National Library of Energy BETA

Sample records for nasa jet propulsion

  1. http://smap.jpl.nasa.gov Jet Propulsion Laboratory

    E-Print Network [OSTI]

    Mojzsis, Stephen J.

    http://smap.jpl.nasa.gov Jet Propulsion Laboratory California Institute of Technology SMAP SAR* On-Orbit Misalignment Calibration Dynamics & Control, Jet Propulsion Laboratory, Pasadena, CA *Synthetic Aperture Radar #12;Jet Propulsion Laboratory California Institute of Technology Jet Propulsion Laboratory California

  2. Batteries and fuel cell research Sri Narayan worked for 20 years at NASA's Jet Propulsion Laboratory (JPL) where he led the

    E-Print Network [OSTI]

    Levi, Anthony F. J.

    Batteries and fuel cell research Sri Narayan worked for 20 years at NASA's Jet Propulsion Laboratory (JPL) where he led the fuel cell research activities for over 15 years and also headed the development of direct methanol fuel cell power sources for military and commercial applications, developed new

  3. Jet propulsion without inertia

    E-Print Network [OSTI]

    Saverio E. Spagnolie; Eric Lauga

    2010-05-04

    A body immersed in a highly viscous fluid can locomote by drawing in and expelling fluid through pores at its surface. We consider this mechanism of jet propulsion without inertia in the case of spheroidal bodies, and derive both the swimming velocity and the hydrodynamic efficiency. Elementary examples are presented, and exact axisymmetric solutions for spherical, prolate spheroidal, and oblate spheroidal body shapes are provided. In each case, entirely and partially porous (i.e. jetting) surfaces are considered, and the optimal jetting flow profiles at the surface for maximizing the hydrodynamic efficiency are determined computationally. The maximal efficiency which may be achieved by a sphere using such jet propulsion is 12.5%, a significant improvement upon traditional flagella-based means of locomotion at zero Reynolds number. Unlike other swimming mechanisms which rely on the presentation of a small cross section in the direction of motion, the efficiency of a jetting body at low Reynolds number increases as the body becomes more oblate, and limits to approximately 162% in the case of a flat plate swimming along its axis of symmetry. Our results are discussed in the light of slime extrusion mechanisms occurring in many cyanobacteria.

  4. NASA's progress in nuclear electric propulsion technology

    SciTech Connect (OSTI)

    Stone, J.R.; Doherty, M.P.; Peecook, K.M.

    1993-01-01

    The National Aeronautics and Space Administration (NASA) has established a requirement for Nuclear Electric Propulsion (NEP) technology for robotic planetary science mission applications with potential future evolution to systems for piloted Mars vehicles. To advance the readiness of NEP for these challenging missions, a near-term flight demonstration on a meaningful robotic science mission is very desirable. The requirements for both near-term and outer planet science missions are briefly reviewed, and the near-term baseline system established under a recent study jointly conducted by the Lewis Research Center (LeRC) and the Jet Propulsion Laboratory (JPL) is described. Technology issues are identified where work is needed to establish the technology for the baseline system, and technology opportunities which could provide improvement beyond baseline capabilities are discussed. Finally, the plan to develop this promising technology is presented and discussed. 19 refs.

  5. NASA's progress in nuclear electric propulsion technology

    SciTech Connect (OSTI)

    Stone, J.R.; Doherty, M.P.; Peecook, K.M.

    1993-06-01

    The National Aeronautics and Space Administration (NASA) has established a requirement for Nuclear Electric Propulsion (NEP) technology for robotic planetary science mission applications with potential future evolution to systems for piloted Mars vehicles. To advance the readiness of NEP for these challenging missions, a near-term flight demonstration on a meaningful robotic science mission is very desirable. The requirements for both near-term and outer planet science missions are briefly reviewed, and the near-term baseline system established under a recent study jointly conducted by the Lewis Research Center (LeRC) and the Jet Propulsion Laboratory (JPL) is described. Technology issues are identified where work is needed to establish the technology for the baseline system, and technology opportunities which could provide improvement beyond baseline capabilities are discussed. Finally, the plan to develop this promising technology is presented and discussed.

  6. M. Bahrami ENSC 461 (S 11) Jet Propulsion Cycle 1 Ideal JetPropulsion Cycle

    E-Print Network [OSTI]

    Bahrami, Majid

    M. Bahrami ENSC 461 (S 11) Jet Propulsion Cycle 1 Ideal JetPropulsion Cycle Gas-turbine engines. Aircraft gas turbines operate on an open cycle called jet-propulsion cycle. Some of the major differences between the gas-turbine and jet-propulsion cycles are: gases are expanded in the turbine to a pressure

  7. JET PROPULSION WITHOUT INERTIA Saverio E. Spagnolie

    E-Print Network [OSTI]

    in and expelling fluid through pores at its surface. We consider this mechanism of jet propulsion without inertia://www.ima.umn.edu #12;Jet propulsion without inertia Saverio E. Spagnolie and Eric Lauga Department of MechanicalJET PROPULSION WITHOUT INERTIA By Saverio E. Spagnolie and Eric Lauga IMA Preprint Series # 2322

  8. Jet propulsion without inertia Saverio E. Spagnoliea

    E-Print Network [OSTI]

    Lauga, Eric

    fluid through pores at its surface. We consider this mechanism of jet propulsion without inertiaJet propulsion without inertia Saverio E. Spagnoliea and Eric Laugab Department of Mechanical corrected 23 August 2010 A body immersed in a highly viscous fluid can locomote by drawing in and expelling

  9. NASA's nuclear electric propulsion technology project

    SciTech Connect (OSTI)

    Stone, J.R.; Sovey, J.S. (NASA, Lewis Research Center, Cleveland, OH (United States))

    1992-07-01

    The National Aeronautics and Space Administration (NASA) has initiated a program to establish the readiness of nuclear electric propulsion (NEP) technology for relatively near-term applications to outer planet robotic science missions with potential future evolution to system for piloted Mars vehicles. This program was initiated in 1991 with a very modest effort identified with nuclear thermal propulsion (NTP); however, NEP is also an integral part of this program and builds upon NASA's Base Research and Technology Program in power and electric propulsion as well as the SP-100 space nuclear power program. The NEP Program will establish the feasibility and practicality of electric propulsion for robotic and piloted solar system exploration. The performance objectives are high specific impulse (200 greater than I(sub sp) greater than 10000 s), high efficiency (over 0.50), and low specific mass. The planning for this program was initially focussed on piloted Mars missions, but has since been redirected to first focus on 100-kW class systems for relatively near-term robotic missions, with possible future evolution to megawatt-and multi-megawatt-class systems applicable to cargo vehicles supporting human missions as well as to the piloted vehicles. This paper reviews current plans and recent progress for the overall nuclear electric propulsion project and closely related activities. 33 refs.

  10. JET PROPULSION LABORATORY 1979 Annual Report

    E-Print Network [OSTI]

    JET PROPULSION LABORATORY 1979 Annual Report #12;(Cover) 10, one of Jupiter's largest moons cloud cover. The remote-sensing capability was developed byIPL for Seasat ocean observations at IPL, and that gives the people who work here astrong sense ofpride, identity, and purpose. I see

  11. MEDIA RELATIONS OFFICE JET PROPULSION LABORATORY

    E-Print Network [OSTI]

    Christian, Eric

    MEDIA RELATIONS OFFICE JET PROPULSION LABORATORY CALIFORNIA INSTITUTE OF TECHNOLOGY NATIONAL FROM SHATTERED STAR The signal of a cataclysmic magnetic flare emanating from a star that cracked apart about some of the most unusual stars in the universe. The magnetic burst from the star SGR1900

  12. PUBLIC INFORMATION OFFICE JET PROPULSION LABORATORY

    E-Print Network [OSTI]

    Christian, Eric

    PUBLIC INFORMATION OFFICE JET PROPULSION LABORATORY CALIFORNIA INSTITUTE OF TECHNOLOGY NATIONAL are above the current sheet, they detect magnetic fields directed outward from the sun. When spacecraft observing magnetic field lines pointing inward only," Marsden said. A pair of magnetometers, each able

  13. Nuclear Thermal Propulsion: A Joint NASA/DOE/DOD Workshop

    SciTech Connect (OSTI)

    Clark, J.S.

    1991-01-01

    Papers presented at the joint NASA/DOE/DOD workshop on nuclear thermal propulsion are compiled. The following subject areas are covered: nuclear thermal propulsion programs; Rover/NERVA and NERVA systems; Low Pressure Nuclear Thermal Rocket (LPNTR); particle bed reactor nuclear rocket; hybrid propulsion systems; wire core reactor; pellet bed reactor; foil reactor; Droplet Core Nuclear Rocket (DCNR); open cycle gas core nuclear rockets; vapor core propulsion reactors; nuclear light bulb; Nuclear rocket using Indigenous Martian Fuel (NIMF); mission analysis; propulsion and reactor technology; development plans; and safety issues.

  14. JET PROPULSION LAB 0 RAT 0 R Y

    E-Print Network [OSTI]

    Waliser, Duane E.

    JET PROPULSION LAB 0 RAT 0 R Y ANN U A L REP 0 R T #12;#12;------ - - ~ CON TEN T S DIRECTOR Administration for the penod January 1 through December 31, 1986. JET PROPULSION LABORATORY Califorrua Institute, Voyager 2 gave us our first close view of the distant giant Uranus, its complex rings, inclined magnetic

  15. JET PROPULSION LABORATORY 1987 ANNUAL REPORT (Cover) At the heart of the

    E-Print Network [OSTI]

    JET PROPULSION LABORATORY 1987 ANNUAL REPORT #12;(Cover) At the heart of the hypercube, which and developed at IPL in 1987 and is one of many technological advances that took place this year, a year filled of fields described in this report. The year reported here, 1987, was a period of progress to help NASA

  16. 1997A N N U A L R E P O R T Jet Propulsion Laboratory

    E-Print Network [OSTI]

    to new positions on top of what is probably soft ice or ice-crusted water. observing NASA's Galileo1997A N N U A L R E P O R T Jet Propulsion Laboratory #12;Below:This 360-degree panorama

  17. Nuclear electric propulsion: An integral part of NASA's nuclear propulsion project

    SciTech Connect (OSTI)

    Stone, J.R.

    1992-01-01

    NASA has initiated a technology program to establish the readiness of nuclear propulsion technology for the Space Exploration Initiative (SEI). This program was initiated with a very modest effort identified with nuclear thermal propulsion (NTP); however, nuclear electric propulsion (NEP) is also an integral part of this program and builds upon NASA's Base Research and Technology Program in power and electric propulsion as well as the SP-100 space nuclear power program. Although the Synthesis Group On America's SEI has identified NEP only as an option for cargo missions, recent studies conducted by NASA-Lewis show that NEP offers the potential for early manned Mars missions as well. Lower power NEP is also of current interest for outer planetary robotic missions. Current plans are reviewed for the overall nuclear propulsion project, with emphasis on NEP and those elements of NTP program which have synergism with NEP.

  18. n a press conference on September 12, NASA announced that Voyager

    E-Print Network [OSTI]

    . This resilient robot, built by NASA's Jet Propulsion Laboratory (JPL), had burst through the sun's magnetic

  19. Nuclear electric propulsion for future NASA space science missions

    SciTech Connect (OSTI)

    Yen, Chen-wan L.

