessary a transient or high energetic and severe solar storm events are needed in decaying processes. We propose that the gradual enhancement processes of space environment will cause satellite surface charging due to energetic electron and enhance drag force.

Herdiwijaya, Dhani, E-mail: dhani@as.itb.ac.id [Astronomy Division and Bosscha Observatory, Faculty of Mathematics and Natural Sciences, Bandung Institute of Technology, Ganesha 10, Bandung 40132 (Indonesia); Rachman, Abdul [Space Science Center, National Institute of Aeronautics and Space, Junjunan 133, Bandung 40173 (Indonesia)

2014-03-24T23:59:59.000Z

260

Extension of the quantum-kinetic model to lunar and Mars return physics  

SciTech Connect (OSTI)

The ability to compute rarefied, ionized hypersonic flows is becoming more important as missions such as Earth reentry, landing high-mass payloads on Mars, and the exploration of the outer planets and their satellites are being considered. A recently introduced molecular-level chemistry model, the quantum-kinetic, or Q-K, model that predicts reaction rates for gases in thermal equilibrium and non-equilibrium using only kinetic theory and fundamental molecular properties, is extended in the current work to include electronic energy level transitions and reactions involving charged particles. Like the Q-K procedures for neutral species chemical reactions, these new models are phenomenological procedures that aim to reproduce the reaction/transition rates but do not necessarily capture the exact physics. These engineering models are necessarily efficient due to the requirement to compute billions of simulated collisions in direct simulation Monte Carlo (DSMC) simulations. The new models are shown to generally agree within the spread of reported transition and reaction rates from the literature for near equilibrium conditions.

Liechty, D. S. [Aerothermodynamics Branch, NASA Langley Research Center, Hampton, Virginia 23681 (United States)] [Aerothermodynamics Branch, NASA Langley Research Center, Hampton, Virginia 23681 (United States); Lewis, M. J. [Department of Aerospace Engineering, University of Maryland, College Park, Maryland 20742 (United States)] [Department of Aerospace Engineering, University of Maryland, College Park, Maryland 20742 (United States)

2014-02-15T23:59:59.000Z

Note: This page contains sample records for the topic "ur3 ur4 payload" from the National Library of EnergyBeta (NLEBeta).
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261

The PLATO End-to-End CCD Simulator -- Modelling space-based ultra-high precision CCD photometry for the assessment study of the PLATO Mission  

E-Print Network [OSTI]

The PLATO satellite mission project is a next generation ESA Cosmic Vision satellite project dedicated to the detection of exo-planets and to asteroseismology of their host-stars using ultra-high precision photometry. The main goal of the PLATO mission is to provide a full statistical analysis of exo-planetary systems around stars that are bright and close enough for detailed follow-up studies. Many aspects concerning the design trade-off of a space-based instrument and its performance can best be tackled through realistic simulations of the expected observations. The complex interplay of various noise sources in the course of the observations made such simulations an indispensable part of the assessment study of the PLATO Payload Consortium. We created an end-to-end CCD simulation software-tool, dubbed PLATOSim, which simulates photometric time-series of CCD images by including realistic models of the CCD and its electronics, the telescope optics, the stellar field, the pointing uncertainty of the satellite ...

Zima, W; De Ridder, J; Salmon, S; Catala, C; Kjeldsen, H; Aerts, C

2010-01-01T23:59:59.000Z

262

The scalability of OTR (out-of-core thermionic reactor) space nuclear power systems  

SciTech Connect (OSTI)

In this document, masses of the STAR-C power system and an optimized out-of-core thermionic reactor (OTR) power system versus power level are investigated. The impacts of key system parameters on system performance are also addressed. The STAR-C is mass competitive below about 15 kWe, but at higher power levels the scalability is relatively poor. An optimized OR is the least massive space nuclear power system below 25 kWe, and scales well to 50 kWe. The system parameters that have a significant impact on the scalability of the STAR-C are core thermal flux, thermionic converter efficiency, and core length to diameter ratio. The emissivity of the core surface is shown to be a relatively unimportant parameter. For an optimized OR power system, the most significant system parameter is the maximum allowable fuel temperature. It is also shown that if advanced radiation-hardened electronics are used in the satellite payload, a very large mass savings is realized. 10 refs., 23 figs., 7 tabs.

Gallup, D.R.

1990-03-01T23:59:59.000Z

263

NEAT, An Astrometric Telescope To Probe Planetary Systems Down To The Earth Mass Around Nearby Solar-Type Stars  

E-Print Network [OSTI]

The NEAT (Nearby Earth Astrometric Telescope) mission is a proposition submitted to ESA for its 2010 call for M-size mission. The main scientific goal is to detect and characterize planetary systems in an exhaustive way down to 1 Earth mass in the habitable zone and further away, around nearby stars for F, G, and K spectral types. This survey would provide the actual planetary masses, the full characterization of the orbits including their inclination, for all the components of the planetary system down to that mass limit. Extremely- high-precision astrometry, in space, can detect the dynamical effect due to even low mass orbiting planets on their central star, reaching those scientific goals. NEAT will continue the work performed by Hipparcos (1mas precision) and Gaia (7{\\mu}as aimed) by reaching a precision that is improved by two orders of magnitude (0.05{\\mu}as, 1{\\sigma} accuracy). The two modules of the payload, the telescope and the focal plane, must be placed 40m away leading to a formation flying opt...

Malbet, F; Goullioud, R; Shao, M; Lagage, P -O; Cara, C; Durand, G; Feautrier, P; Jakobsson, B; Hinglais, E; Mercier, M

2011-01-01T23:59:59.000Z

264

SCADA Protocol Anomaly Detection Utilizing Compression (SPADUC) 2013  

SciTech Connect (OSTI)

There is a significant need to protect the nations energy infrastructures from malicious actors using cyber methods. Supervisory, Control, and Data Acquisition (SCADA) systems may be vulnerable due to the insufficient security implemented during the design and deployment of these control systems. This is particularly true in older legacy SCADA systems that are still commonly in use. The purpose of INLs research on the SCADA Protocol Anomaly Detection Utilizing Compression (SPADUC) project was to determine if and how data compression techniques could be used to identify and protect SCADA systems from cyber attacks. Initially, the concept was centered on how to train a compression algorithm to recognize normal control system traffic versus hostile network traffic. Because large portions of the TCP/IP message traffic (called packets) are repetitive, the concept of using compression techniques to differentiate non-normal traffic was proposed. In this manner, malicious SCADA traffic could be identified at the packet level prior to completing its payload. Previous research has shown that SCADA network traffic has traits desirable for compression analysis. This work investigated three different approaches to identify malicious SCADA network traffic using compression techniques. The preliminary analyses and results presented herein are clearly able to differentiate normal from malicious network traffic at the packet level at a very high confidence level for the conditions tested. Additionally, the master dictionary approach used in this research appears to initially provide a meaningful way to categorize and compare packets within a communication channel.

Gordon Rueff; Lyle Roybal; Denis Vollmer

2013-01-01T23:59:59.000Z

265

An Unprecedented Constraint on Water Content in the Sunlit Lunar Exosphere Seen by Lunar-Based Ultraviolet Telescope of Chang'e-3 Mission  

E-Print Network [OSTI]

The content of $\\mathrm{OH/H_2O}$ molecules in the tenuous exosphere of the Moon is still an open issue at present. We here report an unprecedented upper limit of the content of the OH radicals, which is obtained from the in-situ measurements carried out \\rm by the Lunar-based Ultraviolet Telescope, a payload of Chinese Chang'e-3 mission. By analyzing the diffuse background in the images taken by the telescope, the column density and surface concentration of the OH radicals are inferred to be $<10^{11}\\ \\mathrm{cm^{-2}}$ and $<10^{4}\\ \\mathrm{cm^{-3}}$ (by assuming a hydrostatic equilibrium with a scale height of 100km), respectively, by assuming that the recorded background is fully contributed by their resonance fluorescence emission. The resulted concentration is lower than the previously reported value by about two orders of magnitude, and is close to the prediction of the sputtering model. In addition, the same measurements and method allow us to derive a surface concentration of $<10^{2}\\ \\math...

Wang, J; Qiu, Y L; Meng, X M; Cai, H B; Cao, L; Deng, J S; Han, X H; Wei, J Y

2015-01-01T23:59:59.000Z

266

Extragalactic Inverse Compton Light from Dark Matter annihilation and the Pamela positron excess  

SciTech Connect (OSTI)

We calculate the extragalactic diffuse emission originating from the up-scattering of cosmic microwave photons by energetic electrons and positrons produced in particle dark matter annihilation events at all redshifts and in all halos. We outline the observational constraints on this emission and we study its dependence on both the particle dark matter model (including the particle mass and its dominant annihilation final state) and on assumptions on structure formation and on the density profile of halos. We find that for low-mass dark matter models, data in the X-ray band provide the most stringent constraints, while the gamma-ray energy range probes models featuring large masses and pair-annihilation rates, and a hard spectrum for the injected electrons and positrons. Specifically, we point out that the all-redshift, all-halo inverse Compton emission from many dark matter models that might provide an explanation to the anomalous positron fraction measured by the Pamela payload severely overproduces the observed extragalactic gamma-ray background.

Profumo, Stefano [Department of Physics, University of California, 1156 High St, Santa Cruz, CA 95064 (United States); Jeltema, Tesla E., E-mail: profumo@scipp.ucsc.edu, E-mail: tesla@ucolick.org [UCO/Lick Observatories, 1156 High St, Santa Cruz, CA 95064 (United States)

2009-07-01T23:59:59.000Z

267

Evaluation of using cyclocranes to support drilling and production of oil and gas in wetland areas. Fourth quarterly technical progress report, Second quarter, 1993  

SciTech Connect (OSTI)

The planned program falls under wetlands area research related to drilling, production, and transportation of oil and gas resources. Specifically the planned program addresses an evaluation of using cyclocraft to transport drill rigs, mud, pipes and other materials and equipment in a cost effective and environmentally safe manner to support oil and gas drilling and production operations in wetland areas. The cyclocraft is a proven hybrid aircraft that utilizes aerostatic and aerodynamic lift. This type of aircraft has considerable payload capacity, VTOL capability, high controllability, low operating cost, low downwash and high safety. The benefits of using a cyclocraft to transport drill rigs and materials over environmentally-sensitive surfaces would be significant. The cyclocraft has considerable cost and operational advantages over the helicopter. The major activity during the second quarter of 1993 was focussed on completion of Task 4, Preliminary Design. The selected design has been designated H.1 Cyclocraft by MRC. Also during the report period, Task 6, Ground Support, was completed and a report containing the results was submitted to DOE. This task addressed the complete H.1 Cyclocraft system, i.e. it included the need personnel, facilities and equipment to support cyclocraft operations in wetland areas.

Eggington, W.J.

1993-09-01T23:59:59.000Z

268

Evaluation of using cyclocranes to support drilling and production of oil and gas in wetland areas. Fifth quarterly technical progress report, Third quarter, 1993  

SciTech Connect (OSTI)

The planned program falls under wetlands area research related to drilling, production, and transportation of oil and gas resources. Specifically the planned program addresses an evaluation of using cyclocraft to transport drill rigs, mud, pipes and other materials and equipment in a cost effective and environmentally safe manner to support oil and gas drilling and production operations in wetland areas. The cyclocraft is a proven hybrid aircraft that utilizes aerostatic and aerodynamic lift. This type of aircraft has considerable payload capacity, VTOL capability, high controllability, low operating cost, low downwash and high safety. The benefits of using a cyclocraft to transport drill rigs and materials over environmentally-sensitive surfaces would be significant. The cyclocraft has considerable cost and operational advantages over the helicopter. In 1992, Task 1, Environmental Considerations, and Task 2, Transport Requirements, were completed. In the first two quarters of 1993, Task 3, Parametric Analysis, Task 4, Preliminary Design, and Task 6, Ground Support, were completed. Individual reports containing results obtained from each of these tasks were submitted to DOE. In addition, through June 30, 1993, a Subscale Test Plan was prepared under Task 5, Subscale Tests, and work was initiated on Task 7, Environmental Impacts, Task 8, Development Plan, Task 9, Operating Costs, and Task 10, Technology Transfer.

Eggington, W.J.

1993-12-31T23:59:59.000Z

269

Proton irradiation effect on SCDs  

E-Print Network [OSTI]

The Low Energy X-ray Telescope is a main payload on the Hard X-ray Modulation Telescope satellite. The swept charge device is selected for the Low Energy X-ray Telescope. As swept charge devices are sensitive to proton irradiation, irradiation test was carried out on the HI-13 accelerator at the China Institute of Atomic Energy. The beam energy was measured to be 10 MeV at the SCD. The proton fluence delivered to the SCD was $3\\times10^{8}\\mathrm{protons}/\\mathrm{cm}^{2}$ over two hours. It is concluded that the proton irradiation affects both the dark current and the charge transfer inefficiency of the SCD through comparing the performance both before and after the irradiation. The energy resolution of the proton-irradiated SCD is 212 eV@5.9 keV at $-60\\,^{\\circ}\\mathrm{C}$, while it before irradiated is 134 eV. Moreover, better performance can be reached by lowering the operating temperature of the SCD on orbit.