    1993-07-20

    This study has been made to assess the needs, potential benefits and the applicability of early (circa year 2000) Nuclear Electric Propulsion (NEP) technology in conducting NASA science missions. The study goals are: to obtain the performance characteristics of near term NEP technologies; to measure the performance potential of NEP for important OSSA missions; to compare NEP performance with that of conventional chemical propulsion; to identify key NEP system requirements; to clarify and depict the degree of importance NEP might have in advancing NASA space science goals; and to disseminate the results in a format useful to both NEP users and technology developers. This is a mission performance study and precludes investigations of multitudes of new mission operation and systems design issues attendant in a NEP flight.

  20. Vortex Rings in Bio-inspired and Biological Jet Propulsion Paul S. Krueger1, a

    E-Print Network [OSTI]

    Horth, Lisa

    of the latter, vortex rings are generated by the transient ejection of a jet from a tube or orifice, which leadsVortex Rings in Bio-inspired and Biological Jet Propulsion Paul S. Krueger1, a , Ali A. Moslemi1,b@odu.edu, e wstewart@uci.edu Keywords: Vortex rings, pulsed jets, propulsion, thrust, propulsive efficiency

  1. SUNITA PAYRA VERMA Jet Propulsion Laboratory, California Institute of Technology

    E-Print Network [OSTI]

    Associate · In project entitled "Scale up to obtain super clean coal - Organo-refining and identification1 SUNITA PAYRA VERMA Jet Propulsion Laboratory, California Institute of Technology M/S 183 2001- 2005 Centre for Atmospheric Sciences Indian Institute of Technology Delhi (IIT Delhi), India

  2. PUBLIC INFORMATION OFFICE JET PROPULSION LABORATORY

    E-Print Network [OSTI]

    Christian, Eric

    Force Operational Test and Evaluation Center, assigned to the Los Angeles Air Force Base, Calif. Before in the Space Defense Systems Air Force Space Division, Los Angeles Air Force Base, Calif. In his earlier Air communications and scientific data collection for the highly productive Ulysses mission, a joint mission of NASA

  3. Many squid rely on jet propulsion for locomotion, which is inherently less efficient than the undulatory/oscillatory

    E-Print Network [OSTI]

    Horth, Lisa

    Many squid rely on jet propulsion for locomotion, which is inherently less efficient than the undulatory/oscillatory locomotion employed by many fishes (Vogel, 1994). Jet propulsion is thought through an orifice, thus expelling relatively small volumes of water backwards with each jet pulse

  4. Innovative nuclear thermal propulsion technology evaluation: Results of the NASA/DOE Task Team study

    SciTech Connect (OSTI)

    Howe, S. (Los Alamos National Lab., NM (United States)); Borowski, S. (National Aeronautics and Space Administration, Cleveland, OH (United States). Lewis Research Center); Motloch, C. (EG and G Idaho, Inc., Idaho Falls, ID (United States)); Helms, I. (Nuclear Utility Services, Damascus, MD (United States)); Diaz, N.; Anghaie, S. (Florida Univ., Gainesville, FL (United States)); Latham, T. (United

    1991-01-01

    In response to findings from two NASA/DOE nuclear propulsion workshops held in the summer of 1990, six task teams were formed to continue evaluation of various nuclear propulsion concepts. The Task Team on Nuclear Thermal Propulsion (NTP) created the Innovative Concepts Subpanel to evaluate thermal propulsion concepts which did not utilize solid fuel. The Subpanel endeavored to evaluate each of the concepts on a level technological playing field,'' and to identify critical technologies, issues, and early proof-of-concept experiments. The concepts included the liquid core fission, the gas core fission, the fission foil reactors, explosively driven systems, fusion, and antimatter. The results of the studies by the panel will be provided. 13 refs., 6 figs., 2 tabs.

  5. The rationale/benefits of nuclear thermal rocket propulsion for NASA's lunar space transportation system

    SciTech Connect (OSTI)

    Borowski, S.K.

    1994-09-01

    The solid core nuclear thermal rocket (NTR) represents the next major evolutionary step in propulsion technology. With its attractive operating characteristics, which include high specific impulse (approximately 850-1000 s) and engine thrust-to-weight (approximately 4-20), the NTR can form the basis for an efficient lunar space transportation system (LTS) capable of supporting both piloted and cargo missions. Studies conducted at the NASA Lewis Research Center indicate that an NTR-based LTS could transport a fully-fueled, cargo-laden, lunar excursion vehicle to the Moon, and return it to low Earth orbit (LEO) after mission completion, for less initial mass in LEO than an aerobraked chemical system of the type studied by NASA during its '90-Day Study.' The all-propulsive NTR-powered LTS would also be 'fully reusable' and would have a 'return payload' mass fraction of approximately 23 percent--twice that of the 'partially reusable' aerobraked chemical system. Two NTR technology options are examined--one derived from the graphite-moderated reactor concept developed by NASA and the AEC under the Rover/NERVA (Nuclear Engine for Rocket Vehicle Application) programs, and a second concept, the Particle Bed Reactor (PBR). The paper also summarizes NASA's lunar outpost scenario, compares relative performance provided by different LTS concepts, and discusses important operational issues (e.g., reusability, engine 'end-of life' disposal, etc.) associated with using this important propulsion technology.

  6. LABORATORY ASTROPHYSICS WHITE PAPER (BASED ON THE 2010 NASA LABORATORY ASTROPHYSICS WORKSHOP

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    Savin, Daniel Wolf

    1 LABORATORY ASTROPHYSICS WHITE PAPER (BASED ON THE 2010 NASA LABORATORY ASTROPHYSICS WORKSHOP Federman, University of Toledo Paul Goldsmith, NASA Jet Propulsion Laboratory Caroline Kilbourne, NASA Ridge National Laboratory, LOC Chair Susanna Widicus Weaver, Emory University Additional contributions

  7. Five blind men and the elephant: what can the NASA Aura ozone measurements tell us about stratosphere-troposphere exchange?

    E-Print Network [OSTI]

    Tang, Q.; Prather, M. J

    2012-01-01

    JPL Publication 06–2, NASA/JPL, Jet Propulsion Laboratory,This work is funded by NASA grant (NNX08AR25G) to UCI andthe elephant: what can the NASA Aura ozone measurements tell

  8. K-means in Space: A Radiation Sensitivity Evaluation Kiri L. Wagstaff kiri.wagstaff@jpl.nasa.gov

    E-Print Network [OSTI]

    Wagstaff, Kiri L.

    .wagstaff@jpl.nasa.gov Benjamin Bornstein benjamin.bornstein@jpl.nasa.gov Jet Propulsion Laboratory, California Institute in smaller, cheaper, and faster unhardened RAM. No one has yet examined the innate radiation tolerance (or

  9. Nuclear electric propulsion for planetary science missions: NASA technology program planning

    SciTech Connect (OSTI)

    Doherty, M.P. (NASA Lewis Research Center, 21000 Brookpark Rd., Cleveland, Ohio 44135 (United States))

    1993-01-10

    This paper presents the status of technology program planning to achieve readiness of Nuclear Electric Propulsion technologies needed to meet the advanced propulsion system requirements for planetary science missions in the next century. The technology program planning is based upon technologies of significant maturity: ion electric propulsion and the SP-100 space nulcear power technologies. Detailed plans are presented herein for the required ion electric propulsion technology development and demonstration. Closer coordination between space nuclear power and space electric propulsion technology programs is a necessity as technology plans are being further refined in light of NEP concept definition and possible early NEP flight activities.

  10. Nuclear electric propulsion for planetary science missions: NASA technology program planning

    SciTech Connect (OSTI)

    Doherty, M.P.

    1993-05-01

    This paper presents the status of technology program planning to develop those Nuclear Electric Propulsion technologies needed to meet the advanced propulsion system requirements for planetary science missions in the next century. The technology program planning is based upon technologies with significant development heritage: ion electric propulsion and the SP-100 space nuclear power technologies. Detailed plans are presented for the required ion electric propulsion technology development and demonstration. Closer coordination between space nuclear power and space electric propulsion technology programs is a necessity as technology plans are being further refined in light of NEP concept definition and possible early NEP flight activities.

  11. Exhaust-gas measurements from NASAs HYMETS arc jet.

    SciTech Connect (OSTI)

    Miller, Paul Albert

    2010-11-01

    Arc-jet wind tunnels produce conditions simulating high-altitude hypersonic flight such as occurs upon entry of space craft into planetary atmospheres. They have traditionally been used to study flight in Earth's atmosphere, which consists mostly of nitrogen and oxygen. NASA is presently using arc jets to study entry into Mars' atmosphere, which consists of carbon dioxide and nitrogen. In both cases, a wide variety of chemical reactions take place among the gas constituents and with test articles placed in the flow. In support of those studies, we made measurements using a residual gas analyzer (RGA) that sampled the exhaust stream of a NASA arc jet. The experiments were conducted at the HYMETS arc jet (Hypersonic Materials Environmental Test System) located at the NASA Langley Research Center, Hampton, VA. This report describes our RGA measurements, which are intended to be used for model validation in combination with similar measurements on other systems.

  12. 2002 JET PROPULSION A N N U A L . R E P O R T

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    the world's largest wind tunnel, located at NASA's Ames Research Center, to test the Mars Exploration Rover and other NASA centers as a member of the "One NASA" team. There is a strong emphasis on cost con- trol and management, areas in which we can improve, enabling us to become more com- petitive. This new agreement again

  13. Air-Breathing Propulsion Qualifier Question -2012 A gas turbine jet engine, shown schematically in Figure 1, is operated on a stationary test stand.

    E-Print Network [OSTI]

    de Weck, Olivier L.

    Air-Breathing Propulsion Qualifier Question - 2012 A gas turbine jet engine, shown schematically compressor, a combustion chamber (combustor), a single stage turbine, and an ideally expanded nozzle (nozzle ratio ( C = Tt2 /Tt1 ), what is the turbine stagnation temperature ratio T = Tt4 /Tt3 ? (Suggestion

  14. NASA Conference Publication 3017 Report of the

    E-Print Network [OSTI]

    Rathbun, Julie A.

    Proceedings of a workshop cosponsored by National Aeronautics and Space Administration, Department of Energy to 30, 1987, to begin a joint public/private assessment of new technology requirements of future space of Aeronautics and Space Technology NASA Jet Propulsion Laboratory (JPL) Department of Energy Los Alamos National

  15. NASA LAW 2006 LABORATORY ASTROPHYSICS WHITE PAPER 1 LABORATORY ASTROPHYSICS WHITE PAPER

    E-Print Network [OSTI]

    Savin, Daniel Wolf

    NASA LAW 2006 LABORATORY ASTROPHYSICS WHITE PAPER 1 LABORATORY ASTROPHYSICS WHITE PAPER (BASED ON THE 2006 NASA LABORATORY ASTROPHYSICS WORKSHOP AT THE UNIVERSITY OF NEVADA, LAS VEGAS, 14-16 FEBRUARY, 2006 Chutjian (Jet Propulsion Laboratory), Gary Ferland (University of Ken- tucky), Steve Manson (Georgia State

  16. We Brake for Mars Hi! My name is Mike Meacham. I'm an engineer here at the Jet Propulsion Laboratory and

    E-Print Network [OSTI]

    Waliser, Duane E.

    We Brake for Mars Hi! My name is Mike Meacham. I'm an engineer here at the Jet Propulsion a really big parachute. To make these large parachutes you have to test them before you go. You need a way've got to test big here on Earth. You got to be a little crazy sometimes if you want to do crazy things

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

    SciTech Connect (OSTI)

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

    2014-06-01

    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 payload’s 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.

  18. Software Engineering for Space Exploration Iowa State University and Jet Propulsion Laboratory/California Institute of Technology

    E-Print Network [OSTI]

    Lutz, Robyn R.

    1 Software Engineering for Space Exploration Robyn Lutz Iowa State University and Jet are transforming the way we explore space. Spacecraft are becoming more software-intensive in order to support flight and accelerated understanding of our universe. Advances in software engineering play a vital role

  19. 1Pre-Decisional --For Planning and Discussion Purposes Only. Copyright 2013. All rights reserved. 1Jet Propulsion Laboratory,

    E-Print Network [OSTI]

    Rathbun, Julie A.

    of habitability below? Energy: Can chemical disequilibrium provide energy for life? Chemistry Energy Water Habitability Water: Are a global ocean and lakes of water hidden below the ice? Pre-Decisional -- For Planning the Clipper concept · NASA released ICEE NRA to aid in retiring instrument risk · Top-priority mission trades

  20. Nuclear electric propulsion : assessing the design of Project Prometheus.

    E-Print Network [OSTI]

    Goycoolea, Martin

    2013-01-01

    The high fuel efficiency of electric propulsion makes it a viable alternative for long-distance space travel. Project Prometheus was a NASA-led project that sought to demonstrate that distant electric propulsion missions ...

  1. Nuclear Propulsion in Space (1968)

    SciTech Connect (OSTI)

    2012-06-23

    Project NERVA was an acronym for Nuclear Engine for Rocket Vehicle Application, a joint program of the U.S. Atomic Energy Commission and NASA managed by the Space Nuclear Propulsion Office (SNPO) at the Nuclear Rocket Development Station in Jackass Flats, Nevada U.S.A. Between 1959 and 1972, the Space Nuclear Propulsion Office oversaw 23 reactor tests, both the program and the office ended at the end of 1972.

  2. Nuclear Propulsion in Space (1968)

    ScienceCinema (OSTI)

    None

    2014-06-17

    Project NERVA was an acronym for Nuclear Engine for Rocket Vehicle Application, a joint program of the U.S. Atomic Energy Commission and NASA managed by the Space Nuclear Propulsion Office (SNPO) at the Nuclear Rocket Development Station in Jackass Flats, Nevada U.S.A. Between 1959 and 1972, the Space Nuclear Propulsion Office oversaw 23 reactor tests, both the program and the office ended at the end of 1972.

  3. Jet Propulsion Laboratory ANNUAL REPORT

    E-Print Network [OSTI]

    landing sequence that ended with the rover safe on the Red Planet's surface. A century ago, President -- the Nuclear Spectro- scopic Telescope Array, or NuSTAR -- join our fleet of off-world observatories scrutinizing the universe across the energy spec- trum. These promise science returns ranging

  4. Propulsion materials

    SciTech Connect (OSTI)

    Wall, Edward J.; Sullivan, Rogelio A.; Gibbs, Jerry L.

    2008-01-01

    The Department of Energy’s (DOE’s) Office of Vehicle Technologies (OVT) is pleased to introduce the FY 2007 Annual Progress Report for the Propulsion Materials Research and Development Program. Together with DOE national laboratories and in partnership with private industry and universities across the United States, the program continues to engage in research and development (R&D) that provides enabling materials technology for fuel-efficient and environmentally friendly commercial and passenger vehicles.

  5. Development of a high power density motor for aircraft propulsion 

    E-Print Network [OSTI]

    Dibua, Imoukhuede Tim Odion

    2007-04-25

    Electric propulsion has been studied for a long time. Most of the electrically propelled vehicles that have been developed however have been ground vehicles. Recent research by NASA has promoted the development of electric ...

  6. A Review of Laser Ablation Propulsion

    SciTech Connect (OSTI)

    Phipps, Claude; Bohn, Willy; Lippert, Thomas; Sasoh, Akihiro; Schall, Wolfgang; Sinko, John

    2010-10-08

    Laser Ablation Propulsion is a broad field with a wide range of applications. We review the 30-year history of laser ablation propulsion from the transition from earlier pure photon propulsion concepts of Oberth and Saenger through Kantrowitz's original laser ablation propulsion idea to the development of air-breathing 'Lightcraft' and advanced spacecraft propulsion engines. The polymers POM and GAP have played an important role in experiments and liquid ablation fuels show great promise. Some applications use a laser system which is distant from the propelled object, for example, on another spacecraft, the Earth or a planet. Others use a laser that is part of the spacecraft propulsion system on the spacecraft. Propulsion is produced when an intense laser beam strikes a condensed matter surface and produces a vapor or plasma jet. The advantages of this idea are that exhaust velocity of the propulsion engine covers a broader range than is available from chemistry, that it can be varied to meet the instantaneous demands of the particular mission, and that practical realizations give lower mass and greater simplicity for a payload delivery system. We review the underlying theory, buttressed by extensive experimental data. The primary problem in laser space propulsion theory has been the absence of a way to predict thrust and specific impulse over the transition from the vapor to the plasma regimes. We briefly discuss a method for combining two new vapor regime treatments with plasma regime theory, giving a smooth transition from one regime to the other. We conclude with a section on future directions.

  7. 10/27/09 5:25 PMRobot Armada Might Scale New Worlds -NASA Jet Propulsion Laboratory Page 1 of 2http://www.jpl.nasa.gov/news/features.cfm?feature=2343

    E-Print Network [OSTI]

    Arizona, University of

    , with an air balloon or airship floating overhead to provide a birds-eye view of mountain ranges, lakes the airship or orbiter could confirm that indeed the rover is in a dry riverbed - unlike current missions

  8. 28th Joint Propulsion Conference and Exhibit

    SciTech Connect (OSTI)

    Stone, J.R.; Sovey, J.S.

    1992-07-01

    The National Aeronautics and Space Administration (NASA) has initiated a program to establish the readiness of nuclear electric propulsion (NEP) technology for relatively near-term applications to outer planet robotic science missions with potential future evolution to system for piloted Mars vehicles. This program was initiated in 1991 with a very modest effort identified with nuclear thermal propulsion (NTP); however, NEP is also an integral part of this program and builds upon NASA's Base Research and Technology Program in power and electric propulsion as well as the SP-100 space nuclear power program. The NEP Program will establish the feasibility and practicality of electric propulsion for robotic and piloted solar system exploration. The performance objectives are high specific impulse (200 greater than I(sub sp) greater than 10000 s), high efficiency (over 0.50), and low specific mass. The planning for this program was initially focussed on piloted Mars missions, but has since been redirected to first focus on 100-kW class systems for relatively near-term robotic missions, with possible future evolution to megawatt- and multi-megawatt-class systems applicable to cargo vehicles supporting human missions as well as to the piloted vehicles. This paper reviews current plans and recent progress for the overall nuclear electric propulsion project and closely related activities.

  9. Jet Streams Jet Streams

    E-Print Network [OSTI]

    Hennon, Christopher C.

    ATMS 310 Jet Streams Jet Streams A jet stream is an intense (30+ m/s in upper troposphere, 15+ m of air associated with strong (at least 5-10 ms-1 km-1 ) vertical wind shear. A Jet Streak is an isotach maximum embedded within a jet stream. Jet streams are mesoscale in the cross-flow direction and synoptic

  10. AIAA Paper 2006-0102 Analysis of Jet Effects on Co-Flow Jet Airfoil

    E-Print Network [OSTI]

    Zha, Gecheng

    engine inlet j jet injection Freestream Greek Letters: Turbulent Dissipation Rate Ratio of SpecificAIAA Paper 2006-0102 Analysis of Jet Effects on Co-Flow Jet Airfoil Performance with Integrated Propulsion System Ge-Cheng Zha and Wei Gao Dept. of Mechanical and Aerospace Engineering University of Miami

  11. Fast Track'' nuclear thermal propulsion concept

    SciTech Connect (OSTI)

    Johnson, R.A.; Zweig, H.R. (Rocketdyne Division, Rockwell International Corporation, 6633 Canoga Avenue, P.O. Box 7922, Canoga Park, California 91309-7922 (United States)); Cooper, M.H.; Wett, J. Jr. (Westinghouse Electric Corporation, Post Office Box 158, Madison, Pennsylvania 15663 (United States))

    1993-01-10

    The objective of the Space Exploration Initiative ( America at the Threshold...,'' 1991) is the exploration of Mars by man in the second decade of the 21st century. The NASA Fast Track'' approach (NASA-LeRC Presentation, 1992) could accelerate the manned exploration of Mars to 2007. NERVA-derived nuclear propulsion represents a viable near-term technology approach to accomplish the accelerated schedule. Key milestones in the progression to the manned Mars mission are (1) demonstration of TRL-6 for the man-rateable system by 1999, (2) a robotic lunar mission by 2000, (3) the first cargo mission to Mars by 2005, and (4) the piloted Mars mission in 2007. The Rocketdyne-Westinghouse concept for nuclear thermal propulsion to achieve these milestones combines the nuclear reactor technology of the Rover/NERVA programs and the state-of-the-art hardware designs from hydrogen-fueled rocket engine successes like the Space Shuttle Main Engine (SSME).

  12. Cover: Mariner 9 spacecraft. JET PROPULSION

    E-Print Network [OSTI]

    Waliser, Duane E.

    programs included a police air patrol system, a school alarm system, monitoring systems for hos- pitals, and studies of water pollution and energy management. In general, 1971 was a year of solid ac- complishment following gravity acceleration from the field of Venus. The spacecraft system design was essentially

  13. Nuclear thermal propulsion engine cost trade studies

    SciTech Connect (OSTI)

    Paschall, R.K. (Rocketdyne Division, Rockwell International Corporation, Mail Stop IB57, 6633 Canoga Avenue, P.O. Box 7922, Canoga Park, California 91309-7922 (United States))

    1993-01-10

    The NASA transportation strategy for the Mars Exploration architecture includes the use of nuclear thermal propulsion as the primary propulsion system for Mars transits. It is anticipated that the outgrowth of the NERVA/ROVER programs will be a nuclear thermal propulsion (NTP) system capable of providing the propulsion for missions to Mars. The specific impulse (Isp) for such a system is expected to be in the 870 s range. Trade studies were conducted to investigate whether or not it may be cost effective to invest in a higher performance (Isp[gt]870 s) engine for nuclear thermal propulsion for missions to Mars. The basic cost trades revolved around the amount of mass that must be transported to low-earth orbit prior to each Mars flight and the cost to launch that mass. The mass required depended on the assumptions made for Mars missions scenarios including piloted/cargo flights, number of Mars missions, and transit time to Mars. Cost parameters included launch cost, program schedule for development and operations, and net discount rate. The results were very dependent on the assumptions that were made. Under some assumptions, higher performance engines showed cost savings in the billions of dollars; under other assumptions, the additional cost to develop higher performance engines was not justified.

  14. Nuclear Electric Propulsion Technology Panel findings and recommendations

    SciTech Connect (OSTI)

    Doherty, M.P.

    1992-01-01

    Summarized are the findings and recommendations of a triagency (NASA/DOE/DOD) panel on Nuclear Electric Propulsion (NEP) Technology. NEP has been identified as a candidate nuclear propulsion technology for exploration of the Moon and Mars as part of the Space Exploration Initiative (SEI). The findings are stated in areas of system and subsystem considerations, technology readiness, and ground test facilities. Recommendations made by the panel are summarized concerning: (1) existing space nuclear power and propulsion programs, and (2) the proposed multiagency NEP technology development program.

  15. JOURNAL OF PROPULSION AND POWER Vol. 16, No. 3, MayJune 2000

    E-Print Network [OSTI]

    Flandro, Gary A.