Yan-Ji Yang; Jing-Bin Lu; Yu-Sa Wang; Yong Chen; Yu-Peng Xu; Wei-Wei Cui; Wei Li; Zheng-Wei Li; Mao-Shun Li; Xiao-Yan Liu; Juan Wang; Da-Wei Han; Tian-Xiang Chen; Cheng-Kui Li; Jia Huo; Wei Hu; Yi Zhang; Bo Lu; Yue Zhu; Ke-Yan Ma; Di Wu; Yan Liu; Zi-Liang Zhang; Guo-He Yin; Yu Wang

2014-04-19T23:59:59.000Z

270

Mars mission opportunity and transit time sensitivity for a nuclear thermal rocket propulsion application  

SciTech Connect (OSTI)

President George Bush's 1989 challenge to America to support the Space Exploration Initiative (SEI) of Back to the Moon and Human Mission to Mars'' gives the space industry an opportunity to develop effective and efficient space transportation systems. This paper presents stage performance and requirements for a nuclear thermal rocket (NTR) Mars transportation system to support the human Mars mission of the SEI. Two classes of Mars mission profiles are considered in developing the NTR propulsion vehicle performance and requirements. The two Mars mission classes include the opposition class and conjunction class. The opposition class mission is associated with relatively short Mars stay times ranging from 30 to 90 days and total mission duration of 350 to 600 days. The conjunction class mission is associated with much longer Mars stay times ranging from 500 to 600 days and total mission durations of 875 to 1,000 days. Vehicle mass scaling equations are used to determine the NTR stage mass, size, and performance range required for different Mars mission opportunities and for different Mars mission durations. Mission opportunities considered include launch years 2010 to 2018. The 2010 opportunity is the most demanding launch opportunity and the 2018 opportunity is the least demanding opportunity. NTR vehicle mass and size sensitivity to NTR engine thrust level, engine specific impulse, NTR engine thrust-to-weight ratio, and Mars surface payload are presented. NTR propulsion parameter ranges include those associated with NERVA, particle bed reactor (PBR), low-pressure, and ceramic-metal-type engine design.

Young, A.C.; Mulqueen, J.A.; Nishimuta, E.L.; Emrich, W.J. (George C. Marshall Space Flight Center, Marshall Space Flight Center, Alabama 35812 (United States))

1993-01-10T23:59:59.000Z

271

Interplanetary missions with the GDM propulsion system  

SciTech Connect (OSTI)

The Gasdynamic Mirror (GDM) fusion propulsion system utilizes a magnetic mirror machine in which a hot dense plasma is confined long enough to produce fusion energy while allowing a fraction of its charged particle population to escape from one end to generate thrust. The particles escaping through the opposite end have their energy converted to electric power which can be used to sustain the system in a steady state operation. With the aid of a power flow diagram the minimum demands on energy production can be established and the propulsive capability of the system can be determined by solving an appropriate set of governing equations. We apply these results to several missions within the solar system and compute the trip time by invoking a continuous burn, acceleration/deceleration type of trajectory with constant thrust and specific impulse. Ignoring gravitational effects of the planets or the sun, and neglecting the change in the Earth's position during the flight we compute the round trip time for missions from Earth to Mars, Jupiter, and Pluto using linear distances and certain payload fractions. We find that a round trip to Mars with the GDM rocket takes about 170 days while those to Jupiter and Pluto take 494 and 1566 days respectively.

Kammash, T.; Emrich, W. Jr. [Department of Nuclear Engineering and Radiological Sciences, University of Michigan, Ann Arbor, Michigan 48109 (United States); Marshall Space Flight Center, Huntsville, Alabama 35812 (United States)

1998-01-15T23:59:59.000Z

272

Packaging and transportation of radioactive liquid at the U.S. Department of Energy Hanford Site  

SciTech Connect (OSTI)

Beginning in the 1940`s, radioactive liquid waste has been generated at the US Department of Energy (DOE) Hanford Site as a result of defense material production. The liquid waste is currently stored in 177 underground storage tanks. As part of the tank remediation efforts, Type B quantity packagings for the transport of large volumes of radioactive liquids are required. There are very few Type B liquid packagings in existence because of the rarity of large-volume radioactive liquid payloads in the commercial nuclear industry. Development of aboveground transport systems for large volumes of radioactive liquids involves institutional, economic, and technical issues. Although liquid shipments have taken place under DOE-approved controlled conditions within the boundaries of the Hanford Site for many years, offsite shipment requires compliance with DOE, US Nuclear Regulatory Commission (NRC), and US Department of Transportation (DOT) directives and regulations. At the present time, no domestic DOE nor NRC-certified Type B packagings with the appropriate level of shielding are available for DOT-compliant transport of radioactive liquids in bulk volumes. This paper will provide technical details regarding current methods used to transport such liquids on and off the Hanford Site, and will provide a status of packaging development programs for future liquid shipments.

Smith, R.J.

1995-02-01T23:59:59.000Z

273

Rosie: A mobile worksystem for decontamination and dismantlement operations  

SciTech Connect (OSTI)

RedZone Robotics, Inc. and Carnegie Mellon University`s Field Robotics Center have undertaken a contract to develop a next-generation worksystem for decommissioning and dismantlement tasks in Department of Energy (DOE) facilities. Currently, the authors are closing the second phase of this three phase effort and have completed the design and fabrication of the worksystem: Rosie. Rosie includes a locomotor, heavy manipulator, control center, and control system for robot operation. The locomotor is an omni-directional platform with tether management and hydraulic power capabilities. The heavy manipulator is a high-payload, long-reach system intended to deploy tools into the work area. The heavy manipulator is capable of deploying systems such as the Dual-Arm Work Module--a five degree-of-freedom platform supporting two highly dexterous manipulators--or a single manipulator for performing simpler, less dexterous tasks. Rosie is telerobotic to the point of having servo-controlled motions which can be operated and coordinated through the control center.

Thompson, B.R.; Conley, L.

1996-05-01T23:59:59.000Z

274

The Large Observatory For x-ray Timing  

E-Print Network [OSTI]

The Large Observatory For x-ray Timing (LOFT) was studied within ESA M3 Cosmic Vision framework and participated in the final down-selection for a launch slot in 2022-2024. Thanks to the unprecedented combination of effective area and spectral resolution of its main instrument, LOFT will study the behaviour of matter under extreme conditions, such as the strong gravitational field in the innermost regions of accretion flows close to black holes and neutron stars, and the supra-nuclear densities in the interior of neutron stars. The science payload is based on a Large Area Detector (LAD, 10 m 2 effective area, 2-30 keV, 240 eV spectral resolution, 1 deg collimated field of view) and a WideField Monitor (WFM, 2-50 keV, 4 steradian field of view, 1 arcmin source location accuracy, 300 eV spectral resolution). The WFM is equipped with an on-board system for bright events (e.g. GRB) localization. The trigger time and position of these events are broadcast to the ground within 30 s from discovery. In this paper we ...

Feroci, M; Bozzo, E; Barret, D; Brandt, S; Hernanz, M; van der Klis, M; Pohl, M; Santangelo, A; Stella, L; Watts, A; Wilms, J; Zane, S; Ahangarianabhari, M; Albertus, C; Alford, M; Alpar, A; Altamirano, D; Alvarez, L; Amati, L; Amoros, C; Andersson, N; Antonelli, A; Argan, A; Artigue, R; Artigues, B; Atteia, J -L; Azzarello, P; Bakala, P; Baldazzi, G; Balman, S; Barbera, M; van Baren, C; Bhattacharyya, S; Baykal, A; Belloni, T; Bernardini, F; Bertuccio, G; Bianchi, S; Bianchini, A; Binko, P; Blay, P; Bocchino, F; Bodin, P; Bombaci, I; Bidaud, J -M Bonnet; Boutloukos, S; Bradley, L; Braga, J; Brown, E; Bucciantini, N; Burderi, L; Burgay, M; Bursa, M; Budtz-Jrgensen, C; Cackett, E; Cadoux, F R; Cais, P; Caliandro, G A; Campana, R; Campana, S; Capitanio, F; Casares, J; Casella, P; Castro-Tirado, A J; Cavazzuti, E; Cerda-Duran, P; Chakrabarty, D; Chteau, F; Chenevez, J; Coker, J; Cole, R; Collura, A; Cornelisse, R; Courvoisier, T; Cros, A; Cumming, A; Cusumano, G; D'A, A; D'Elia, V; Del Monte, E; De Luca, A; De Martino, D; Dercksen, J P C; De Pasquale, M; De Rosa, A; Del Santo, M; Di Cosimo, S; Diebold, S; Di Salvo, T; 1), I Donnarumma; (32), A Drago; (33), M Durant; (107), D Emmanoulopoulos; (135), M H Erkut; (85), P Esposito; (1, Y Evangelista; 1b),; (24), A Fabian; (34), M Falanga; (25), Y Favre; (35), C Feldman; (128), V Ferrari; (3), C Ferrigno; (133), M Finger; (36), M H Finger; (35, G W Fraser; +),; (2), M Frericks; (7), F Fuschino; (125), M Gabler; (37), D K Galloway; (6), J L Galvez Sanchez; (6), E Garcia-Berro; (10), B Gendre; (62), S Gezari; (39), A B Giles; (40), M Gilfanov; (10), P Giommi; (102), G Giovannini; (102), M Giroletti; (4), E Gogus; (105), A Goldwurm; (86), K Goluchov; (16), D Gtz; (16), C Gouiffes; (56), M Grassi; (42), P Groot; (17), M Gschwender; (128), L Gualtieri; (32), C Guidorzi; (3), L Guy; (2), D Haas; (50), P Haensel; (29), M Hailey; (19), F Hansen; (42), D H Hartmann; (43), C A Haswell; (88), K Hebeler; (37), A Heger; (2), W Hermsen; (28), J Homan; (19), A Hornstrup; (23, R Hudec; 72),; (45), J Huovelin; (5), A Ingram; (2), J J M in't Zand; (27), G Israel; (20), K Iwasawa; (47), L Izzo; (2), H M Jacobs; (17), F Jetter; (118, T Johannsen; 127),; (2), H M Jacobs; (2), P Jonker; (126), J Jos; (49), P Kaaret; (123), G Kanbach; (23), V Karas; (6), D Karelin; (29), D Kataria; (49), L Keek; (29), T Kennedy; (17), D Klochkov; (50), W Kluzniak; (17), K Kokkotas; (45), S Korpela; (51), C Kouveliotou; (87), I Kreykenbohm; (2), L M Kuiper; (19), I Kuvvetli; (7), C Labanti; (52), D Lai; (53), F K Lamb; (2), P P Laubert; (105), F Lebrun; (8), D Lin; (29), D Linder; (54), G Lodato; (55), F Longo; (19), N Lund; (131), T J Maccarone; (14), D Macera; (8), S Maestre; (62), S Mahmoodifar; (17), D Maier; (56), P Malcovati; (120), I Mandel; (144), V Mangano; (50), A Manousakis; (7), M Marisaldi; (109), A Markowitz; (35), A Martindale; (59), G Matt; (107), I M McHardy; (60), A Melatos; (61), M Mendez; (85), S Mereghetti; (68), M Michalska; (20), S Migliari; (85, R Mignani; 108),; (62), M C Miller; (49), J M Miller; (57), T Mineo; (112), G Miniutti; (64), S Morsink; (65), C Motch; (13), S Motta; (66), M Mouchet; (8), G Mouret; (19), J Mula?ov; (1, F Muleri; 1b),; (140), T Muoz-Darias; (95), I Negueruela; (28), J Neilsen; (43), A J Norton; (28), M Nowak; (35), P O'Brien; (19), P E H Olsen; (102), M Orienti; (99, M Orio; 110),; (7), M Orlandini; (68), P Orleanski; (35), J P Osborne; (69), R Osten; (70), F Ozel; (1, L Pacciani; 1b),; (119), M Paolillo; (6), A Papitto; (20), J M Paredes; (83, A Patruno; 141),; (71), B Paul; (17), E Perinati; (115), A Pellizzoni; (47), A V Penacchioni; (136), M A Perez; (72), V Petracek; (10), C Pittori; (95), J Pons; (6), J Portell; (115), A Possenti; (73), J Poutanen; (122), M Prakash; (16), P Le Provost; (70), D Psaltis; (8), D Rambaud; (8), P Ramon; (76), G Ramsay; (1, M Rapisarda; 1b),; (77), A Rachevski; (77), I Rashevskaya; (78), P S Ray; (6), N Rea; (80), S Reddy; (113, P Reig; 81),; (63), M Reina Aranda; (28), R Remillard; (62), C Reynolds; (124), L Rezzolla; (20), M Ribo; (2), R de la Rie; (115), A Riggio; (138), A Rios; (82, P Rodrguez- Gil; 104),; (16), J Rodriguez; (3), R Rohlfs; (57), P Romano; (83), E M R Rossi; (50), A Rozanska; (29), A Rousseau; (84), F Ryde; (63), L Sabau-Graziati; (6), G Sala; (85), R Salvaterra; (61), A Sanna; (134), J Sandberg; (130), S Scaringi; (16), S Schanne; (86), J Schee; (87), C Schmid; (117), S Shore; (27), R Schneider; (88), A Schwenk; (89), A D Schwope; (114), J -Y Seyler; (90), A Shearer; (29), A Smith; (58), D M Smith; (29), P J Smith; (23), V Sochora; (1), P Soffitta; (61), P Soleri; (29), A Spencer

2014-01-01T23:59:59.000Z

275

SPECTRA OF COSMIC-RAY PROTONS AND HELIUM PRODUCED IN SUPERNOVA REMNANTS  

SciTech Connect (OSTI)

Data obtained in the Advanced Thin Ionization Calorimeter (ATIC-2), Cosmic Ray Energetics and Mass (CREAM), and Payload for Antimatter Matter Exploration and Light-nuclei Astrophysics (PAMELA) experiments suggest that the elemental interstellar spectra of cosmic rays below the knee at a few times 10{sup 6} GeV are not simple power laws, but that they experience hardening at a magnetic rigidity of about 240 GV. Another essential feature is the difference between proton and helium energy spectra, such that the He/p ratio increases by more than 50% in the energy range from 10{sup 2} to 10{sup 4} GV. We consider the concavity of the particle spectrum resulting from the nonlinear nature of diffusive shock acceleration in supernova remnants (SNRs) as a possible reason for the observed spectrum hardening. The increase of the helium-to-proton ratio with energy can be interpreted as a consequence of cosmic-ray acceleration by forward and reverse shocks in SNRs. The contribution of particles accelerated by reverse shocks makes the concavity of the produced overall cosmic-ray spectrum more pronounced. The spectra of protons and helium nuclei accelerated in SNRs and released into the interstellar medium are calculated. The derived steady-state interstellar spectra are in reasonably good agreement with observations.

Ptuskin, Vladimir; Zirakashvili, Vladimir [Pushkov Institute of Terrestrial Magnetism, Ionosphere and Radio Wave Propagation of the Russian Academy of Science (IZMIRAN), Troitsk, Moscow Region 142190 (Russian Federation)] [Pushkov Institute of Terrestrial Magnetism, Ionosphere and Radio Wave Propagation of the Russian Academy of Science (IZMIRAN), Troitsk, Moscow Region 142190 (Russian Federation); Seo, Eun-Suk [Department of Physics and Institute of Physical Science and Technology, University of Maryland, College Park, MD 20742 (United States)] [Department of Physics and Institute of Physical Science and Technology, University of Maryland, College Park, MD 20742 (United States)

2013-01-20T23:59:59.000Z

276

Intelligent Unmanned Vehicle Systems Suitable For Individual or Cooperative Missions  

SciTech Connect (OSTI)

The Department of Energys Idaho National Laboratory (INL) has been researching autonomous unmanned vehicle systems for the past several years. Areas of research have included unmanned ground and aerial vehicles used for hazardous and remote operations as well as teamed together for advanced payloads and mission execution. Areas of application include aerial particulate sampling, cooperative remote radiological sampling, and persistent surveillance including real-time mosaic and geo-referenced imagery in addition to high resolution still imagery. Both fixed-wing and rotary airframes are used possessing capabilities spanning remote control to fully autonomous operation. Patented INL-developed auto steering technology is taken advantage of to provide autonomous parallel path swathing with either manned or unmanned ground vehicles. Aerial look-ahead imagery is utilized to provide a common operating picture for the ground and air vehicle during cooperative missions. This paper will discuss the various robotic vehicles, including sensor integration, used to achieve these missions and anticipated cost and labor savings.

Matthew O. Anderson; Mark D. McKay; Derek C. Wadsworth

2007-04-01T23:59:59.000Z

277

Adaptive and mobile ground sensor array.  

SciTech Connect (OSTI)

The goal of this LDRD was to demonstrate the use of robotic vehicles for deploying and autonomously reconfiguring seismic and acoustic sensor arrays with high (centimeter) accuracy to obtain enhancement of our capability to locate and characterize remote targets. The capability to accurately place sensors and then retrieve and reconfigure them allows sensors to be placed in phased arrays in an initial monitoring configuration and then to be reconfigured in an array tuned to the specific frequencies and directions of the selected target. This report reviews the findings and accomplishments achieved during this three-year project. This project successfully demonstrated autonomous deployment and retrieval of a payload package with an accuracy of a few centimeters using differential global positioning system (GPS) signals. It developed an autonomous, multisensor, temporally aligned, radio-frequency communication and signal processing capability, and an array optimization algorithm, which was implemented on a digital signal processor (DSP). Additionally, the project converted the existing single-threaded, monolithic robotic vehicle control code into a multi-threaded, modular control architecture that enhances the reuse of control code in future projects.

Holzrichter, Michael Warren; O'Rourke, William T.; Zenner, Jennifer; Maish, Alexander B.

2003-12-01T23:59:59.000Z

278

Safety analysis report for the TRUPACT-II shipping package (condensed version). Volume 2, Rev. 14  

SciTech Connect (OSTI)

This appendix determines the effective G values for payload shipping categories of contact handled transuranic (CH-TRU) waste materials, based on the radiolytic G values for waste materials that are discussed in detail in Appendix 3.6.8 of the Safety Analysis Report for the TRUPACT-II Shipping Package. The effective G values take into account self-absorption of alpha decay energy inside particulate contamination and the fraction of energy absorbed by nongas-generating materials. As described in Appendix 3.6.8, an effective G value, G{sub eff}, is defined by: G{sub eff} - {Sigma}{sub M} (F{sub M} x G{sub M}) F{sub M}-fraction of energy absorbed by material maximum G value for a material where the sum is over all materials present inside a waste container. The G value itself is determined primarily by the chemical properties of the material and its temperature. The value of F is determined primarily by the size of the particles containing the radionuclides, the distribution of radioactivity on the various materials present inside the waste container, and the stopping distance of alpha particles in air, in the waste materials, or in the waste packaging materials.

NONE

1994-10-01T23:59:59.000Z

279

Contact-Handled Transuranic Waste Acceptance Criteria for the Waste Isolation Pilot Plant  

SciTech Connect (OSTI)

The purpose of this document is to summarize the waste acceptance criteria applicable to the transportation, storage, and disposal of contact-handled transuranic (CH-TRU) waste at the Waste Isolation Pilot Plant (WIPP). These criteria serve as the U.S. Department of Energy's (DOE) primary directive for ensuring that CH-TRU waste is managed and disposed of in a manner that protects human health and safety and the environment.The authorization basis of WIPP for the disposal of CH-TRU waste includes the U.S.Department of Energy National Security and Military Applications of Nuclear EnergyAuthorization Act of 1980 (reference 1) and the WIPP Land Withdrawal Act (LWA;reference 2). Included in this document are the requirements and associated criteriaimposed by these acts and the Resource Conservation and Recovery Act (RCRA,reference 3), as amended, on the CH-TRU waste destined for disposal at WIPP.|The DOE TRU waste sites must certify CH-TRU waste payload containers to thecontact-handled waste acceptance criteria (CH-WAC) identified in this document. Asshown in figure 1.0, the flow-down of applicable requirements to the CH-WAC istraceable to several higher-tier documents, including the WIPP operational safetyrequirements derived from the WIPP CH Documented Safety Analysis (CH-DSA;reference 4), the transportation requirements for CH-TRU wastes derived from theTransuranic Package Transporter-Model II (TRUPACT-II) and HalfPACT Certificates ofCompliance (references 5 and 5a), the WIPP LWA (reference 2), the WIPP HazardousWaste Facility Permit (reference 6), and the U.S. Environmental Protection Agency(EPA) Compliance Certification Decision and approval for PCB disposal (references 7,34, 35, 36, and 37). The solid arrows shown in figure 1.0 represent the flow-down of allapplicable payload container-based requirements. The two dotted arrows shown infigure 1.0 represent the flow-down of summary level requirements only; i.e., the sitesmust reference the regulatory source documents from the U.S. Nuclear RegulatoryCommission (NRC) and the New Mexico Environment Department (NMED) for acomprehensive and detailed listing of the requirements.This CH-WAC does not address the subject of waste characterization relating to adetermination of whether the waste is hazardous; rather, the sites are referred to theWaste Analysis Plan (WAP) contained in the WIPP Hazardous Waste Facility Permit fordetails of the sampling and analysis protocols to be used in determining compliance withthe required physical and chemical properties of the waste. Requirements andassociated criteria pertaining to a determination of the radiological properties of thewaste, however, are addressed in appendix A of this document. The collectiveinformation obtained from waste characterization records and acceptable knowledge(AK) serves as the basis for sites to certify that their CH-TRU waste satisfies the WIPPwaste acceptance criteria listed herein.

Washington TRU Solutions LLC

2005-12-29T23:59:59.000Z

280

Improvements in Hanford TRU Program Utilizing Systems Modeling and Analyses  

SciTech Connect (OSTI)

Hanford's Transuranic (TRU) Program is responsible for certifying contact-handled (CH) TRU waste and shipping the certified waste to the Waste Isolation Pilot Plant (WIPP). Hanford's CH TRU waste includes material that is in retrievable storage as well as above ground storage, and newly generated waste. Certifying a typical container entails retrieving and then characterizing it (Non-Destructive Examination [NDE], Non-Destructive Assay [NDA], and Head Space Gas Sampling [HSG]), validating records (data review and reconciliation), and designating the container for a payload. The certified payload is then shipped to WIPP. Systems modeling and analysis techniques were applied to Hanford's TRU Program to help streamline the certification process and increase shipping rates. The modeling and analysis yields several benefits: - Maintains visibility on system performance and predicts downstream consequences of production issues. - Predicts future system performance with higher confidence, based on tracking past performance. - Applies speculation analyses to determine the impact of proposed changes (e.g., apparent shortage of feed should not be used as basis to reassign personnel if more feed is coming in the queue). - Positively identifies the appropriate queue for all containers (e.g., discovered several containers that were not actively being worked because they were in the wrong 'physical' location - method used previously for queuing up containers). - Identifies anomalies with the various data systems used to track inventory (e.g., dimensional differences for Standard Waste Boxes). A model of the TRU Program certification process was created using custom queries of the multiple databases for managing waste containers. The model was developed using a simplified process chart based on the expected path for a typical container. The process chart was augmented with the remediation path for containers that do not meet acceptance criteria for WIPP. Containers are sorted into queues based on their current status in the process. A container can be in only one queue at any given time. Existing data systems are queried to establish the quantity of containers in each queue on any given day. This sets the amount of feed available that is then modeled to be processed according to the daily production plans. The daily production plans were created by identifying the equipment necessary and the staff that performs each process step, and determining the expected production rate for each step. Production performance is monitored on a weekly basis with Project senior staff to establish a total operating efficiency (TOE) for each step (comparing actual performance to production capacity). The unit operations were modeled to be constrained by each day's feed queue plus the performance of the preceding step. The TOE for each unit operation was applied to an integrated model to determine bottlenecks and identify areas for improvement. All of the steps were linked to predict future system performance based on available feed and integrated system-level TOE. It has been determined that at times sub-optimization of a particular unit operation is necessary to ensure the system remains balanced (e.g., having excess capacity in assay does no good if there is no feed available because the real-time radiography [RTR] is working at half capacity). Several recommendations have been provided to the Project management team resulting in improvements in the performance of TRU certification activities by Hanford's TRU Program. (authors)

Baynes, P.A.; Bailey, K.B.; McKenney, D.E. [Fluor Hanford, Inc., Richland, WA (United States); Uytioco, E. [Fluor Government Group, Richland, WA (United States)

2008-07-01T23:59:59.000Z

Note: This page contains sample records for the topic "ur3 ur4 payload" from the National Library of EnergyBeta (NLEBeta).
While these samples are representative of the content of NLEBeta,
they are not comprehensive nor are they the most current set.
We encourage you to perform a real-time search of NLEBeta
to obtain the most current and comprehensive results.


281

Photovoltaic electric power applied to Unmanned Aerial Vehicles (UAV)  

SciTech Connect (OSTI)

Photovoltaic electric-powered flight is receiving a great deal of attention in the context of the United States` Unmanned Aerial Vehicle (UAV) program. This paper addresses some of the enabling technical areas and their potential solutions. Of particular interest are the long-duration, high-altitude class of UAV`s whose mission it is to achieve altitudes between 60,000 and 100,000 feet, and to remain at those altitudes for prolonged periods performing various mapping and surveillance activities. Addressed herein are studies which reveal the need for extremely light-weight and efficient solar cells, high-efficiency electric motor-driven propeller modules, and power management and distribution control elements. Since the potential payloads vary dramatically in their power consumption and duty cycles, a typical load profile has been selected to provide commonality for the propulsion power comparisons. Since missions vary widely with respect to ground coverage requirements, from repeated orbiting over a localized target to long-distance routes over irregular terrain, the authors have also averaged the power requirements for on-board guidance and control power, as well as ground control and communication link utilization. In the context of the national technology reinvestment program, wherever possible they modeled components and materials which have been qualified for space and defense applications, yet are compatible with civilian UAV activities. These include, but are not limited to, solar cell developments, electric storage technology for diurnal operation, local and ground communications, power management and distribution, and control servo design. And finally, the results of tests conducted by Wright Laboratory on ultralight, highly efficient MOCVD GaAs solar cells purchased from EPI Materials Ltd. (EML) of the UK are presented. These cells were also used for modeling the flight characteristics of UAV aircraft.