    JOURNAL OF PROPULSION AND POWER Vol. 16, No. 3, May­June 2000 Convergence of Two Analytical and Jet Propulsion Cen- ter. Member AIAA. = mean ratio of specific heats = pressure wave amplitude, Ap-flow effects are properly accounted for. Such effects must be included when the wave motion is parallel

  16. Efficiency of Fish Propulsion

    E-Print Network [OSTI]

    Maertens, A P; Yue, D K P

    2014-01-01

    It is shown that the system efficiency of a self-propelled flexible body is ill-defined unless one considers the concept of quasi-propulsive efficiency, defined as the ratio of the power needed to tow a body in rigid-straight condition over the power it needs for self-propulsion, both measured for the same speed. Through examples we show that the quasi-propulsive efficiency is the only rational non-dimensional metric of the propulsive fitness of fish and fish-like mechanisms. Using two-dimensional viscous simulations and the concept of quasi-propulsive efficiency, we discuss the efficiency two-dimensional undulating foils. We show that low efficiencies, due to adverse body-propulsor hydrodynamic interactions, cannot be accounted for by the increase in friction drag.

  17. AIAA 2014-3820 Propulsion and Energy Forum

    E-Print Network [OSTI]

    Zha, Gecheng

    -breathing engine heated by a fission nuclear reactor based on the open Brayton cycle. The engine will generate both density of nuclear fission. The ultra-high lift co-flow jet flow control airfoil will be implemented/ASME/SAE/ASEE Joint Propulsion Conference Mars Aerial Nuclear Global Landing Explorer: A Global Mobility and Multi

  18. ECR-GDM Thruster for Fusion Propulsion

    SciTech Connect (OSTI)

    Brainerd, Jerome J.; Reisz, Al [Reisz Engineers 2909 Johnson Rd. Huntsville, Alabama 35805 256-325-2531 (United States)

    2009-03-16

    The concept of the Gasdynamic Mirror (GDM) device for fusion propulsion was proposed by and Lee (1995) over a decade ago and several theoretical papers has supported the feasibility of the concept. A new ECR plasma source has been built to supply power to the GDM experimental thruster previously tested at the Marshall Space Flight Center (MSFC). The new plasma generator, powered by microwaves at 2.45 or 10 GHz. is currently being tested. This ECR plasma source operates in a number of distinct plasma modes, depending upon the strength and shape of the local magnetic field. Of particular interest is the compact plasma jet issuing form the plasma generator when operated in a mirror configuration. The measured velocity profile in the jet plume is bimodal, possibly as a result of the GDM effect in the ECR chamber of the thruster.

  19. Contributions Regarding the Aircraft Nuclear Propulsion

    SciTech Connect (OSTI)

    Mitrica, Bogdan; Petre, Marian; Dima, Mihai Octavian; Stanciu, Virgil; Petre, Carmelia; Precup, Irinel

    2010-01-21

    The possibility to use a nuclear reactor for airplanes propulsion was investigated taking in to account 2 possible solutions: the direct cycle (where the fluid pass through the reactor's core) and the indirect cycle (where the fluid is passing through a heat exchanger). Taking in to account the radioprotection problems, the only realistic solution seems to be the indirect cycle, where the energy transfer should be performed by a heat exchanger that must work at very high speed of the fluid. The heat exchanger will replace the classical burning room. We had performed a more precise theoretical study for the nuclear jet engine regarding the performances of the nuclear reactor, of the heat exchanger and of the jet engine. It was taken in to account that in the moment when the burning room is replaced by a heat exchanger, a new model for gasodynamic process from the engine must be performed. Studies regarding the high flow speed heat transfer were performed.

  20. Ground Test Facility for Propulsion and Power Modes of Nuclear Engine Operation

    SciTech Connect (OSTI)

    Michael, WILLIAMS

    2004-11-22

    Existing DOE Ground Test Facilities have not been used to support nuclear propulsion testing since the Rover/NERVA programs of the 1960's. Unlike the Rover/NERVA programs, DOE Ground Test facilities for space exploration enabling nuclear technologies can no longer be vented to the open atmosphere. The optimal selection of DOE facilities and accompanying modifications for confinement and treatment of exhaust gases will permit the safe testing of NASA Nuclear Propulsion and Power devices involving variable size and source nuclear engines for NASA Jupiter Icy Moon Orbiter (JIMO) and Commercial Space Exploration Missions with minimal cost, schedule and environmental impact. NASA site selection criteria and testing requirements are presented.

  1. Progress in colloid propulsion

    E-Print Network [OSTI]

    López Urdiales, Jóse Mariano, 1977-

    2004-01-01

    In the early decades of the Space Age, a great deal of work was put into the development of the Colloid Thruster as an electric propulsion system for spacecraft. In spite of the effort by the end of the 70s the programs ...

  2. Propulsion engineering study for small-scale Mars missions

    SciTech Connect (OSTI)

    Whitehead, J.

    1995-09-12

    Rocket propulsion options for small-scale Mars missions are presented and compared, particularly for the terminal landing maneuver and for sample return. Mars landing has a low propulsive {Delta}v requirement on a {approximately}1-minute time scale, but at a high acceleration. High thrust/weight liquid rocket technologies, or advanced pulse-capable solids, developed during the past decade for missile defense, are therefore more appropriate for small Mars landers than are conventional space propulsion technologies. The advanced liquid systems are characterize by compact lightweight thrusters having high chamber pressures and short lifetimes. Blowdown or regulated pressure-fed operation can satisfy the Mars landing requirement, but hardware mass can be reduced by using pumps. Aggressive terminal landing propulsion designs can enable post-landing hop maneuvers for some surface mobility. The Mars sample return mission requires a small high performance launcher having either solid motors or miniature pump-fed engines. Terminal propulsion for 100 kg Mars landers is within the realm of flight-proven thruster designs, but custom tankage is desirable. Landers on a 10 kg scale also are feasible, using technology that has been demonstrated but not previously flown in space. The number of sources and the selection of components are extremely limited on this smallest scale, so some customized hardware is required. A key characteristic of kilogram-scale propulsion is that gas jets are much lighter than liquid thrusters for reaction control. The mass and volume of tanks for inert gas can be eliminated by systems which generate gas as needed from a liquid or a solid, but these have virtually no space flight history. Mars return propulsion is a major engineering challenge; earth launch is the only previously-solved propulsion problem requiring similar or greater performance.

  3. Deuterium microbomb rocket propulsion

    E-Print Network [OSTI]

    Friedwardt Winterberg

    2008-12-02

    Large scale manned space flight within the solar system is still confronted with the solution of two problems: 1. A propulsion system to transport large payloads with short transit times between different planetary orbits. 2. A cost effective lifting of large payloads into earth orbit. For the solution of the first problem a deuterium fusion bomb propulsion system is proposed where a thermonuclear detonation wave is ignited in a small cylindrical assembly of deuterium with a gigavolt-multimegampere proton beam, drawn from the magnetically insulated spacecraft acting in the ultrahigh vacuum of space as a gigavolt capacitor. For the solution of the second problem, the ignition is done by argon ion lasers driven by high explosives, with the lasers destroyed in the fusion explosion and becoming part of the exhaust.

  4. An historical collection of papers on nuclear thermal propulsion

    SciTech Connect (OSTI)

    Not Available

    1992-01-01

    The present volume of historical papers on nuclear thermal propulsion (NTP) encompasses NTP technology development regarding solid-core NTP technology, advanced concepts from the early years of NTP research, and recent activities in the field. Specific issues addressed include NERVA rocket-engine technology, the development of nuclear rocket propulsion at Los Alamos, fuel-element development, reactor testing for the Rover program, and an overview of NTP concepts and research emphasizing two decades of NASA research. Also addressed are the development of the 'nuclear light bulb' closed-cycle gas core and a demonstration of a fissioning UF6 gas in an argon vortex. The recent developments reviewed include the application of NTP to NASA's Lunar Space Transportation System, the use of NTP for the Space Exploration Initiative, and the development of nuclear rocket engines in the former Soviet Union.

  5. Scoping calculations of power sources for nuclear electric propulsion

    SciTech Connect (OSTI)

    Difilippo, F.C. [Oak Ridge National Lab., TN (United States)] [Oak Ridge National Lab., TN (United States)

    1994-05-01

    This technical memorandum describes models and calculational procedures to fully characterize the nuclear island of power sources for nuclear electric propulsion. Two computer codes were written: one for the gas-cooled NERVA derivative reactor and the other for liquid metal-cooled fuel pin reactors. These codes are going to be interfaced by NASA with the balance of plant in order to making scoping calculations for mission analysis.

  6. NASA's satellite orbit anomaly problem can be solved precisely in the frame of Einstein's special theory of relativity. Anomaly confirms that gravity fields propagate with velocity of light as Einstein predicted

    E-Print Network [OSTI]

    Victor M. Bogdan

    2009-10-17

    NASA's Jet Propulsion Laboratory put on You Tube a problem that has been baffling the scientists for sometime. It involves an unexpected force acting on the space probes. The author proves that NASA'S satellite orbit anomaly problem can be solved in the frame of Einstein's Special Theory of Relativity. The anomaly confirms that gravity fields propagate with velocity of light as Einstein predicted. The proof is based on the authors discovery of the relativistic version of Newton's gravity field. The author provides formulas for relativistic equation of motion for a spacecraft in the joint gravitational field of the Earth and the Sun in a Lorentzian frame attached to the Earth. The formulas are suitable for digital computers and can be easily implemented. He also shows how to find solutions of the relativistic equations of motion for the spacecraft.

  7. Propulsion considerations for supersonic oblique flying wings

    E-Print Network [OSTI]

    Shinagawa, Yuto

    2006-01-01

    Propulsion considerations unique to the supersonic oblique flying wing, including cycle selection, sizing, and integration were investigated via the development and interrogation of aerodynamic and propulsive synthesis ...

  8. Vorticity structure and evolution in a transverse jet with new algorithms for scalable particle simulation

    E-Print Network [OSTI]

    Marzouk, Youssef M. (Youssef Mohamed)

    2004-01-01

    Transverse jets arise in many applications, including propulsion, effluent dispersion, oil field flows, V/STOL aerodynamics, and drug delivery. Furthermore, they exemplify flows dominated by coherent structures that cascade ...

  9. Lagrangian simulation of transverse jets with a distribution-based diffusion scheme

    E-Print Network [OSTI]

    Wee, Daehyun, 1974-

    2007-01-01

    Transverse jets form a dominant group of flow fields arising in many applications of modern energy utilization, including propulsion and effluent dispersion. Furthermore, they form canonical examples where the flow field ...

  10. JET FORMATION AND allbook.tex; 15/11/2000; 21:17; p.1

    E-Print Network [OSTI]

    Greiner, Jochen

    Part V JET FORMATION AND DYNAMICS allbook.tex; 15/11/2000; 21:17; p.1 #12; 2 allbook.tex; 15/11/2000; 21:17; p.2 #12; Relativistic Jet Formation in Microquasars David L. Meier Jet Propulsion Laboratory to a Lorentz factor of #24; 3 (0.94c). It is generally believed that such ow velocities indicate that jet

  11. Machine Intelligence and Robotics Report of the NASA Study Group

    E-Print Network [OSTI]

    Shamos, Michael I.

    of Computer Science University of Southern California Dr. Thomas O. Binford, Research Associate Artificial, Jet Propulsion Laboratory Dr. Elliott C. Levinthal Adjunct Professor of Genetics Stanford University Professor of Computer Science University of Maryland Dr. Thomas B. Sheridan Professor of Engineering

  12. Ontogeny of Squid Mantle Function: Changes in the Mechanics of Escape-Jet Locomotion in the Oval

    E-Print Network [OSTI]

    Kier, William M.