Geis, J.; Arnold, J.H. [Rockwell International Corp., Canoga Park, CA (United States)

1994-09-01T23:59:59.000Z

282

Nuclear space power and propulsion requirements and issues  

SciTech Connect (OSTI)

The use of nuclear power in space is going through a low point. The kinds of missions that would use nuclear power are expensive and there are few new expensive missions. Both NASA and DoD are in a mode of cheaper, faster, better, which means using what is available as much as possible and only incorporating new technology to reduce mission cost. NASA is performing Mission to Planet Earth and detailed exploration missions of Mars. These NASA missions can be done with solar-battery power subsystems and there is no need for nuclear power. The NASA mission to Pluto does require nuclear radioisotope power. Ways to reduce the power subsystem cost and the power level are being investigated. NASA is studying ways to explore beyond Mars with solar-battery power because of the cost and uncertainty in the availability and launchability of nuclear space power systems. The DoD missions are all in earth orbit and can be done with solar-battery systems. The major DoD requirement at present is to reduce costs of all their space missions. One way to do this is to develop highly efficient upper stage boosters that can be integrated with lower cost Earth to low orbit stages and still place their payloads in to higher orbits. One attractive upper stage is a nuclear bimodal (propulsion and power) engine to accomplished lower booster cost to place space assets in GEO. However this is not being pursued because of DOE`s new policy not to fund nuclear space power research and development as well as the difficulty in obtaining launch approval for nuclear propulsion and power systems.

Swerdling, M. [IR Associates, North Hills, CA (United States); Isenberg, L. [IR Associates, La Habra, CA (United States)

1995-12-31T23:59:59.000Z

283

Overview of Requirements for Using Overweight Vehicles to Ship Spent Nuclear Fuel  

SciTech Connect (OSTI)

The U.S. Department of Energy's (DOE's) Final Environmental Impact Statement for a Geologic Repository for the Disposal of Spent Nuclear Fuel and High-Level Radioactive Waste at Yucca Mountain, Nye County, Nevada, considered a range of options for transportation. In evaluating the impacts of the mostly-legal weight truck scenario, DOE assumed that some shipments would use overweight trucks. The use of overweight trucks is also considered in the Draft Supplemental Environmental Impact Statement for a Geologic Repository for the Disposal of Spent Nuclear Fuel and High-Level Radioactive Waste at Yucca Mountain, Nye County, Nevada, issued for public comment in Fall 2007. With the exception of permit requirements and operating restrictions, the vehicles for overweight shipments would be similar to legal-weight truck shipments but might weigh as much as 52,200 kilograms (115,000 pounds). The use of overweight trucks was determined to be acceptable for the Office of Civilian Radioactive Waste Management (OCRWM) Program because the payload is not divisible and the packaging alone may make shipments overweight. Overweight truck shipments are common, and states routinely issue overweight permits, some for vehicles with a gross vehicle weight up to 58,500 kilograms (129,000 pounds). This paper will present an overview of state overweight truck permitting policies and national and regional approaches to promote safety and uniformity. In conclusion: Overweight truck shipments are made routinely by carriers throughout the country. State permits are obtained by the carriers or by companies that provide permitting services to the carriers. While varying state permit restrictions may add complexity to OCRWM's planning activities, the well-established experience of commercial carriers and efforts to bring uniformity to the permitting process should allow the overweight shipment of SNF to be a viable option. (authors)

Thrower, A.W. [U.S. Department of Energy, Office of Civilian Radioactive Waste Management, Washington, DC (United States); Offner, J. [Booz Allen Hamilton, Washington, DC (United States); Bolton, P. [Booz Allen Hamilton, Santa Fe, NM (United States)

2008-07-01T23:59:59.000Z

284

The VAMOS Ocean-Cloud-Atmosphere-Land Study Regional Experiment (VOCALS-REx): Goals, platforms, and field operations  

SciTech Connect (OSTI)

The VAMOS Ocean-Cloud-Atmosphere-Land Study Regional Experiment (VOCALS-REx) was an international field program designed to make observations of poorly understood but critical components of the coupled climate system of the southeast Pacific. This region is characterized by strong coastal upwelling, the coolest SSTs in the tropical belt, and is home to the largest subtropical stratocumulus deck on Earth. The field intensive phase of VOCALS-REx took place during October and November 2008 and constitutes a critical part of a broader CLIVAR program (VOCALS) designed to develop and promote scientific activities leading to improved understanding, model simulations, and predictions of the southeastern Pacific (SEP) coupled ocean-atmosphere-land system, on diurnal to interannual timescales. The other major components of VOCALS are a modeling program with a model hierarchy ranging from the local to global scales, and a suite of extended observations from regular research cruises, instrumented moorings, and satellites. The two central themes of VOCALS-REx focus upon (a) links between aerosols, clouds and precipitation and their impacts on marine stratocumulus radiative properties, and (b) physical and chemical couplings between the upper ocean and the lower atmosphere, including the role that mesoscale ocean eddies play. A set of hypotheses designed to be tested with the combined field, monitoring and modeling work in VOCALS is presented here. A further goal of VOCALS-REx is to provide datasets for the evaluation and improvement of large-scale numerical models. VOCALS-REx involved five research aircraft, two ships and two surface sites in northern Chile. We describe the instrument payloads and key mission strategies for these platforms and give a summary of the missions conducted.

Wood, R.; Springston, S.; Mechoso, C. R.; Bretherton, C. S.; A.Weller, R.; Huebert, B.; Straneo, F.; Albrecht, B. A.; Coe, H.; Allen, G.; Vaughan, G.; Daum, P.; Fairall, C.; Chand, D.; Klenner, L. G.; Garreaud, R.; Grados, C.; Covert, D. S.; Bates, T. S.; Krejci, R.; Russell, L. M.; Szoeke, S. d.; Brewer, A.; Yuter, S. E.; Chaigneau, A.; Toniazzo, T.; Minnis, P.; Palikonda, R.; Abel, S. J.; Brown, W. O. J.; Williams, S.; Fochesatto, J.; Brioude, J.; Bower, K. N

2011-01-21T23:59:59.000Z

285

Operations of a Radioisotope-based Propulsion System Enabling CubeSat Exploration of the Outer Planets  

SciTech Connect (OSTI)

Exploration to the outer planets is an ongoing endeavor but in the current economical environment, cost reduction is the forefront of all concern. The success of small satellites such as CubeSats launched to Near-Earth Orbit has lead to examine their potential use to achieve cheaper science for deep space applications. However, to achieve lower cost missions; hardware, launch and operations costs must be minimized. Additionally, as we push towards smaller exploration beds with relative limited power sources, allowing for adequate communication back to Earth is imperative. Researchers at the Center for Space Nuclear Research are developing the potential of utilizing an advanced, radioisotope-based system. This system will be capable of providing both the propulsion power needed to reach the destination and the additional requirements needed to maintain communication while at location. Presented here are a basic trajectory analysis, communication link budget and concept of operations of a dual-mode (thermal and electric) radioisotope-based propulsion system, for a proposed mission to Enceladus (Saturnian icy moon) using a 6U CubeSat payload. The radioisotope system being proposed will be the integration of three sub-systems working together to achieve the overall mission. At the core of the system, stored thermal energy from radioisotope decay is transferred to a passing propellant to achieve high thrust useful for quick orbital maneuvering. An auxiliary closed-loop Brayton cycle can be operated in parallel to the thrusting mode to provide short bursts of high power for high data-rate communications back to Earth. Additionally, a thermal photovoltaic (TPV) energy conversion system will use radiation heat losses from the core. This in turn can provide the electrical energy needed to utilize the efficiency of ion propulsion to achieve quick interplanetary transit times. The intelligent operation to handle all functions of this system under optimized conditions adds to the complexity of the mission architecture.

Dr. Steven Howe; Nathan Jerred; Troy Howe; Adarsh Rajguru

2014-05-01T23:59:59.000Z

286

Enrichment Zoning Options for the Small Nuclear Rocket Engine (SNRE)  

SciTech Connect (OSTI)

Advancement of U.S. scientific, security, and economic interests through a robust space exploration program requires high performance propulsion systems to support a variety of robotic and crewed missions beyond low Earth orbit. In NASAs recent Mars Design Reference Architecture (DRA) 5.0 study (NASA-SP-2009-566, July 2009), nuclear thermal propulsion (NTP) was again selected over chemical propulsion as the preferred in-space transportation system option because of its high thrust and high specific impulse (-900 s) capability, increased tolerance to payload mass growth and architecture changes, and lower total initial mass in low Earth orbit. An extensive nuclear thermal rocket technology development effort was conducted from 1955-1973 under the Rover/NERVA Program. The Small Nuclear Rocket Engine (SNRE) was the last engine design studied by the Los Alamos National Laboratory during the program. At the time, this engine was a state-of-the-art design incorporating lessons learned from the very successful technology development program. Past activities at the NASA Glenn Research Center have included development of highly detailed MCNP Monte Carlo transport models of the SNRE and other small engine designs. Preliminary core configurations typically employ fuel elements with fixed fuel composition and fissile material enrichment. Uniform fuel loadings result in undesirable radial power and temperature profiles in the engines. Engine performance can be improved by some combination of propellant flow control at the fuel element level and by varying the fuel composition. Enrichment zoning at the fuel element level with lower enrichments in the higher power elements at the core center and on the core periphery is particularly effective. Power flattening by enrichment zoning typically results in more uniform propellant exit temperatures and improved engine performance. For the SNRE, element enrichment zoning provided very flat radial power profiles with 551 of the 564 fuel elements within 1% of the average element power. Results for this and alternate enrichment zoning options for the SNRE are compared.

Bruce G. Schnitzler; Stanley K. Borowski

2010-07-01T23:59:59.000Z

287

Optimization of a CNG series hybrid concept vehicle  

SciTech Connect (OSTI)

Compressed Natural Gas (CNG) has favorable characteristics as a vehicular fuel, in terms of fuel economy as well as emissions. Using CNG as a fuel in a series hybrid vehicle has the potential of resulting in very high fuel economy (between 26 and 30 km/liter, 60 to 70 mpg) and very low emissions (substantially lower than Federal Tier II or CARB ULEV). This paper uses a vehicle evaluation code and an optimizer to find a set of vehicle parameters that result in optimum vehicle fuel economy. The vehicle evaluation code used in this analysis estimates vehicle power performance, including engine efficiency and power, generator efficiency, energy storage device efficiency and state-of-charge, and motor and transmission efficiencies. Eight vehicle parameters are selected as free variables for the optimization. The optimum vehicle must also meet two perfect requirements: accelerate to 97 km/h in less than 10 s, and climb an infinitely long hill with a 6% slope at 97 km/h with a 272 kg (600 lb.) payload. The optimizer used in this work was originally developed in the magnetic fusion energy program, and has been used to optimize complex systems, such as magnetic and inertial fusion devices, neutron sources, and mil guns. The optimizer consists of two parts: an optimization package for minimizing non-linear functions of many variables subject to several non-linear equality and/or inequality constraints and a programmable shell that allows interactive configuration and execution of the optimizer. The results of the analysis indicate that the CNG series hybrid vehicle has a high efficiency and low emissions. These results emphasize the advantages of CNG as a near-term alternative fuel for vehicles.

Aceves, S.M.; Smith, J.R.; Perkins, L.J.; Haney, S.W.; Flowers, D.L.

1995-09-22T23:59:59.000Z

288

An intelligent inspection and survey robot. Volume 1  

SciTech Connect (OSTI)

ARIES {number_sign}1 (Autonomous Robotic Inspection Experimental System), has been developed for the Department of Energy to survey and inspect drums containing low-level radioactive waste stored in warehouses at DOE facilities. The drums are typically stacked four high and arranged in rows with three-foot aisle widths. The robot will navigate through the aisles and perform an inspection operation, typically performed by a human operator, making decisions about the condition of the drums and maintaining a database of pertinent information about each drum. A new version of the Cybermotion series of mobile robots is the base mobile vehicle for ARIES. The new Model K3A consists of an improved and enhanced mobile platform and a new turret that will permit turning around in a three-foot aisle. Advanced sonar and lidar systems were added to improve navigation in the narrow drum aisles. Onboard computer enhancements include a VMEbus computer system running the VxWorks real-time operating system. A graphical offboard supervisory UNIX workstation is used for high-level planning, control, monitoring, and reporting. A camera positioning system (CPS) includes primitive instructions for the robot to use in referencing and positioning the payload. The CPS retracts to a more compact position when traveling in the open warehouse. During inspection, the CPS extends up to deploy inspection packages at different heights on the four-drum stacks of 55-, 85-, and 110-gallon drums. The vision inspection module performs a visual inspection of the waste drums. This system will locate and identify each drum, locate any unique visual features, characterize relevant surface features of interest and update a data-base containing the inspection data.