    Ontogeny of Squid Mantle Function: Changes in the Mechanics of Escape-Jet Locomotion in the Oval.01). These ontogenetic changes in the mechanics of the escape jet suggest (1) that propulsion efficiency of the exhalant phase of the jet is highest in hatchlings, and (2) that the mechanics of the circumferential muscles

  13. Fuzzy Jets

    E-Print Network [OSTI]

    Mackey, Lester; Schwartzman, Ariel; Stansbury, Conrad

    2015-01-01

    Collimated streams of particles produced in high energy physics experiments are organized using clustering algorithms to form jets. To construct jets, the experimental collaborations based at the Large Hadron Collider (LHC) primarily use agglomerative hierarchical clustering schemes known as sequential recombination. We propose a new class of algorithms for clustering jets that use infrared and collinear safe mixture models. These new algorithms, known as fuzzy jets, are clustered using maximum likelihood techniques and can dynamically determine various properties of jets like their size. We show that the fuzzy jet size adds additional information to conventional jet tagging variables. Furthermore, we study the impact of pileup and show that with some slight modifications to the algorithm, fuzzy jets can be stable up to high pileup interaction multiplicities.

  14. Fuzzy Jets

    E-Print Network [OSTI]

    Lester Mackey; Benjamin Nachman; Ariel Schwartzman; Conrad Stansbury

    2015-09-07

    Collimated streams of particles produced in high energy physics experiments are organized using clustering algorithms to form jets. To construct jets, the experimental collaborations based at the Large Hadron Collider (LHC) primarily use agglomerative hierarchical clustering schemes known as sequential recombination. We propose a new class of algorithms for clustering jets that use infrared and collinear safe mixture models. These new algorithms, known as fuzzy jets, are clustered using maximum likelihood techniques and can dynamically determine various properties of jets like their size. We show that the fuzzy jet size adds additional information to conventional jet tagging variables. Furthermore, we study the impact of pileup and show that with some slight modifications to the algorithm, fuzzy jets can be stable up to high pileup interaction multiplicities.

  15. annual progress report Propulsion Materials

    E-Print Network [OSTI]

    Pennycook, Steve

    for Propulsion Materials Energy Efficiency and Renewable Energy Office of Vehicle Technologies Advanced Materials Agreement 13295 - Permanent Magnet Development for Automotive Traction Motors......... 55 PROJECT 18517 PROJECT 18519 ­ MATERIALS FOR CONTROL OF EXHAUST GASES AND ENERGY RECOVERY SYSTEMS

  16. annual progress report Propulsion Materials

    E-Print Network [OSTI]

    Pennycook, Steve

    Progress Report for Propulsion Materials Energy Efficiency and Renewable Energy Office of Vehicle - Permanent Magnet Development for Automotive Traction Motors......... 47 PROJECT 18518 - MATERIALS FOR HIGH)...................................................................... 193 PROJECT 18519 ­ MATERIALS FOR CONTROL OF EXHAUST GASES AND ENERGY RECOVERY SYSTEMS

  17. National Aeronautics and Space Administration In-Space propulSIon SyStemS roadmap

    E-Print Network [OSTI]

    Waliser, Duane E.

    National Aeronautics and Space Administration In-Space propulSIon SyStemS roadmap Technology Area Missions TA02-24 Acknowledgements TA02-24 #12;Foreword NASA's integrated technology roadmap, including both Roadmap, an integrated set of fourteen technology area roadmaps, recommending the overall technology

  18. Analysis of Advanced Actinide-Fueled Energy Systems for Deep Space Propulsion Applications 

    E-Print Network [OSTI]

    Guy, Troy Lamar

    2011-02-22

    Collimator Reactor JANIS Java-based Nuclear Information Software JIMO Jupiter Icy Moons Orbiter LWR Light Water Reactor NASA National Aeronautics and Space Administration NDDEC Nuclear Driven Direct Energy Conversion NEP Nuclear Electric Propulsion... Metric T1/2: Half-Life 18 - 900 years A: Specific Activity 2.6 neutrons per neutron absorbed ?F: Fission Cross Section > U, Pu baseline...

  19. Jets in Soft-Collinear Effective Theory

    E-Print Network [OSTI]

    Hornig, Andrew

    2010-01-01

    Jet Functions . . . . . . . . . . . . . . . . . . . .Event Shapes . . . . . . . . . . . . . . . . . . . . . JetQuark Jet

  20. Recapturing NERVA-Derived Fuels for Nuclear Thermal Propulsion

    SciTech Connect (OSTI)

    Qualls, A L [ORNL] [ORNL; Hancock, Emily F [ORNL] [ORNL

    2011-01-01

    The Department of Energy is working with NASA to examine fuel options for Nuclear Thermal Propulsion applications. Extensive development and testing was performed on graphite-based fuels during the Nuclear Engineer Rocket Vehicle Application (NERVA) and Rover programs through the early 1970s. This paper explores the possibility of recapturing the technology and the issues associated with using it for the next generation of nuclear thermal rockets. The issues discussed include a comparison of today's testing capabilities, analysis techniques and methods, and knowledge to that of previous development programs and presents a plan to recapture the technology for a flight program.

  1. Stellar jets

    E-Print Network [OSTI]

    Thomas J. Maccarone

    2008-05-23

    With a goal of understanding the conditions under which jets might be produced in novae and related objects, I consider the conditions under which jets are produced from other classes of accreting compact objects. I give an overview of accretion disk spectral states, including a discussion of in which states these jets are seen. I highlight the differences between neutron stars and black holes, which may help give us insights about when and how the presence of a solid surface may help or inhibit jet production.

  2. Gravitomagnetic Jets

    E-Print Network [OSTI]

    C. Chicone; B. Mashhoon

    2011-03-12

    We present a family of dynamic rotating cylindrically symmetric Ricci-flat gravitational fields whose geodesic motions have the structure of gravitomagnetic jets. These correspond to helical motions of free test particles up and down parallel to the axis of cylindrical symmetry and are reminiscent of the motion of test charges in a magnetic field. The speed of a test particle in a gravitomagnetic jet asymptotically approaches the speed of light. Moreover, numerical evidence suggests that jets are attractors. The possible implications of our results for the role of gravitomagnetism in the formation of astrophysical jets are briefly discussed.

  3. National Aeronautics and Space Administration Jet Propulsion Laboratory

    E-Print Network [OSTI]

    extensions of our ability to peer into the far reaches of our solar system, other galaxies, and the very to image the anisotropies of the cosmic background radiation field over the whole sky with unprecedented observatory launched to date. herschel observes at wavelengths that have never previously been explored. SPire

  4. Pulsed jet dynamics of squid hatchlings at intermediate Reynolds numbers Ian K. Bartol, Paul S. Krueger, William J. Stewart and Joseph T. Thompson

    E-Print Network [OSTI]

    Horth, Lisa

    Pulsed jet dynamics of squid hatchlings at intermediate Reynolds numbers Ian K. Bartol, Paul S of various appendages, squid paralarvae (hatchlings) employ a pulsed jet for locomotion at intermediate Re different propulsive mechanism, i.e. jetting, involves (1) radial expansion of the mantle, resulting

  5. Several groups of fishes have been shown to use or are suspected of using water jets from the opercular valves to aid

    E-Print Network [OSTI]

    Fish, Frank

    Several groups of fishes have been shown to use or are suspected of using water jets from, 1987; Pietsch and Grobecker, 1987). Most studies of jet propulsion in fishes have been concerned with multiple jets that produce continuous, if somewhat staccato, locomotion. Some sources, however, have

  6. HYDRODYNAMICS OF UNDULATORY PROPULSION GEORGE V. LAUDER

    E-Print Network [OSTI]

    Lauder, George V.

    of a quantitative nature. The combination of highresolution highspeed video systems, high powered continuous wave11 HYDRODYNAMICS OF UNDULATORY PROPULSION GEORGE V. LAUDER ERIC D. TYTELL I. Introduction II. Classical Modes of Undulatory Propulsion III. Theory of Undulatory Propulsion A. Resistive Models B

  7. Temperature Effect on Acoustics of Supersonic Impinging Jet

    E-Print Network [OSTI]

    impinging jets have been of interest both from an applications and a fundamental fluid mechanics point for Advanced Aero-Propulsion, Florida A&M University/Florida State University College of Engineering, Tallahassee, FL 32310 Paul A. Ragaller2 Department of Mechanical Engineering Massachusetts Institute

  8. American Institute of Aeronautics and Astronautics Aeroacoustics of Three-Stream High-Speed Jets from

    E-Print Network [OSTI]

    Papamoschou, Dimitri

    American Institute of Aeronautics and Astronautics 1 Aeroacoustics of Three-Stream High-Speed Jets contributions in the literature. Here we mention selected works in the area of multi-stream jets. The study of the jet. Initial experiments at NASA Glenn Research Center on three-stream nozzles noted a modest benefit

  9. Cosmic Jets

    E-Print Network [OSTI]

    C. Chicone; B. Mashhoon; K. Rosquist

    2011-02-17

    We discuss time-dependent gravitational fields that "accelerate" free test particles to the speed of light resulting in cosmic double-jet configurations. It turns out that complete gravitational collapse along a spatial axis together with corresponding expansion along the other two axes leads to the accelerated motion of free test particles up and down parallel to the collapse axis such that a double-jet pattern is asymptotically formed with respect to the collapsed configuration.

  10. Heavy Vehicle Propulsion Materials Program

    SciTech Connect (OSTI)

    Diamond, S.; Johnson, D.R.

    1999-04-26

    The objective of the Heavy Vehicle Propulsion Materials Program is to develop the enabling materials technology for the clean, high-efficiency diesel truck engines of the future. The development of cleaner, higher-efficiency diesel engines imposes greater mechanical, thermal, and tribological demands on materials of construction. Often the enabling technology for a new engine component is the material from which the part can be made. The Heavy Vehicle Propulsion Materials Program is a partnership between the Department of Energy (DOE), and the diesel engine companies in the United States, materials suppliers, national laboratories, and universities. A comprehensive research and development program has been developed to meet the enabling materials requirements for the diesel engines of the future. Advanced materials, including high-temperature metal alloys, intermetallics, cermets, ceramics, amorphous materials, metal- and ceramic-matrix composites, and coatings, are investigated for critical engine applications.

  11. Emerging Jets

    E-Print Network [OSTI]

    Pedro Schwaller; Daniel Stolarski; Andreas Weiler

    2015-05-11

    In this work, we propose a novel search strategy for new physics at the LHC that utilizes calorimeter jets that (i) are composed dominantly of displaced tracks and (ii) have many different vertices within the jet cone. Such emerging jet signatures are smoking guns for models with a composite dark sector where a parton shower in the dark sector is followed by displaced decays of dark pions back to SM jets. No current LHC searches are sensitive to this type of phenomenology. We perform a detailed simulation for a benchmark signal with two regular and two emerging jets, and present and implement strategies to suppress QCD backgrounds by up to six orders of magnitude. At the 14 TeV LHC, this signature can be probed with mediator masses as large as 1.5 TeV for a range of dark pion lifetimes, and the reach is increased further at the high-luminosity LHC. The emerging jet search is also sensitive to a broad class of long-lived phenomena, and we show this for a supersymmetric model with R-parity violation. Possibilities for discovery at LHCb are also discussed.

  12. Jet observables without jet algorithms

    E-Print Network [OSTI]

    Bertolini, Daniele

    We introduce a new class of event shapes to characterize the jet-like structure of an event. Like traditional event shapes, our observables are infrared/collinear safe and involve a sum over all hadrons in an event, but ...