NONE

1995-12-15T23:59:59.000Z

289

X-RED: A Satellite Mission Concept To Detect Early Universe Gamma Ray Bursts  

E-Print Network [OSTI]

Gamma ray bursts (GRBs) are the most energetic eruptions known in the Universe. Instruments such as Compton-GRO/BATSE and the GRB monitor on BeppoSAX have detected more than 2700 GRBs and, although observational confirmation is still required, it is now generally accepted that many of these bursts are associated with the collapse of rapidly spinning massive stars to form black holes. Consequently, since first generation stars are expected to be very massive, GRBs are likely to have occurred in significant numbers at early epochs. X-red is a space mission concept designed to detect these extremely high redshifted GRBs, in order to probe the nature of the first generation of stars and hence the time of reionisation of the early Universe. We demonstrate that the gamma and x-ray luminosities of typical GRBs render them detectable up to extremely high redshifts (z~10-30), but that current missions such as HETE2 and SWIFT operate outside the observational range for detection of high redshift GRB afterglows. Therefore, to redress this, we present a complete mission design from the science case to the mission architecture and payload, the latter comprising three instruments, namely wide field x-ray cameras to detect high redshift gamma-rays, an x-ray focussing telescope to determine accurate coordinates and extract spectra, and an infrared spectrograph to observe the high redshift optical afterglow. The mission is expected to detect and identify for the first time GRBs with z > 10, thereby providing constraints on properties of the first generation of stars and the history of the early Universe.

Mirko Krumpe; Deirdre Coffey; Georg Egger; Francesc Vilardell; Karolien Lefever; Adriane Liermann; Agnes I. D. Hoffmann; Joerg Steiper; Marc Cherix; Simon Albrecht; Pedro Russo; Thomas Strodl; Rurik Wahlin; Pieter Deroo; Arvind Parmar; Niels Lund; Guenther Hasinger

2005-11-10T23:59:59.000Z

290

Multi Megawatt Power System Analysis Report  

SciTech Connect (OSTI)

Missions to the outer planets or to near-by planets requiring short times and/or increased payload carrying capability will benefit from nuclear power. A concept study was undertaken to evaluate options for a multi-megawatt power source for nuclear electric propulsion. The nominal electric power requirement was set at 15 MWe with an assumed mission profile of 120 days at full power, 60 days in hot standby, and another 120 days of full power, repeated several times for 7 years of service. Of the numerous options considered, two that appeared to have the greatest promise were a gas-cooled reactor based on the NERVA Derivative design, operating a closed cycle Brayton power conversion system; and a molten lithium-cooled reactor based on SP-100 technology, driving a boiling potassium Rankine power conversion system. This study examined the relative merits of these two systems, seeking to optimize the specific mass. Conclusions were that either concept appeared capable of approaching the specific mass goal of 3-5 kg/kWe estimated to be needed for this class of mission, though neither could be realized without substantial development in reactor fuels technology, thermal radiator mass efficiency, and power conversion and distribution electronics and systems capable of operating at high temperatures. Though the gas-Brayton systems showed an apparent advantage in specific mass, differences in the degree of conservatism inherent in the models used suggests expectations for the two approaches may be similar. Brayton systems eliminate the need to deal with two-phase flows in the microgravity environment of space.

Longhurst, Glen Reed; Harvego, Edwin Allan; Schnitzler, Bruce Gordon; Seifert, Gary Dean; Sharpe, John Phillip; Verrill, Donald Alan; Watts, Kenneth Donald; Parks, Benjamin Travis

2001-11-01T23:59:59.000Z

291

GAISUS-1 thermionic converter for the integrated solar upper stage  

SciTech Connect (OSTI)

The Integrated Solar Upper Stage (ISUS) system is a compact orbital transfer vehicle which generates thrust to boost payloads from LEO to higher orbits. It does this by collecting and concentrating solar flux into a sensible thermal storage, graphite receiver which is used to heat hydrogen propellant to temperatures of up to 2500 K. The ISUS receiver also radiates heat into an array of thermionic converters which produce electrical power. The GAISUS-1 thermionic converter is a first generation planar converter designed to produce electrical power when coupled with the ISUS receiver. GAISUS-1 will deliver over 31 W{sub e} at 1900 K. A wrought Re hotshoe accepts radiant heat from the receiver. The back side of the hotshoe forms the emitting surface of the converter. Special attention was paid to optimize the electrical and thermal losses experienced through the sleeve. Triple and single sleeve geometries were thermally modeled and evaluated, resulting in the selection of a single sleeve design. A high temperature metal/ceramic seal isolates the emitter sleeve from the collector. A Nb collector is used and is an integral part of a Nb/Na heat pipe. The heat pipe transports reject heat from the collector surface to a thermal radiator (condenser) portion of the heat pipe. The converter utilizes an integral graphite Cs reservoir. This type of reservoir automatically produces a rise in Cs pressure in response to a rise in emitter/collector temperatures. This Cs pressure feedback mechanism insures adequate Cs coverage of the emitter over a broad range of operating conditions (temperatures).

Begg, L.L.; Heffernan, T.F.; Horner, M.H. [General Atomics, San Diego, CA (United States)

1997-12-31T23:59:59.000Z

292

Best Practices for Finite Element Analysis of Spent Nuclear Fuel Transfer, Storage, and Transportation Systems  

SciTech Connect (OSTI)

Storage casks and transportation packages for spent nuclear fuel (SNF) are designed to confine SNF in sealed canisters or casks, provide structural integrity during accidents, and remove decay through a storage or transportation overpack. The transfer, storage, and transportation of SNF in dry storage casks and transport packages is regulated under 10 CFR Part 72 and 10 CFR Part 71, respectively. Finite Element Analysis (FEA) is used with increasing frequency in Safety Analysis Reports and other regulatory technical evaluations related to SNF casks and packages and their associated systems. Advances in computing power have made increasingly sophisticated FEA models more feasible, and as a result, the need for careful review of such models has also increased. This paper identifies best practice recommendations that stem from recent NRC review experience. The scope covers issues common to all commercially available FEA software, and the recommendations are applicable to any FEA software package. Three specific topics are addressed: general FEA practices, issues specific to thermal analyses, and issues specific to structural analyses. General FEA practices covers appropriate documentation of the model and results, which is important for an efficient review process. The thermal analysis best practices are related to cask analysis for steady state conditions and transient scenarios. The structural analysis best practices are related to the analysis of casks and associated payload during standard handling and drop scenarios. The best practices described in this paper are intended to identify FEA modeling issues and provide insights that can help minimize associated uncertainties and errors, in order to facilitate the NRC licensing review process.

Bajwa, Christopher S.; Piotter, Jason; Cuta, Judith M.; Adkins, Harold E.; Klymyshyn, Nicholas A.; Fort, James A.; Suffield, Sarah R.

2010-08-11T23:59:59.000Z

293

Incentives for the use of depleted uranium alloys as transport cask containment structure  

SciTech Connect (OSTI)

Radioactive material transport casks use either lead or depleted uranium (DU) as gamma-ray shielding material. Stainless steel is conventionally used for structural containment. If a DU alloy had sufficient properties to guarantee resistance to failure during both nominal use and accident conditions to serve the dual-role of shielding and containment, the use of other structure materials (i.e., stainless steel) could be reduced. (It is recognized that lead can play no structural role.) Significant reductions in cask weight and dimensions could then be achieved perhaps allowing an increase in payload. The mechanical response of depleted uranium has previously not been included in calculations intended to show that DU-shielded transport casks will maintain their containment function during all conditions. This paper describesa two-part study of depleted uranium alloys: First, the mechanical behavior of DU alloys was determined in order to extend the limited set of mechanical properties reported in the literature. The mechanical properties measured include the tensile behavior the impact energy. Fracture toughness testing was also performed to determine the sensitivity of DU alloys to brittle fracture. Fracture toughness is the inherent material property which quantifies the fracmm resistance of a material. Tensile strength and ductility are significant in terms of other failure modes, however, as win be discussed. These mechanical properties were then input into finite element calculations of cask response to loading conditions to quantify the potential for claiming structural credit for DU. (The term structural credit'' describes whether a material has adequate properties to allow it to assume a positive role in withstanding structural loadings.)

McConnell, P [GRAM, Inc., Albuquerque, NM (United States); Salzbrenner, R; Wellman, G W; Sorenson, K B [Sandia National Labs., Albuquerque, NM (United States)

1992-01-01T23:59:59.000Z

294

Advances in technology for the construction of deep-underground facilities  

SciTech Connect (OSTI)

The workshop was organized in order to address technological issues important to decisions regarding the feasibility of strategic options. The objectives of the workshop were to establish the current technological capabilities for deep-underground construction, to project those capabilities through the compressed schedule proposed for construction, and to identify promising directions for timely allocation of existing research and development resources. The earth has been used as a means of protection and safekeeping for many centuries. Recently, the thickness of the earth cover required for this purpose has been extended to the 2,000- to 3,000-ft range in structures contemplated for nuclear-waste disposal, energy storage, and strategic systems. For defensive missile basing, it is now perceived that the magnitude of the threat has increased through better delivery systems, larger payloads, and variable tactics of attack. Thus, depths of 3,000 to 8,000 ft are being considered seriously for such facilities. Moreover, it appears desirable that the facilities be operational (if not totally complete) for defensive purposes within a five-year construction schedule. Deep excavations such as mines are similar in many respects to nearsurface tunnels and caverns for transit, rail, sewer, water, hydroelectric, and highway projects. But the differences that do exist are significant. Major distinctions between shallow and deep construction derive from the stress fields and behavior of earth materials around the openings. Different methodologies are required to accommodate other variations resulting from increased depth, such as elevated temperatures, reduced capability for site exploration, and limited access during project execution. This report addresses these and other questions devoted to geotechnical characterization, design, construction, and excavation equipment.

Not Available

1987-12-31T23:59:59.000Z

295

Integrating end-to-end encryption and authentication technology into broadband networks  

SciTech Connect (OSTI)

BISDN services will involve the integration of high speed data, voice, and video functionality delivered via technology similar to Asynchronous Transfer Mode (ATM) switching and SONET optical transmission systems. Customers of BISDN services may need a variety of data authenticity and privacy assurances, via Asynchronous Transfer Mode (ATM) services Cryptographic methods can be used to assure authenticity and privacy, but are hard to scale for implementation at high speed. The incorporation of these methods into computer networks can severely impact functionality, reliability, and performance. While there are many design issues associated with the serving of public keys for authenticated signaling and for establishment of session cryptovariables, this paper is concerned with the impact of encryption itself on such communications once the signaling and setup have been completed. Network security protections should be carefully matched to the threats against which protection is desired. Even after eliminating unnecessary protections, the remaining customer-required network security protections can impose severe performance penalties. These penalties (further discussed below) usually involve increased communication processing for authentication or encryption, increased error rate, increased communication delay, and decreased reliability/availability. Protection measures involving encryption should be carefully engineered so as to impose the least performance, reliability, and functionality penalties, while achieving the required security protection. To study these trade-offs, a prototype encryptor/decryptor was developed. This effort demonstrated the viability of implementing certain encryption techniques in high speed networks. The research prototype processes ATM cells in a SONET OC-3 payload. This paper describes the functionality, reliability, security, and performance design trade-offs investigated with the prototype.

Pierson, L.G.

1995-11-01T23:59:59.000Z

296

Life-cycle analysis of alternative aviation fuels in GREET  

SciTech Connect (OSTI)

The Greenhouse gases, Regulated Emissions, and Energy use in Transportation (GREET) model, developed at Argonne National Laboratory, has been expanded to include well-to-wake (WTWa) analysis of aviation fuels and aircraft. This report documents the key WTWa stages and assumptions for fuels that represent alternatives to petroleum jet fuel. The aviation module in GREET consists of three spreadsheets that present detailed characterizations of well-to-pump and pump-to-wake parameters and WTWa results. By using the expanded GREET version (GREET1{_}2011), we estimate WTWa results for energy use (total, fossil, and petroleum energy) and greenhouse gas (GHG) emissions (carbon dioxide, methane, and nitrous oxide) for (1) each unit of energy (lower heating value) consumed by the aircraft or (2) each unit of distance traveled/ payload carried by the aircraft. The fuel pathways considered in this analysis include petroleum-based jet fuel from conventional and unconventional sources (i.e., oil sands); Fisher-Tropsch (FT) jet fuel from natural gas, coal, and biomass; bio-jet fuel from fast pyrolysis of cellulosic biomass; and bio-jet fuel from vegetable and algal oils, which falls under the American Society for Testing and Materials category of hydroprocessed esters and fatty acids. For aircraft operation, we considered six passenger aircraft classes and four freight aircraft classes in this analysis. Our analysis revealed that, depending on the feedstock source, the fuel conversion technology, and the allocation or displacement credit methodology applied to co-products, alternative bio-jet fuel pathways have the potential to reduce life-cycle GHG emissions by 55-85 percent compared with conventional (petroleum-based) jet fuel. Although producing FT jet fuel from fossil feedstock sources - such as natural gas and coal - could greatly reduce dependence on crude oil, production from such sources (especially coal) produces greater WTWa GHG emissions compared with petroleum jet fuel production unless carbon management practices, such as carbon capture and storage, are used.