  13. Lightweighting and Propulsion Materials Roadmapping Workshop...

    Energy Savers [EERE]

    Lightweighting and Propulsion Materials Roadmapping Workshop Outbrief 2012 DOE Hydrogen and Fuel Cells Program and Vehicle Technologies Program Annual Merit Review and Peer...

  14. Jet Quenching via Jet Collimation

    E-Print Network [OSTI]

    Jorge Casalderrey-Solana; Jose Guilherme Milhano; Urs Achim Wiedemann

    2010-12-03

    The ATLAS Collaboration recently reported strong modifications of dijet properties in heavy ion collisions. In this work, we discuss to what extent these first data constrain already the microscopic mechanism underlying jet quenching. Simple kinematic arguments lead us to identify a frequency collimation mechanism via which the medium efficiently trims away the soft components of the jet parton shower. Through this mechanism, the observed dijet asymmetry can be accomodated with values of $\\hat{q}\\, L$ that lie in the expected order of magnitude.

  15. Feasibility of MHD submarine propulsion

    SciTech Connect (OSTI)

    Doss, E.D. ); Sikes, W.C. )

    1992-09-01

    This report describes the work performed during Phase 1 and Phase 2 of the collaborative research program established between Argonne National Laboratory (ANL) and Newport News Shipbuilding and Dry Dock Company (NNS). Phase I of the program focused on the development of computer models for Magnetohydrodynamic (MHD) propulsion. Phase 2 focused on the experimental validation of the thruster performance models and the identification, through testing, of any phenomena which may impact the attractiveness of this propulsion system for shipboard applications. The report discusses in detail the work performed in Phase 2 of the program. In Phase 2, a two Tesla test facility was designed, built, and operated. The facility test loop, its components, and their design are presented. The test matrix and its rationale are discussed. Representative experimental results of the test program are presented, and are compared to computer model predictions. In general, the results of the tests and their comparison with the predictions indicate that thephenomena affecting the performance of MHD seawater thrusters are well understood and can be accurately predicted with the developed thruster computer models.

  16. Propulsion in a viscoelastic fluid

    E-Print Network [OSTI]

    Eric Lauga

    2007-03-21

    Flagella beating in complex fluids are significantly influenced by viscoelastic stresses. Relevant examples include the ciliary transport of respiratory airway mucus and the motion of spermatozoa in the mucus-filled female reproductive tract. We consider the simplest model of such propulsion and transport in a complex fluid, a waving sheet of small amplitude free to move in a polymeric fluid with a single relaxation time. We show that, compared to self-propulsion in a Newtonian fluid occurring at a velocity U_N, the sheet swims (or transports fluid) with velocity U / U_N = [1+De^2 (eta_s)/(eta) ]/[1+De^2], where eta_s is the viscosity of the Newtonian solvent, eta is the zero-shear-rate viscosity of the polymeric fluid, and De is the Deborah number for the wave motion, product of the wave frequency by the fluid relaxation time. Similar expressions are derived for the rate of work of the sheet and the mechanical efficiency of the motion. These results are shown to be independent of the particular nonlinear constitutive equations chosen for the fluid, and are valid for both waves of tangential and normal motion. The generalization to more than one relaxation time is also provided. In stark contrast with the Newtonian case, these calculations suggest that transport and locomotion in a non-Newtonian fluid can be conveniently tuned without having to modify the waving gait of the sheet but instead by passively modulating the material properties of the liquid.

  17. Ablative Laser Propulsion: An Update, Part II

    SciTech Connect (OSTI)

    Pakhomov, Andrew V.; Lin Jun; Thompson, M. Shane

    2004-03-30

    This paper presents an updated review of studies on Ablative Laser Propulsion conducted by the Laser Propulsion Group (LPG) at the University of Alabama in Huntsville. In particular, we describe the experimental technique developed for determination of specific impulses from plasma plume imaging with an intensified CCD camera.

  18. Ablative Laser Propulsion: An Update, Part I

    SciTech Connect (OSTI)

    Pakhomov, Andrew V.; Cohen, Timothy; Lin Jun; Thompson, M. Shane; Herren, Kenneth A.

    2004-03-30

    This paper presents an updated review of studies on Ablative Laser Propulsion conducted by the Laser Propulsion Group (LPG) at the University of Alabama in Huntsville. In particular, we describe the newest results of our experimental study of specific impulses and coupling coefficients achieved by double-pulsed ablation of graphite, aluminum, copper and lead targets.

  19. OBLIQUE DETONATIONS: THEORY AND PROPULSION APPLICATIONS

    E-Print Network [OSTI]

    OBLIQUE DETONATIONS: THEORY AND PROPULSION APPLICATIONS Joseph M. Powers1 University of Notre Dame accelerator and the oblique detona- tion wave engine. Additionally, it is the generic two of both oblique det- onations and their application to propulsion devices. The plan of this paper

  20. Vehicle Technologies Office: 2013 Propulsion Materials R&D Annual...

    Office of Energy Efficiency and Renewable Energy (EERE) Indexed Site

    Vehicle Technologies Office: 2013 Propulsion Materials R&D Annual Progress Report Vehicle Technologies Office: 2013 Propulsion Materials R&D Annual Progress Report This report...

  1. Enabling Green Energy and Propulsion Systems via Direct Noise...

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

    GE propulsion systems Enabling Green Energy and Propulsion Systems via Direct Noise Computation PI Name: Umesh Paliath PI Email: paliath@ge.com Institution: GE Global Research...

  2. Hydrogen peroxide propulsion for smaller satellites (SSC98-VIII...

    Office of Scientific and Technical Information (OSTI)

    Conference: Hydrogen peroxide propulsion for smaller satellites (SSC98-VIII-1) Citation Details In-Document Search Title: Hydrogen peroxide propulsion for smaller satellites...

  3. Naval Nuclear Propulsion Plants | National Nuclear Security Administra...

    National Nuclear Security Administration (NNSA)

    Naval Nuclear Propulsion Plants In naval nuclear propulsion plants, fissioning of uranium atoms in the reactor core produces heat. Because the fission process also produces...

  4. Looking From A Hilltop: Automotive Propulsion System Technology...

    Office of Energy Efficiency and Renewable Energy (EERE) Indexed Site

    Looking From A Hilltop: Automotive Propulsion System Technology Looking From A Hilltop: Automotive Propulsion System Technology Outlook for global fuel economy requirements and...

  5. Haar LBP Gabor Jet boosting Gabor Jet

    E-Print Network [OSTI]

    Ai, Haizhou

    Boosting 1 boosting Haar LBP Gabor Jet boosting LBP Haar Gabor Jet boosting TP391. Further more, three kinds of local feature, Haar like feature, LBP histogram and Gabor jet are extracted, Haar like feature is more efficient for discriminating young and middle aged people, and Gabor Jet fits

  6. NASA OFFICE OF INSPECTOR GENERAL

    E-Print Network [OSTI]

    . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .26 NASA's Top Management and Performance Challenges . . . . . . . .28 Congressional Testimony

  7. DICHOTOMY OF SOLAR CORONAL JETS: STANDARD JETS AND BLOWOUT JETS

    SciTech Connect (OSTI)

    Moore, Ronald L.; Cirtain, Jonathan W.; Sterling, Alphonse C.; Falconer, David A.

    2010-09-01

    By examining many X-ray jets in Hinode/X-Ray Telescope coronal X-ray movies of the polar coronal holes, we found that there is a dichotomy of polar X-ray jets. About two thirds fit the standard reconnection picture for coronal jets, and about one third are another type. We present observations indicating that the non-standard jets are counterparts of erupting-loop H{alpha} macrospicules, jets in which the jet-base magnetic arch undergoes a miniature version of the blowout eruptions that produce major coronal mass ejections. From the coronal X-ray movies we present in detail two typical standard X-ray jets and two typical blowout X-ray jets that were also caught in He II 304 A snapshots from STEREO/EUVI. The distinguishing features of blowout X-ray jets are (1) X-ray brightening inside the base arch in addition to the outside bright point that standard jets have, (2) blowout eruption of the base arch's core field, often carrying a filament of cool (T {approx} 10{sup 4} - 10{sup 5} K) plasma, and (3) an extra jet-spire strand rooted close to the bright point. We present cartoons showing how reconnection during blowout eruption of the base arch could produce the observed features of blowout X-ray jets. We infer that (1) the standard-jet/blowout-jet dichotomy of coronal jets results from the dichotomy of base arches that do not have and base arches that do have enough shear and twist to erupt open, and (2) there is a large class of spicules that are standard jets and a comparably large class of spicules that are blowout jets.

  8. Propulsive Efficiency of Rowing Oars David S. Cabrera1

    E-Print Network [OSTI]

    Ruina, Andy L.

    Propulsive Efficiency of Rowing Oars David S. Cabrera1 Andy L. Ruina2 Department of Theoretical Is the common folklore, that oars are less efficient at propulsion than propellers, correct? Here we examine the propulsive efficiency of the oars used in competitive rowing. We take the propulsive efficiency of rowing

  9. Experimental investigations of elastic tail propulsion at low Reynolds number

    E-Print Network [OSTI]

    Lauga, Eric

    of such a propulsive mechanism. A robotic swimmer is constructed and both tail shape and propulsive force are measured in a viscous fluid, generating traveling waves along the filament that produce a propulsive force see also RefsExperimental investigations of elastic tail propulsion at low Reynolds number Tony S. Yu, Eric

  10. HEAVY QUARKS JETS

    E-Print Network [OSTI]

    Suzuki, M.

    2010-01-01

    i'iAsm Heavy Quark Jets iBirijets. Short-distance vs long-than a few wide angle sub-jets at to draw first skelton jet

  11. Propulsion mechanisms in a helicon plasma thruster

    E-Print Network [OSTI]

    Sinenian, Nareg

    2008-01-01

    Electric thrusters offer an attractive option for various in-space propulsion tasks due to their high thrust efficiencies. The performance characteristics of a compact electric thruster utilizing a helicon plasma source ...

  12. Chaotic Jets

    E-Print Network [OSTI]

    Xavier Leoncini; George M. Zaslavsky

    2006-02-21

    The problem of characterizing the origin of the non-Gaussian properties of transport resulting from Hamiltonian dynamics is addressed. For this purpose the notion of chaotic jet is revisited and leads to the definition of a diagnostic able to capture some singular properties of the dynamics. This diagnostic is applied successfully to the problem of advection of passive tracers in a flow generated by point vortices. We present and discuss this diagnostic as a result of which clues on the origin of anomalous transport in these systems emerge.

  13. Activities of the NASA Exploration Team Human-Robotics Working Group Chris Culbert, Jen Rochlis, Fred Rehnmark, David Kortenkamp, Kevin Watson,

    E-Print Network [OSTI]

    Kortenkamp, David

    Activities of the NASA Exploration Team Human-Robotics Working Group Chris Culbert, Jen Rochlis, Fred Rehnmark, David Kortenkamp, Kevin Watson, Rob Ambrose, Ron Diftler, Brenda Ward NASA/Johnson Space Center Liam Pedersen NASA/Ames Research Center Chuck Weisbin, Guillermo Rodriguez, Bob Easter Jet

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

    SciTech Connect (OSTI)

    Bruce G. Schnitzler

    2012-01-01

    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.