Elgowainy, A.; Han, J.; Wang, M.; Carter, N.; Stratton, R.; Hileman, J.; Malwitz, A.; Balasubramanian, S. (Energy Systems)

2012-07-23T23:59:59.000Z

297

Geophex Airborne Unmanned Survey System (GAUSS). Topical report, October 1993--March 1995  

SciTech Connect (OSTI)

The objectives of the project are to construct a geophysical sensor system based on a remotely operated model helicopter (ROH) and to evaluate the efficacy of the system for characterization of hazardous environmental sites. Geophex Airborne Unmanned Survey System (GAUSS) is a geophysical survey system that uses a ROH as the survey vehicle. We have selected the ROH because of its advantages over fixed wing and ground based vehicles. Lower air speed and superior maneuverability of the ROH make it better suited for geophysical surveys than a fixed wing model aircraft. The ROH can fly close to the ground, allowing detection of weak or subtle anomalies. Unlike ground based vehicles, the ROH can traverse difficult terrain while providing a stable sensor platform. ROH does not touch the ground during the course of a survey and is capable of functioning over water and surf zones. The ROH has been successfully used in the motion picture industry and by geology companies for payload bearing applications. The only constraint to use of the airborne system is that the ROH must remain visible to the pilot. Obstructed areas within a site can be characterized by relocating the base station to alternate positions. GAUSS consists of a ROH with radio controller, a data acquisition and processing (DAP) system, and lightweight digital sensor systems. The objective of our Phase I research was to develop a DAP and sensors suitable for ROH operation. We have constructed these subsystems and integrated them to produce an automated, hand-held geophysical surveying system, referred to as the ``pre-prototype``. We have performed test surveys with the pre-prototype to determine the functionality of the and DAP and sensor subsystems and their suitability for airborne application. The objective of the Phase II effort will be to modify the existing subsystems and integrate them into an airborne prototype. Efficacy of the prototype for geophysical survey of hazardous sites will then be determined.

NONE

1995-03-01T23:59:59.000Z

298

Computation of Hypersonic Flow about Maneuvering Vehicles with Changing Shapes  

SciTech Connect (OSTI)

Vehicles moving at hypersonic speeds have great importance to the National Security. Ballistic missile re-entry vehicles (RV's) travel at hypersonic speeds, as do missile defense intercept vehicles. Despite the importance of the problem, no computational analysis method is available to predict the aerodynamic environment of maneuvering hypersonic vehicles, and no analysis is available to predict the transient effects of their shape changes. The present state-of-the-art for hypersonic flow calculations typically still considers steady flow about fixed shapes. Additionally, with present computational methods, it is not possible to compute the entire transient structural and thermal loads for a re-entry vehicle. The objective of this research is to provide the required theoretical development and a computational analysis tool for calculating the hypersonic flow about maneuvering, deforming RV's. This key enabling technology will allow the development of a complete multi-mechanics simulation of the entire RV flight sequence, including important transient effects such as complex flight dynamics. This will allow the computation of the as-delivered state of the payload in both normal and unusual operational environments. This new analysis capability could also provide the ability to predict the nonlinear, transient behavior of endo-atmospheric missile interceptor vehicles to the input of advanced control systems. Due to the computational intensity of fluid dynamics for hypersonics, the usual approach for calculating the flow about a vehicle that is changing shape is to complete a series of steady calculations, each with a fixed shape. However, this quasi-steady approach is not adequate to resolve the frequencies characteristic of a vehicle's structural dynamics. Our approach is to include the effects of the unsteady body shape changes in the finite-volume method by allowing for arbitrary translation and deformation of the control volumes. Furthermore, because the Eulerian computational mesh for the fluid domain must be attached to the vehicle as it undergoes potentially high accelerations, that mesh must be viewed in a non-inertial coordinate frame. The usual conservation-law form of the fluid dynamic governing equations must be augmented. This approach thus requires the derivation of a significantly new numerical formulation, especially to incorporate a modern flux-splitting methodology as needed for numerical stability and accuracy.

Ferencz, R M; Felker, F F; Castillo, V M

2004-02-23T23:59:59.000Z

299

Mesoporous silica nanoparticles as smart and safe devices for regulating blood biomolecule levels  

SciTech Connect (OSTI)

Stimuli-responsive end-capped MSN materials are promising drug carriers that securely deliver a large payload of drug molecules without degradation or premature release. A general review of the recent progress in this field is presented, including a summary of a series of hard and soft caps for drug encapsulation and a variety of internal and external stimuli for controlled release of different therapeutics, a discussion of the biocompatibility of MSN both in vitro and in vivo, and a description of the sophisticated stimuli-responsive systems with novel capping agents and controlled release mechanism. The unique internal and external surfaces of MSN were utilized for the development of a glucose-responsive double delivery system end-capped with insulin. This unique system consists of functionalized MSNs capable of releasing insulin when the concentration of sugar in blood exceeds healthy levels. The insulin-free nanoparticles are then up taken by pancreatic cells, and release inside of them another biomolecule that stimulates the production of more insulin. The in vivo application of this system for the treatment of diabetes requires further understanding on the biological behaviors of these nanoparticles in blood vessels. The research presented in this dissertation demonstrated the size and surface effects on the interaction of MSNs with red blood cell membranes, and discovered how the surface of the nanoparticles can be modified to improve their compatibility with red blood cells and avoid their dangerous side effects. In order to optimize the properties of MSN for applying them as efficient intracellular drug carriers it is necessary to understand the factors that can regulate their internalization into and exocytosis out of the cells. The correlation between the particle morphology and aggregation of MSNs to the effectiveness of cellular uptake is discussed and compared with different cell lines. The differences in the degree of exocytosis of MSNs between healthy and cancer cells is reported and found to be responsible for the asymmetric transfer of the particles between both cell types. The fundamental studies on the hemocompatibility, endo- and exocytosis of MSN along with its ability to sequentially release multiple therapeutics in response to different stimuli, allow us to propose MSN as an intravascular vehicle with a great potential for various biomedical applications.

Zhao, Yan

2011-05-15T23:59:59.000Z

300

Development and Application of an Oversize Reusable DOT 7A Type A Overpack Container at the Y-12 National Security Complex - 13150  

SciTech Connect (OSTI)

Waste Management personnel at the Y-12 National Security Complex (Y-12) are concluding a multi-year effort to dispose of a large backlog of low-level waste. Six containers presented a particularly difficult technical challenge in that they each contained large robust equipment (mostly salt baths) with elevated levels of highly enriched uranium (exceeding U.S. Department of Transportation (DOT) fissile-excepted quantities). The equipment was larger than the standard 1.2 m x 1.2 m x 1.8 m (4 ft x 4 ft x 6 ft) DOT Specification 7A Type A box and would have been very difficult to size-reduce because of several inches of steel plate (along with insulating block and concrete) in the equipment design. A critical breakthrough for the success of the project involved procuring and developing two oversize reusable DOT Specification 7A Type A (fissile tested) containers (referred to as the CTI Model 7AF-690-SC) that could be used as overpacks for the original boxes of equipment. The 7A Type A overpack containers are approximately 3.5 m long x 2.7 m wide x 2.8 m high (11.7 ft x 8.9 ft x 9.2 ft) with a maximum gross weight of 10,660 kg (23,500 lb) and a payload capacity of 6,804 kg (15,000 lbs). The boxes were designed and fabricated using a split cavity design that allowed the gasketed and bolted closure to lie along the horizontal centerline of the box. The central closure location in this design allows for strengthening of box corners that tend to be points of weakness or failure in 49CFR173.465 drop tests. By combining the split cavity design with large diameter tubing and diagonal cross bracing, drop test requirements of 49CFR173.465(1) and (2) were met and demonstrated through finite element analysis modeling. The development and use of this new container dramatically reduced the need for down-sizing the equipment and allowed the project to meet objectives within cost and schedule targets. (authors)

Tharp, Tim [B and W Technical Services Y-12, LLC, Oak Ridge, TN 37831 (United States)] [B and W Technical Services Y-12, LLC, Oak Ridge, TN 37831 (United States); Martin, David [Container Technologies Industries, LLC, Helenwood, TN 37755 (United States)] [Container Technologies Industries, LLC, Helenwood, TN 37755 (United States); Franco, Paul [Navarro Research and Engineering, Inc., Oak Ridge, TN 37831 (United States)] [Navarro Research and Engineering, Inc., Oak Ridge, TN 37831 (United States)

2013-07-01T23:59:59.000Z

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301

2-D linear motion system. Innovative technology summary report  

SciTech Connect (OSTI)

The US Department of Energy's (DOE's) nuclear facility decontamination and decommissioning (D and D) program requires buildings to be decontaminated, decommissioned, and surveyed for radiological contamination in an expeditious and cost-effective manner. Simultaneously, the health and safety of personnel involved in the D and D activities is of primary concern. D and D workers must perform duties high off the ground, requiring the use of manlifts or scaffolding, often, in radiologically or chemically contaminated areas or in areas with limited access. Survey and decontamination instruments that are used are sometimes heavy or awkward to use, particularly when the worker is operating from a manlift or scaffolding. Finding alternative methods of performing such work on manlifts or scaffolding is important. The 2-D Linear Motion System (2-D LMS), also known as the Wall Walker{trademark}, is designed to remotely position tools and instruments on walls for use in such activities as radiation surveys, decontamination, and painting. Traditional (baseline) methods for operating equipment for these tasks require workers to perform duties on elevated platforms, sometimes several meters above the ground surface and near potential sources of contamination. The Wall Walker 2-D LMS significantly improves health and safety conditions by facilitating remote operation of equipment. The Wall Walker 2-D LMS performed well in a demonstration of its precision, accuracy, maneuverability, payload capacity, and ease of use. Thus, this innovative technology is demonstrated to be a viable alternative to standard methods of performing work on large, high walls, especially those that have potential contamination concerns. The Wall Walker was used to perform a final release radiological survey on over 167 m{sup 2} of walls. In this application, surveying using a traditional (baseline) method that employs an aerial lift for manual access was 64% of the total cost of the improved technology. However, for areas over approximately 600 m{sup 2}, the Wall Walker would cost less than the baseline. Using the Wall Walker 2-D LMS, ALARA exposure and worker safety is improved, and there is potential for increased productivity. This innovative technology performed better than the baseline by providing real-time monitoring of the tool or instrument position. Also, the Wall Walker 2-D LMS can traverse any two-dimensional path at constant speeds of up to 18.3 linear meters per minute (60 linear feet per minute). The survey production rate for the innovative technology was about 0.6 m{sup 2}/min (6 ft{sup 2}/min); the baseline production rate was approximately 0.3 m{sup 2}/min (3 ft{sup 2}/min), using the same surveying instrument and maximum scanning rate.

NONE

1998-11-01T23:59:59.000Z

302

USED FUEL RAIL SHOCK AND VIBRATION TESTING OPTIONS ANALYSIS  

SciTech Connect (OSTI)

The objective of the rail shock and vibration tests is to complete the framework needed to quantify loads of fuel assembly components that are necessary to guide materials research and establish a technical basis for review organizations such as the U.S. Nuclear Regulatory Commission (NRC). A significant body of experimental and numerical modeling data exists to quantify loads and failure limits applicable to normal conditions of transport (NCT) rail transport, but the data are based on assumptions that can only be verified through experimental testing. The test options presented in this report represent possible paths for acquiring the data that are needed to confirm the assumptions of previous work, validate modeling methods that will be needed for evaluating transported fuel on a case-by-case basis, and inform material test campaigns on the anticipated range of fuel loading. The ultimate goal of this testing is to close all of the existing knowledge gaps related to the loading of used fuel under NCT conditions and inform the experiments and analysis program on specific endpoints for their research. The options include tests that would use an actual railcar, surrogate assemblies, and real or simulated rail transportation casks. The railcar carrying the cradle, cask, and surrogate fuel assembly payload would be moved in a train operating over rail track modified or selected to impart shock and vibration forces that occur during normal rail transportation. Computer modeling would be used to help design surrogates that may be needed for a rail cask, a casks internal basket, and a transport cradle. The objective of the design of surrogate components would be to provide a test platform that effectively simulates responses to rail shock and vibration loads that would be exhibited by state-of-the-art rail cask, basket, and/or cradle structures. The computer models would also be used to help determine the placement of instrumentation (accelerometers and strain gauges) on the surrogate fuel assemblies, cask and cradle structures, and the railcar so that forces and deflections that would result in the greatest potential for damage to high burnup and long-cooled UNF can be determined. For purposes of this report we consider testing on controlled track when we have control of the track and speed to facilitate modeling.

Ross, Steven B.; Best, Ralph E.; Klymyshyn, Nicholas A.; Jensen, Philip J.; Maheras, Steven J.

2014-09-29T23:59:59.000Z

303

Small Reactor Designs Suitable for Direct Nuclear Thermal Propulsion: Interim Report  

SciTech Connect (OSTI)

Advancement of U.S. scientific, security, and economic interests requires high performance propulsion systems to support missions beyond low Earth orbit. A robust space exploration program will include robotic outer planet and crewed missions to a variety of destinations including the moon, near Earth objects, and eventually Mars. Past studies, in particular those in support of both the Strategic Defense Initiative (SDI) and the Space Exploration Initiative (SEI), have shown nuclear thermal propulsion systems provide superior performance for high mass high propulsive delta-V missions. In NASA's recent Mars Design Reference Architecture (DRA) 5.0 study, nuclear thermal propulsion (NTP) was again selected over chemical propulsion as the preferred in-space transportation system option for the human exploration of Mars because of its high thrust and high specific impulse ({approx}900 s) capability, increased tolerance to payload mass growth and architecture changes, and lower total initial mass in low Earth orbit. The recently announced national space policy2 supports the development and use of space nuclear power systems where such systems safely enable or significantly enhance space exploration or operational capabilities. An extensive nuclear thermal rocket technology development effort was conducted under the Rover/NERVA, GE-710 and ANL nuclear rocket programs (1955-1973). Both graphite and refractory metal alloy fuel types were pursued. The primary and significantly larger Rover/NERVA program focused on graphite type fuels. Research, development, and testing of high temperature graphite fuels was conducted. Reactors and engines employing these fuels were designed, built, and ground tested. The GE-710 and ANL programs focused on an alternative ceramic-metallic 'cermet' fuel type consisting of UO2 (or UN) fuel embedded in a refractory metal matrix such as tungsten. The General Electric program examined closed loop concepts for space or terrestrial applications as well as open loop systems for direct nuclear thermal propulsion. Although a number of fast spectrum reactor and engine designs suitable for direct nuclear thermal propulsion were proposed and designed, none were built. This report summarizes status results of evaluations of small nuclear reactor designs suitable for direct nuclear thermal propulsion.

Bruce G. Schnitzler

2012-01-01T23:59:59.000Z

304

Advantages of the shielded containers at the Waste Isolation Pilot Plant.  

SciTech Connect (OSTI)

The Waste Isolation Pilot Plant (WIPP) disposal operations currently employ two different disposal methods: one for Contact Handled (CH) waste and another for Remote Handled (RH) waste. CH waste is emplaced in a variety of payload container configurations on the floor of each disposal room. In contrast, RH waste is packaged into a single type of canister and emplaced in pre-drilled holes in the walls of disposal rooms. Emplacement of the RH waste in the walls must proceed in advance of CH waste emplacement and therefore poses logistical constraints, in addition to the loss of valuable disposal capacity. To improve operational efficiency and disposal capacity, the Department of Energy (DOE) has proposed a shielded container for certain RH waste streams. RH waste with relatively low gammaemitting activity would be packaged in lead-lined containers, shipped to WIPP in existing certified transportation packages for CH waste and emplaced in WIPP among the stacks of CH waste containers on the floor of a disposal room. RH waste with high gamma-emitting activity would continue to be emplaced in the boreholes along the walls. The new RH container is similar to the nominal 208-liter (55-gallon) drum, however it includes about 2.5 cm (1 in) of lead, sandwiched between thick steel sheets. Furthermore, the top and bottom are made of thick plate steel to strengthening the package to meet transportation requirements. This robust configuration provides an overpack for materials that otherwise would be RH waste. This paper describes the container and the regulatory approach used to meet the requirements imposed by regulations that apply to WIPP. This includes a Performance Assessment used to evaluate WIPP's long-term performance and the DOE's approach to gain approval for the transportation of shielded containers. This paper also describes estimates of the DOE's RH transuranic waste inventory that may be packaged and emplaced in shielded containers. Finally, the paper includes a discussion of how the DOE proposes to track the waste packaged into shielded containers against the RH waste inventory and how this will comply with the regulated volume.

Nelson, Roger A. (U.S. Department of Energy, Carlsbad, NM); Dunagan, Sean C.

2010-05-01T23:59:59.000Z

305

UNDERFLIGHT CALIBRATION OF SOHO/CDS AND HINODE/EIS WITH EUNIS-07  

SciTech Connect (OSTI)

Flights of Goddard Space Flight Center's Extreme Ultraviolet Normal Incidence Spectrograph (EUNIS) sounding rocket in 2006 and 2007 provided updated radiometric calibrations for Solar and Heliospheric Observatory/Coronal Diagnostic Spectrometer (SOHO/CDS) and Hinode/Extreme Ultraviolet Imaging Spectrometer (Hinode/EIS). EUNIS carried two independent imaging spectrographs covering wavebands of 300-370 A in first order and 170-205 A in second order. After each flight, end-to-end radiometric calibrations of the rocket payload were carried out in the same facility used for pre-launch calibrations of CDS and EIS. During the 2007 flight, EUNIS, SOHO/CDS, and Hinode/EIS observed the same solar locations, allowing the EUNIS calibrations to be directly applied to both CDS and EIS. The measured CDS NIS 1 line intensities calibrated with the standard (version 4) responsivities with the standard long-term corrections are found to be too low by a factor of 1.5 due to the decrease in responsivity. The EIS calibration update is performed in two ways. One uses the direct calibration transfer of the calibrated EUNIS-07 short wavelength (SW) channel. The other uses the insensitive line pairs, in which one member was observed by the EUNIS-07 long wavelength (LW) channel and the other by EIS in either the LW or SW waveband. Measurements from both methods are in good agreement, and confirm (within the measurement uncertainties) the EIS responsivity measured directly before the instrument's launch. The measurements also suggest that the EIS responsivity decreased by a factor of about 1.2 after the first year of operation (although the size of the measurement uncertainties is comparable to this decrease). The shape of the EIS SW response curve obtained by EUNIS-07 is consistent with the one measured in laboratory prior to launch. The absolute value of the quiet-Sun He II 304 A intensity measured by EUNIS-07 is consistent with the radiance measured by CDS NIS in quiet regions near the disk center and the solar minimum irradiance recently obtained by CDS NIS and the Solar Dynamics Observatory/Extreme Ultraviolet Variability Experiment.

Wang Tongjiang; Brosius, Jeffrey W. [Institute for Astrophysics and Computational Sciences (IACS) in the Department of Physics, Catholic University of America, 620 Michigan Avenue NE, Washington, DC 20064 (United States); Thomas, Roger J.; Rabin, Douglas M.; Davila, Joseph M. [NASA Goddard Space Flight Center, Code 671, Greenbelt, MD 20771 (United States); Young, Peter R. [College of Science, George Mason University, 4400 University Drive, Fairfax, VA 22030 (United States); Del Zanna, Giulio, E-mail: tongjiang.wang@nasa.gov [DAMTP, Centre for Mathematical Sciences, University of Cambridge, Wilberforce Road, Cambridge, CB3 0WA (United Kingdom)

2011-12-01T23:59:59.000Z

306

Type B package for the transport of large medical and industrial sources  

SciTech Connect (OSTI)

AREVA Federal Services LLC, under contract to the Los Alamos National Laboratory's Offsite Source Recovery Project, is developing a new Type B(U)-96 package for the transport of unwanted or abandoned high activity gamma and neutron radioactive sealed sources (sources). The sources were used primarily in medical or industrial devices, and are of domestic (USA) or foreign origin. To promote public safety and mitigate the possibility of loss or misuse, the Offsite Source Recovery Project is recovering and managing sources worldwide. The package, denoted the LANL-B, is designed to accommodate the sources within an internal gamma shield. The sources are located either in the IAEA's Long Term Storage Shield (LTSS), or within intact medical or industrial irradiation devices. As the sources are already shielded separately, the package does not include any shielding of its own. A particular challenge in the design of the LANL-B has been weight. Since the LTSS shield weighs approximately 5,000 lb [2,270 kg], and the total package gross weight must be limited to 10,000 lb [4,540 kg], the net weight of the package was limited to 5,000 lb, for an efficiency of 50% (i.e., the payload weight is 50% of the gross weight of the package). This required implementation of a light-weight bell-jar concept, in which the containment takes the form of a vertical bell which is bolted to a base. A single impact limiter is used on the bottom, to protect the elastomer seals and bolted joint. A top-end impact is mitigated by the deformation of a tori spherically-shaped head. Impacts in various orientations on the bottom end are mitigated by a cylindrical, polyurethane foam-filled impact limiter. Internally, energy is absorbed using honeycomb blocks at each end, which fill the torispherical head volumes. As many of the sources are considered to be in normal form, the LANL-B package offers leak-tight containment using an elastomer seal at the joint between the bell and the base, as well as on the single vent port. Leak testing prior to transport may be either using helium mass spectrometry or the pressure-rise concept.

Brown, Darrell Dwaine [Los Alamos National Laboratory; Noss, Philip W [AREVA FEDERAL SERVICES

2010-09-14T23:59:59.000Z

307

Unmanned air vehicle (UAV) ultra-persitence research  

SciTech Connect (OSTI)

Sandia National Laboratories and Northrop Grumman Corporation Integrated Systems, Unmanned Systems (NGIS UMS) collaborated to further ultra-persistence technologies for unmanned air vehicles (UAVs). The greatest shortfalls in UAV capabilities have been repeatedly identified as (1) insufficient flight persistence or 'hang time,' (2) marginal electrical power for running higher power avionics and payload systems, and (3) inadequate communications bandwidth and reach. NGIS UMS requested support from Sandia to develop an ultra-persistent propulsion and power system (UP3S) for potential incorporation into next generation UAV systems. The team members tried to determine which energy storage and power generation concepts could most effectively push UAV propulsion and electrical power capabilities to increase UAV sortie duration from days to months while increasing available electrical power at least two-fold. Primary research and development areas that were pursued included these goals: perform general system engineering and integration analyses; develop initial thermal and electrical power estimates; provide mass, volume, dimensional, and balance estimates; conduct preliminary safety assessments; assess logistics support requirements; perform, preliminary assessments of any security and safeguards; evaluate options for removal, replacement, and disposition of materials; generally advance the potential of the UP3S concept. The effort contrasted and compared eight heat sources technologies, three power conversion, two dual cycle propulsion system configurations, and a single electrical power generation scheme. Overall performance, specific power parameters, technical complexities, security, safety, and other operational features were successfully investigated. Large and medium sized UAV systems were envisioned and operational flight profiles were developed for each concept. Heat source creation and support challenges for domestic and expeditionary operations were considered. Fundamental cost driver analysis was also performed. System development plans were drafted in order to determine where the technological and programmatic critical paths lay. As a result of this effort, UAVs were to be able to provide far more surveillance time and intelligence information per mission while reducing the high cost of support activities. This technology was intended to create unmatched global capabilities to observe and preempt terrorist and weapon of mass destruction (WMD) activities. Various DOE laboratory and contractor personnel and facilities could have been used to perform detailed engineering, fabrication, assembly and test operations including follow-on operational support. Unfortunately, none of the results will be used in the near-term or mid-term future. NGIS UMS and SNL felt that the technical goals for the project were accomplished. NGIS UMS was quite pleased with the results of analysis and design although it was disappointing to all that the political realities would not allow use of the results. Technology and system designs evaluated under this CRADA had previously never been applied to unmanned air vehicles (UAVs). Based upon logistic support cost predictions, because the UAVs would not have had to refuel as often, forward basing support costs could have been reduced due to a decrease in the number and extent of support systems and personnel being required to operate UAVs in remote areas. Basic application of the advanced propulsion and power approach is well understood and industry now understands the technical, safety, and political issues surrounding implementation of these strategies. However, the overall economic impact was not investigated. The results will not be applied/implemented. No near-term benefit to industry or the taxpayer will be encountered as a result of these studies.

Dron, S. B.

2012-03-01T23:59:59.000Z

308

U.S. Department of Energy FreedomCAR and Vehicle Technologies Program Advanced Vehicle Testing Activity Federal Fleet Use of Electric Vehicles  

SciTech Connect (OSTI)

Per Executive Order 13031, Federal Alternative Fueled Vehicle Leadership, the U.S. Department of Energys (DOEs) Advanced Vehicle Testing Activity provided $998,300 in incremental funding to support the deployment of 220 electric vehicles in 36 Federal fleets. The 145 electric Ford Ranger pickups and 75 electric Chrysler EPIC (Electric Powered Interurban Commuter) minivans were operated in 14 states and the District of Columbia. The 220 vehicles were driven an estimated average of 700,000 miles annually. The annual estimated use of the 220 electric vehicles contributed to 39,000 fewer gallons of petroleum being used by Federal fleets and the reduction in emissions of 1,450 pounds of smog-forming pollution. Numerous attempts were made to obtain information from all 36 fleets. Information responses were received from 25 fleets (69% response rate), as some Federal fleet personnel that were originally involved with the Incremental Funding Project were transferred, retired, or simply could not be found. In addition, many of the Department of Defense fleets indicated that they were supporting operations in Iraq and unable to provide information for the foreseeable future. It should be noted that the opinions of the 25 fleets is based on operating 179 of the 220 electric vehicles (81% response rate). The data from the 25 fleets is summarized in this report. Twenty-two of the 25 fleets reported numerous problems with the vehicles, including mechanical, traction battery, and charging problems. Some of these problems, however, may have resulted from attempting to operate the vehicles beyond their capabilities. The majority of fleets reported that most of the vehicles were driven by numerous drivers each week, with most vehicles used for numerous trips per day. The vehicles were driven on average from 4 to 50 miles per day on a single charge. However, the majority of the fleets reported needing gasoline vehicles for missions beyond the capabilities of the electric vehicles, usually because of range limitations. Twelve fleets reported experiencing at least one charge depletion while driving, whereas nine fleets reported not having this problem. Twenty-four of the 25 fleets responded that the electric vehicles were easy to use and 22 fleets indicated that the payload was adequate. Thirteen fleets reported charging problems; eleven fleets reported no charging problems. Nine fleets reported the vehicles broke down while driving; 14 fleets reported no onroad breakdowns. Some of the breakdowns while driving, however, appear to include normal flat tires and idiot lights coming on. In spite of operation and charging problems, 59% of the fleets responded that they were satisfied, very satisfied, or extremely satisfied with the performance of the electric vehicles. As of September 2003, 74 of the electric vehicles were still being used and 107 had been returned to the manufacturers because the leases had concluded.