  15. http://lez1.pppl.gov/pub/LiMagPropulsion.ps http://lez1.pppl.gov/pub/LiMagPropulsion.pdf

    E-Print Network [OSTI]

    Zakharov, Leonid E.

    http://lez1.pppl.gov/pub/LiMagPropulsion.ps http://lez1.pppl.gov/pub/LiMagPropulsion.pdf Magnetic propulsion for driving liquid Li walls L. E. Zakharov, PPPL Background: The mechanism of magnetic propulsion the technical aspects of magnetic propulsion, the issues and the necessary R & D. Electro-magnetic propulsion

  16. Nuclear electric propulsion: A better, safer, cheaper transportation system for human exploration of Mars

    SciTech Connect (OSTI)

    Clark, J.S.; George, J.A.; Gefert, L.P.; Doherty, M.P.; Sefcik, R.J.

    1994-03-01

    NASA has completed a preliminary mission and systems study of nuclear electric propulsion (NEP) systems for split-sprint' human exploration and related robotic cargo missions to Mars. This paper describes the study, the mission architecture selected, the NEP system and technology development needs, proposed development schedules, and estimated development costs. Since current administration policy makers have delayed funding for key technology development activities that could make Mars exploration missions a reality in the near future, NASA will have time to evaluate various alternate mission options, and it appears prudent to ensure that Mars mission plans focus on astronaut and mission safety, while reducing costs to acceptable levels. The split-sprint nuclear electric propulsion system offers trip times comparable to nuclear thermal propulsion (NTP) systems, while providing mission abort opportunities that are not possible with reference' mission architectures. Thus, NEP systems offer short transit times for the astronauts, reducing the exposure of the crew to intergalactic cosmic radiation. The high specific impulse of the NEP system, which leads to very low propellant requirements, results in significantly lower initial mass in low earth orbit' (IMLEO). Launch vehicle packaging studies show that the NEP system can be launched, assembled, and deployed, with about one less 240-metric-ton heavy lift launch vehicle (HLLV) per mission opportunity - a very Technology development cost of the nuclear reactor for an NEP system would be shared with the proposed nuclear surface power systems, since nuclear systems will be required to provide substantial electrical power on the surface of Mars. The NEP development project plan proposed includes evolutionary technology development for nuclear electric propulsion systems that expands upon SP-100 (Space Power - 100 kw(e)) technology that has been developed for lunar and Mars surface nuclear power.

  17. Space Propulsion Field Exam: Space Propulsion/Plasma Physics REQUIRED BY ALL STUDENTS

    E-Print Network [OSTI]

    de Weck, Olivier L.

    Space Propulsion Field Exam: Space Propulsion/Plasma Physics REQUIRED BY ALL STUDENTS From) Both devices use magnetic fields, even though they both are electrostatic ion accelerators. Explain the role of the magnetic field in each of them, and how this guides the layout of these fields. 3) One

  18. Modeling of Jet-by-Jet Diffraction Dimitri Papamoschou

    E-Print Network [OSTI]

    Papamoschou, Dimitri

    . Figure 1. Example of engine layout of Hybrid-Wing-Body airplane (Ref. 2). Research on jet-by-jetModeling of Jet-by-Jet Diffraction Dimitri Papamoschou The paper presents an analytical model for the prediction of jet-by-jet diffraction. The source jet is modeled as a radiating cylinder on which one can

  19. NASA Advisory Council Subcommittee Recommendation

    E-Print Network [OSTI]

    Rathbun, Julie A.

    NASA Advisory Council Subcommittee Recommendation Subcommittee Name: Planetary Science Chair: Sean. Short description of the proposed Recommendation The PSS recommends that NASA reconsider PI at selection and either mission cost growth or mission success. We recommend further that NASA advertise

  20. NASA/CP--2006214202 NASA Space Exploration Logistics Workshop

    E-Print Network [OSTI]

    de Weck, Olivier L.

    NASA/CP--2006­214202 NASA Space Exploration Logistics Workshop Proceedings January 17-18, 2006 Hanover, MD 21076-1320 #12;NASA/CP--2006­214202 NASA Space Exploration Logistics Workshop Proceedings January 17-18, 2006 Washington, DC The first Space Exploration Logistics Workshop, hosted by MIT and SOLE

  1. A development approach for nuclear thermal propulsion

    SciTech Connect (OSTI)

    Buden, D.

    1992-09-01

    The cost and time to develop nuclear thermal propulsion systems are very approach dependent. The objectives addressed are the development of an ``acceptable`` nuclear thermal propulsion system that can be used as part of the transportation system for people to explore Mars and the enhancement performance of other missions, within highly constrained budgets and schedules. To accomplish this, it was necessary to identify the cost drivers considering mission parameters, safety of the crew, mission success, facility availability and time and cost to construct new facilities, qualification criteria, status of technologies, management structure, and use of such system engineering techniques as concurrent engineering.

  2. A development approach for nuclear thermal propulsion

    SciTech Connect (OSTI)

    Buden, D.

    1992-01-01

    The cost and time to develop nuclear thermal propulsion systems are very approach dependent. The objectives addressed are the development of an acceptable'' nuclear thermal propulsion system that can be used as part of the transportation system for people to explore Mars and the enhancement performance of other missions, within highly constrained budgets and schedules. To accomplish this, it was necessary to identify the cost drivers considering mission parameters, safety of the crew, mission success, facility availability and time and cost to construct new facilities, qualification criteria, status of technologies, management structure, and use of such system engineering techniques as concurrent engineering.

  3. Boston University Physics Colloquium Microscale propulsion in biological and

    E-Print Network [OSTI]

    Mohanty, Raj

    Boston University Physics Colloquium Microscale propulsion in biological and engineered systems biological locomotion and engineered propulsion. In the first example, we examine swimming microorganisms the microstructure. In the second example, we examine engineered magnetic artificial microswimmers which can

  4. Top Jets at the LHC

    E-Print Network [OSTI]

    Almeida, L.G.

    2009-01-01

    Top Jets at the LHC Leandro G. Almeida, Seung J. Lee, GiladWIS/17/08-SEPT-DPP Top Jets at the LHC Leandro G. Almeidareconstructed as a single jet, a “top-jet”. The most basic “

  5. Particle Physics Phenomenology 8. QCD jets and jet algorithms

    E-Print Network [OSTI]

    Sjöstrand, Torbjörn

    Particle Physics Phenomenology 8. QCD jets and jet algorithms Torbj¨orn Sj¨ostrand Department rotationally symmetric. SppS (CERN): need to separate beam jets from highp ones. First solution: cone jets" infrared safe return to UA1 cone algorithm. Torbj¨orn Sj¨ostrand PPP 8: QCD jets and jet algorithms slide 2

  6. Propulsive Efficiency of the Underwater Dolphin Kick in Humans

    E-Print Network [OSTI]

    Fish, Frank

    Propulsive Efficiency of the Underwater Dolphin Kick in Humans Alfred von Loebbecke Rajat Mittal's propulsive efficiencies. These estimates are compared with those of a ceta- cean performing the dolphin kick kinematics is based on underwater video footage. The simulations indicate that the propulsive efficiency

  7. PROPULSION AND ENERGY 54 AEROSPACE AMERICA/DECEMBER 2005

    E-Print Network [OSTI]

    Walker, Mitchell

    PROPULSION AND ENERGY 54 AEROSPACE AMERICA/DECEMBER 2005 Electric propulsion Several significant advancements in electric propulsion (EP) systems and related technolo- gies occurred this year. Flight programs throughout the discharge and includes the effects of magnetic fields on the primary electrons. PRIMA is used

  8. Michael J. Alexander Propulsion Systems Research Lab,

    E-Print Network [OSTI]

    Papalambros, Panos

    along with the selection of motor performance curves such that maxi- mum energy efficiency is achievedMichael J. Alexander Propulsion Systems Research Lab, General Motors Technical Center, 330500 Mound Road, Warren, MI 48090 e-mail: michael.j.alexander@gm.com James T. Allison Department of Industrial

  9. Substructure of Boosted Jets

    E-Print Network [OSTI]

    Ehud Duchovni

    2013-05-21

    Jets with transverse energy of few TeV are becoming now common in LHC data. Most of these jets are produced by QCD processes and some from the collimated decay of highly boosted objects like W, Z, H0 and top-quark. The study of such QCD jets may shed light on QCD showering processes and the identification of the jets coming from decays may test the Standard Model under extreme conditions and may also provide the first hints for Physics Beyond the Standard Model. A short review of jet algorithms, Correction procedures for pile-up effects and commonly used substructure observables are described.

  10. Fluidic electrodynamics: Approach to electromagnetic propulsion

    SciTech Connect (OSTI)

    Martins, Alexandre A.; Pinheiro, Mario J. [Institute for Plasmas and Nuclear Fusion and Instituto Superior Tecnico Lisboa, Portugal 351.1.21.841.92.43 (Portugal); Department of Physics and Institute for Plasmas and Nuclear Fusion and Instituto Superior Tecnico Lisboa, Portugal 351.1.21.841.93.22 (Portugal)

    2009-03-16

    We report on a new methodological approach to electrodynamics based on a fluidic viewpoint. We develop a systematic approach establishing analogies between physical magnitudes and isomorphism (structure-preserving mappings) between systems of equations. This methodological approach allows us to give a general expression for the hydromotive force, thus re-obtaining the Navier-Stokes equation departing from the appropriate electromotive force. From this ground we offer a fluidic approach to different kinds of issues with interest in propulsion, e.g., the force exerted by a charged particle on a body carrying current; the magnetic force between two parallel currents; the Magnus's force. It is shown how the intermingle between the fluid vector fields and electromagnetic fields leads to new insights on their dynamics. The new concepts introduced in this work suggest possible applications to electromagnetic (EM) propulsion devices and the mastery of the principles of producing electric fields of required configuration in plasma medium.

  11. Engineering Challenges in Antiproton Triggered Fusion Propulsion

    SciTech Connect (OSTI)

    Cassenti, Brice [Department. of Engineering and Science, Rensselaer Polytechnic Institute, 275 Windsor Avenue, Hattford, CT 06120 (United States); Kammash, Terry [Nuclear Engineering Department, University of Michigan, Ann Arbor, MI 48109 (United States)

    2008-01-21

    During the last decade antiproton triggered fusion propulsion has been investigated as a method for achieving high specific impulse, high thrust in a nuclear pulse propulsion system. In general the antiprotons are injected into a pellet containing fusion fuel with a small amount of fissionable material (i.e., an amount less than the critical mass) where the products from the fission are then used to trigger a fusion reaction. Initial calculations and simulations indicate that if magnetically insulated inertial confinement fusion is used that the pellets should result in a specific impulse of between 100,000 and 300,000 seconds at high thrust. The engineering challenges associated with this propulsion system are significant. For example, the antiprotons must be precisely focused. The pellet must be designed to contain the fission and initial fusion products and this will require strong magnetic fields. The fusion fuel must be contained for a sufficiently long time to effectively release the fusion energy, and the payload must be shielded from the radiation, especially the excess neutrons emitted, in addition to many other particles. We will review the recent progress, possible engineering solutions and the potential performance of these systems.

  12. Magnetized target fusion and fusion propulsion.

    SciTech Connect (OSTI)

    Kirkpatrick, R. C. (Ronald C.)

    2001-01-01

    Magnetized target fusion (MTF) is a thermonuclear fusion concept that is intermediate between the two mainline approaches, magnetic confinement and inertial confinement fusion (MCF and ICF). MTF incorporates some aspects of each and offers advantages over each of the mainline approaches. First, it provides a means of reducing the driver power requirements, thereby admitting a wider range of drivers than ICF. Second, the magnetic field is only used for insulation, not confinement, and the plasma is wall confined, so that plasma instabilities are traded in for hydrodynamic instabilities. However, the degree of compression required to reach fusion conditions is lower than for ICF, so that hydrodynamic instabilities are much less threatening. The standoff driver innovation proposes to dynamically form the target plasma and a gaseous shell that compresses and confines the target plasma. Therefore, fusion target fabrication is traded in for a multiplicity of plasma guns, which must work in synchrony. The standoff driver embodiment of MTF leads to a fusion propulsion system concept that is potentially compact and lightweight. We will discuss the underlying physics of MTF and some of the details of the fusion propulsion concept using the standoff driver approach. We discuss here the optimization of an MTF target design for space propulsion.