Mindy Kirpatrick; J. E. Francfort

2003-11-01T23:59:59.000Z

309

LIFETIME PREDICTION FOR MODEL 9975 O-RINGS IN KAMS  

SciTech Connect (OSTI)

The Savannah River Site (SRS) is currently storing plutonium materials in the K-Area Materials Storage (KAMS) facility. The materials are packaged per the DOE 3013 Standard and transported and stored in KAMS in Model 9975 shipping packages, which include double containment vessels sealed with dual O-rings made of Parker Seals compound V0835-75 (based on Viton{reg_sign} GLT). The outer O-ring of each containment vessel is credited for leaktight containment per ANSI N14.5. O-ring service life depends on many factors, including the failure criterion, environmental conditions, overall design, fabrication quality and assembly practices. A preliminary life prediction model has been developed for the V0835-75 O-rings in KAMS. The conservative model is based primarily on long-term compression stress relaxation (CSR) experiments and Arrhenius accelerated-aging methodology. For model development purposes, seal lifetime is defined as a 90% loss of measurable sealing force. Thus far, CSR experiments have only reached this target level of degradation at temperatures {ge} 300 F. At lower temperatures, relaxation values are more tolerable. Using time-temperature superposition principles, the conservative model predicts a service life of approximately 20-25 years at a constant seal temperature of 175 F. This represents a maximum payload package at a constant ambient temperature of 104 F, the highest recorded in KAMS to date. This is considered a highly conservative value as such ambient temperatures are only reached on occasion and for short durations. The presence of fiberboard in the package minimizes the impact of such temperature swings, with many hours to several days required for seal temperatures to respond proportionately. At 85 F ambient, a more realistic but still conservative value, bounding seal temperatures are reduced to {approx}158 F, with an estimated seal lifetime of {approx}35-45 years. The actual service life for O-rings in a maximum wattage package likely lies higher than the estimates due to the conservative assumptions used for the model. For lower heat loads at similar ambient temperatures, seal lifetime is further increased. The preliminary model is based on several assumptions that require validation with additional experiments and longer exposures at more realistic conditions. The assumption of constant exposure at peak temperature is believed to be conservative. Cumulative damage at more realistic conditions will likely be less severe but is more difficult to assess based on available data. Arrhenius aging behavior is expected, but non-Arrhenius behavior is possible. Validation of Arrhenius behavior is ideally determined from longer tests at temperatures closer to actual service conditions. CSR experiments will therefore continue at lower temperatures to validate the model. Ultrasensitive oxygen consumption analysis has been shown to be useful in identifying non-Arrhenius behavior within reasonable test periods. Therefore, additional experiments are recommended and planned to validate the model.

Hoffman, E.; Skidmore, E.

2009-11-24T23:59:59.000Z

310

Development of autonomous magnetometer rotorcraft for wide area assessment  

SciTech Connect (OSTI)

Large areas across the United States are potentially contaminated with UXO, with some ranges encompassing tens to hundreds of thousands of acres. Technologies are needed which will allow for cost effective wide area scanning with 1) near 100 % coverage and 2) near 100 % detection of subsurface ordnance or features indicative of subsurface ordnance. The current approach to wide area assessment is a multi-level one, in which medium - altitude fixed wing optical imaging is used for an initial site assessment. This assessment is followed with low altitude manned helicopter based magnetometry. Subsequent to this wide area assessment targeted surface investigations are performed using either towed geophysical sensor arrays or man portable sensors. In order to be an effective tool for small UXO detection, the sensing altitude for magnetic site investigations needs to be on the order of 1 3 meters. These altitude requirements mean that manned helicopter surveys will generally only be feasible in large, open and relatively flat terrains. While such surveys are effective in mapping large areas relatively fast there are substantial mobilization/demobilization, staffing and equipment costs associated with these surveys (resulting in costs of approximately $100-$150/acre). In addition, due to the low altitude there are substantial risks to pilots and equipment. Surface towed arrays provide high resolution maps but have other limitations, e.g. in their ability to navigate rough terrain effectively. There is thus a need for other systems which can be used for effective data collection. An UAV (Unmanned Aerial Vehicle) magnetometer platform is an obvious alternative. The motivation behind such a system is that it reduces risk to operators, is lower in initial and Operational and Maintenance (O&M) costs (and can thus potentially be applied to smaller sites) and has the potential of being more effective in terms of detection and possibly characterization (through the use of dynamic acquisition, i.e. survey mission inflight reprioritization). We describe and report on a one year effort with as primary goal to provide a recommendation to SERDP for a path forward in the implementation of one or more autonomous unmanned magnetometer rotorcraft platforms. This recommendation (which is provided in chapter 6) is based on the following three elements a) An assessment on the applicability of autonomous rotorcraft magnetometer systems to the current DoD site inventory, and an initial assessment of which type(s) of autonomous unmanned magnetometer rotorcraft platforms (in terms of performance characteristics such as payload, altitude, obstacle avoidance, production rate and flight time) would be most relevant to this inventory (chapter 3); b) An evaluation of the feasibility of assembling such platforms from commercial components (unmanned rotorcraft, control systems and sensors both magnetometer sensors and supporting sensors). This evaluation included several highly successful field tests (chapter 4 and 5); c) A recommendation of the path forward, which includes a detailed outline of the efforts required in the design, assembly and testing of different modular platforms (chapter 6)

Roelof Versteeg; Matt Anderson; Les Beard; Eric Corban; Darryl Curley; Jeff Gamey; Ross Johnson; Dwight Junkin; Mark McKay; Jared Salzmann; Mikhail Tchernychev; Suraj Unnikrishnan; Scott Vinson

2010-04-01T23:59:59.000Z

311

Waste Isolation Pilot Plant Status and Plans - 2012 - 12049  

SciTech Connect (OSTI)

The Waste Isolation Pilot Plant (WIPP), a deep geologic repository for safe disposal of long-lived transuranic radioactive waste related to the nation's defense, is completing its 12. year of operations. WIPP's mission includes coordination of all Department of Energy (DOE) sites to prepare, package and characterize transuranic (TRU) waste for final shipment and emplacement in WIPP. Five of the 10 disposal panels planned have been filled and sealed from ventilation. Additional small quantity sites have been de-inventoried by consolidating their waste through the certified characterization line at the Idaho National Laboratory (INL). New emplacement methods for RH waste in shielded containers are being considered for disposal by WIPP's regulatory authorities. A new large Type B shipping package, was added to the WIPP transportation fleet, and facility modifications to the WIPP waste unloading and emplacement processes for large containers were completed in 2011. Shipments from the Savannah River site in these new large rectangular packages began in August 2011. Licensing efforts are proceeding for a new criticality control over-pack container that will allow almost twice the fissile content to be shipped than previously. This will reduce the number and cost of shipments of Special Nuclear Material (SNM) declared as waste. Modifications to WIPP regulatory requirements for the disposal footprint and disposal unit closure systems are in progress. These, and other developments, make for exciting times at WIPP. This paper provides an up-to-date look at the many aspects of America's only deep geologic long-lived radioactive waste repository, which is completing its 12. year of operations. A record year of safe and compliant shipments to WIPP tops the list of accomplishments in 2011. Four more small quantity sites were de-inventoried by consolidating their waste through the certified characterization line at INL in 2011. A new Type B shipping package, the TRUPACT-III has been added to the transportation fleet, and large waste boxes are being shipped from SRS without the need for repackaging. New emplacement methods for remote-handled waste in shielded containers are undergoing regulatory review. WIPP plans to license a new criticality control payload container that will allow almost twice the fissile content to be shipped than previously, thereby reducing the number and cost of shipments of SNM declared as waste. Other regulatory modifications planned in 2012 include approval of a design change that would replace the disposal concept for panels 9 and 10 from using the common access drifts (the 'mains') with a new footprint south of panels 4 and 5. DOE also plans to change the panel closure design set forth in its certification by EPA and the HWFP by the NMED. The panel closure design change will be a rule making under EPA's procedures and a class 3 permit modification request under NMED procedures. Plans for achieving 90% of legacy TRU waste retrieval and emplacement in WIPP by 2015 have been developed. Key to the success of this so-called 90/15 plan is adequate funding, both for WIPP operations, as well as for TRU retrieval programs at the generator sites. (authors)

Nelson, Roger A.; Ziemianski, Edward J. [U.S. Department of Energy, Carlsbad, NM 88220 (United States)

2012-07-01T23:59:59.000Z

312

Medium Truck Duty Cycle Data from Real-World Driving Environments: Project Interim Report  

SciTech Connect (OSTI)

Since the early part of the 20th century, the US trucking industry has provided a safe and economical means of moving commodities across the country. At the present time, nearly 80% of the US domestic freight movement involves the use of trucks. The US Department of Energy (DOE) is spearheading a number of research efforts to improve heavy vehicle fuel efficiencies. This includes research in engine technologies (including hybrid and fuel cell technologies), lightweight materials, advanced fuels, and parasitic loss reductions. In addition, DOE is developing advanced tools and models to support heavy vehicle truck research, and is leading the 21st Century Truck Partnership whose stretch goals involve a reduction by 50% of the fuel consumption of heavy vehicles on a ton-mile basis. This Medium Truck Duty Cycle (MTDC) Project is a critical element in DOE s vision for improved heavy vehicle energy efficiency and is unique in that there is no other national database of characteristic duty cycles for medium trucks. It involves the collection of real-world data for various situational characteristics (rural/urban, freeway/arterial, congested/free-flowing, good/bad weather, etc.) and looks at the unique nature of medium trucks drive cycles (stop-and-go delivery, power takeoff, idle time, short-radius trips), to provide a rich source of data that can contribute to the development of new tools for fuel efficiency and modeling, provide DOE a sound basis upon which to make technology investment decisions, and provide a national archive of real-world-based medium-truck operational data to support heavy vehicle energy efficiency research. The MTDC project involves a two-part field operational test (FOT). For the Part-1 FOT, three vehicles, each from two vocations (urban transit and dry-box delivery) were instrumented for one year of data collection. The Part-2 FOT will involve the towing/recovery and utility vocations. The vehicles participating in the MTDC project are doing so through gratis partnerships in return for early access to the results of this study. Partnerships such as these are critical to FOTs in which real-world data is being collected. In Part 1 of the project, Oak Ridge National Laboratory(ORNL) established partnerships with the H.T. Hackney Company, one of the largest wholesale distributors in the country, distributing products to 21 states; and with the Knoxville Area Transit (KAT), the City of Knoxville s transit system, operating services across the city of Knoxville and parts of Knox co. These partnerships and agreements provided ORNL access to three Class-7 2005/2007 International day-cab tractors, model 8600, which regularly haul 28 ft pup trailers (H.T. Hackney Co) and three Class-7 2005 Optima LF-34 buses (KAT), for collection of duty cycle data. In addition, ORNL has collaborated with the Federal Motor Carrier Safety Administration (FMCSA) to determine if there were possible synergies between this duty cycle data collection effort and FMCSA s need to learn more about the operation and duty cycles of the second-largest fuel consuming commercial vehicle category in the US. FMCSA s primary interest was in collecting safety data relative to the driver, carrier, and vehicle. In order to collect the duty cycle and safety-related data, ORNL developed a data acquisition and wireless communication system that was placed on each test vehicle. Each signal recorded in this FOT was collected by means of one of the instruments incorporated into each data acquisition system (DAS). Native signals were obtained directly from the vehicle s J1939 and J1708 data buses. A VBOX II Lite collected Global Positioning System related information including speed, acceleration, and spatial location information at a rate of 5 Hz, and communicated this data via the CAN (J1939) protocol. The Air-Weigh LoadMaxx, a self-weighing system which determines the vehicle s gross weight by means of pressure transducers and posts the weight to the vehicle s J1939 data bus, was used to collect vehicle payload information. A cellular modem, the Raven X

Franzese, Oscar [ORNL; Lascurain, Mary Beth [ORNL; Capps, Gary J [ORNL

2011-01-01T23:59:59.000Z