  13. NASA Advisory Council Subcommittee Recommendation

    E-Print Network [OSTI]

    Rathbun, Julie A.

    NASA Advisory Council Subcommittee Recommendation Subcommittee Name: Planetary Science Chair: Sean in the Lunar Exploration Roadmap, that NASA formulate a transition strategy during the roadmapping process and capabilities built up on the Moon. The PSS further recommends that NASA expand its current level of interaction

  14. NASA Advisory Council Subcommittee Recommendation

    E-Print Network [OSTI]

    Rathbun, Julie A.

    NASA Advisory Council Subcommittee Recommendation Subcommittee Name: Planetary Science Chair: Sean requirements than NASA alone can support. The Cassini-Huygens mission is an example where such a partnership, there are key areas of technological expertise for which NASA will always wish to maintain a position

  15. NASA CR-187041 DESIGN PROGRAM

    E-Print Network [OSTI]

    Rathbun, Julie A.

    NASA CR- 187041 ADVANCED DESIGN PROGRAM Proceedings of the 6 t h Annual Summer Conference University Advanced Design Program Hosted by NASA Lewis Research Center June I 1-15,1990 NATIONAL AERONAUTICS & SPACE ADMINISTRATION UNIVERSITIES SPACE RESEARCH ASSOCIATION #12;#12;#12;#12;#12;#12;NASA

  16. NASA Advisory Council Subcommittee Recommendation

    E-Print Network [OSTI]

    Rathbun, Julie A.

    NASA Advisory Council Subcommittee Recommendation Subcommittee Name: Planetary Science Chair: Sean description of the proposed Recommendation The PSS recommends that NASA and NAC approve the formation). Following NAC and NASA approval of an SBAG, a Small Bodies Workshop will be planned to develop

  17. Propulsive options for a manned Mars transportation system

    SciTech Connect (OSTI)

    Braun, R.D.; Blersch, D.J.

    1989-01-01

    In this investigation, five potential manned Mars transportation systems are compared. These options include: (1) a single vehicle, chemically propelled (CHEM) option, (2) a single vehicle, nuclear thermal propulsion (NTP) option, (3) a single vehicle solar electric propulsion (SEP) option, (4) a single vehicle hybrid nuclear electric propulsion (NEP)/CHEM option, and (5) a dual vehicle option (NEP cargo spacecraft and CHEM manned vehicle). In addition to utilizing the initial vehicle weight in low-earth orbit as a measure of mission feasibility, this study addresses the major technological barriers each propulsive scenario must surpass. It is shown that instead of a single clearly superior propulsion system, each means of propulsion may be favored depending upon the specified program policy and the extent of the desired manned flight time. Furthermore, the effect which aerobraking and multiple transfer cycles have upon mission feasibility is considered. 18 refs.

  18. Simplest AB-Thermonuclear Space Propulsion and Electric Generator

    E-Print Network [OSTI]

    Alexander Bolonkin

    2007-01-19

    The author applies, develops and researches mini-sized Micro- AB Thermonuclear Reactors for space propulsion and space power systems. These small engines directly convert the high speed charged particles produced in the thermonuclear reactor into vehicle thrust or vehicle electricity with maximum efficiency. The simplest AB-thermonuclear propulsion offered allows spaceships to reach speeds of 20,000 50,000 km/s (1/6 of light speed) for fuel ratio 0.1 and produces a huge amount of useful electric energy. Offered propulsion system permits flight to any planet of our Solar system in short time and to the nearest non-Sun stars by E-being or intellectual robots during a single human life period. Key words: AB-propulsion, thermonuclear propulsion, space propulsion, thermonuclear power system.

  19. Jet studies with STAR at RHIC: jet algorithms, jet shapes, jets in AA

    E-Print Network [OSTI]

    Jan Kapitan; for the STAR Collaboration

    2011-11-08

    Hard scattered partons are predicted to be well calibrated probes of the hot and dense medium produced in heavy ion collisions. Interactions of these partons with the medium w ill result in modifications of internal jet structure in Au+Au events compared to that observed in the p+p/d+Au reference. Full jet reconstruction is a promising tool to measu re these effects without the significant biases present in measurements with high-$\\pT$ hadrons. One of the most significant challenges for jet reconstruction in the heavy ion environment comes from the correct characterization of the background fluctuations. The jet mome ntum irresolution due to background fluctuations has to be understood in order to recover the correct jet spectrum. Recent progress in jet reconstruction methodology is discu ssed, as well as recent measurements from p+p, d+Au and Au+Au collisions at $\\sqrt{s_\\mathrm{NN}}=200 \\gev$.

  20. Reconstructed Jets at RHIC

    E-Print Network [OSTI]

    Sevil Salur

    2010-04-30

    To precisely measure jets over a large background such as pile up in high luminosity p+p collisions at LHC, a new generation of jet reconstruction algorithms is developed. These algorithms are also applicable to reconstruct jets in the heavy ion environment where large event multiplicities are produced. Energy loss in the medium created in heavy ion collisions are already observed indirectly via inclusive hadron distributions and di-hadron correlations. Jets can be used to study this energy loss in detail with reduced biases. We review the latest results on jet-medium interactions as seen in A+A collisions at RHIC, focusing on the recent progress on jet reconstruction in heavy ion collisions.

  1. QCD and Jet Physics

    E-Print Network [OSTI]

    B R Webber

    1994-10-12

    The current status of the QCD coupling constant $\\alpha_S$ and experimental and theoretical studies of hadronic jets are reviewed.

  2. Jets in QCD

    SciTech Connect (OSTI)

    Seymour, M.H.

    1996-02-01

    Many analyses at the collider utilize the hadronic jets that are the footprints of QCD partons. These are used both to study the QCD processes themselves and increasingly as tools to study other physics, for example top mass reconstruction. However, jets are not fundamental degrees of freedom in the theory, so we need an {ital operational} {ital jet} {ital definition} and {ital reliable} {ital methods} {ital to} {ital calculate} {ital their} {ital properties}. This talk covers both of these important areas of jet physics. {copyright} {ital 1996 American Institute of Physics.}

  3. Interpretation of extragalactic jets

    SciTech Connect (OSTI)

    Norman, M.L.

    1985-01-01

    The nature of extragalatic radio jets is modeled. The basic hypothesis of these models is that extragalatic jets are outflows of matter which can be described within the framework of fluid dynamics and that the outflows are essentially continuous. The discussion is limited to the interpretation of large-scale (i.e., kiloparsec-scale) jets. The central problem is to infer the physical parameters of the jets from observed distributions of total and polarized intensity and angle of polarization as a function of frequency. 60 refs., 6 figs.

  4. A Microwave Thruster for Spacecraft Propulsion Chiravalle, Vincent...

    Office of Scientific and Technical Information (OSTI)

    that have higher specific impulse and lower thrust than conventional chemical rocket engines. Examples of electric propulsion devices are given in this presentation and it is...

  5. Vehicle Technologies Office: Propulsion Materials for Cars and Trucks

    Broader source: Energy.gov [DOE]

    Manufacturers use propulsion (or powertrain) materials in the components that move vehicles of every size and shape. Conventional vehicles use these materials in components such as the engine,...

  6. Marine Hybrid Propulsion Market Revenue is anticipated to Reach...

    Open Energy Info (EERE)

    ferry operators are the major adopters of marine hybrid propulsion systems across the world. These vessels primarily operate in coastal areas and inland waterways, where emission...

  7. Vehicle Technologies Office: 2011 Propulsion Materials R&D Annual...

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

    electronics development. 2011propulsionmaterials.pdf More Documents & Publications Vehicle Technologies Office: 2009 Propulsion Materials R&D Annual Progress Report Vehicle...

  8. Vehicle Technologies Office: 2013 Propulsion Materials R&D Annual...

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

    research and development projects funded by the Propulsion Materials subprogram in the Vehicle Technologies Office. Past year's reports are listed on the Annual Progress Reports...

  9. Vehicle Technologies Office: 2008 Propulsion Materials R&D Annual...

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

    2008propulsionmaterials.pdf More Documents & Publications Vehicle Technologies Office: 2010 Propulsion Materials R&D Annual Progress Report Vehicle Technologies Office: 2013...

  10. Propulsion Materials R&D | Clean Energy | ORNL

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

    area of Propulsion Materials is designed to identify and develop advanced materials and processes that improve powertrain system efficiency and reduce emissions. Cutting-edge...

  11. Large-Eddy Simulation for Green Energy and Propulsion Systems...

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

    Large-Eddy Simulation for Green Energy and Propulsion Systems PI Name: Umesh Paliath PI Email: paliath@ge.com Institution: General Electric Allocation Program: INCITE Allocation...

  12. Enabling Green Energy and Propulsion Systems via Direct Noise...

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

    Umesh Paliath, GE Global Research; Joe Insley, Argonne National Laboratory Enabling Green Energy and Propulsion Systems via Direct Noise Computation PI Name: Umesh Paliath PI...

  13. FY2013 Propulsion Materials R&D Annual Progress Report

    SciTech Connect (OSTI)

    none,

    2014-01-01

    This report describes the progress made during 2013 on the research and development projects funded by the Propulsion Materials subprogram in the Vehicle Technologies Office.

  14. Integrated Mathematical Modeling Software Series of Vehicle Propulsion...

    Office of Energy Efficiency and Renewable Energy (EERE) Indexed Site

    Mathematical Modeling Software Series of Vehicle Propulsion System: (1) Tractive Effort (T sub ew) of Vehicle Road WheelTrack Sprocket Integrated Mathematical Modeling Software...

  15. Vehicle Technologies Office: 2010 Propulsion Materials R&D Annual...

    Office of Energy Efficiency and Renewable Energy (EERE) Indexed Site

    Propulsion Materials R&D Annual Progress Report Vehicle Technologies Office Merit Review 2014: Cost-Effective Fabrication of High-Temperature Ceramic Capacitors for Power Inverters...

  16. Using Nanotechnology in Agriculture Kent Pinkerton, Ph.D.

    E-Print Network [OSTI]

    Leistikow, Bruce N.

    Laser only 17 mm 20 mm Untreated No Residual MWCN T + Laser #12;Aerogels (Frozen Smoke) for Increased Insulation and Energy Storage Image Source: NASA Jet Propulsion Lab (http://stardust.jpl.nasa.gov/photo/aerogel

  17. On-board Analysis of Uncalibrated Data for a Spacecraft at Mars

    E-Print Network [OSTI]

    Schaffer, Steven

    timothy.stough@jpl.nasa.gov Benyang Tang benyang.tang@jpl.nasa.gov Jet Propulsion Laboratory California limited CPU and RAM resources. In many cases, the data available is uncalibrated. An emerging paradigm

  18. Taming jets in magnetised fluids

    E-Print Network [OSTI]

    Kosuga, Yusuke; Brummell, Nicholas

    2010-01-01

    Down right: Cancellation of stresses and quenching of Jets.to Reynolds stress driven jets, since both ?ux expulsion andTaming Jets in magnetized ?uids Y. Kosuga 1 and N. H.

  19. QCD Jets and Parton Showers

    E-Print Network [OSTI]

    Bryan R. Webber

    2010-09-29

    I discuss the calculation of QCD jet rates in e+e- annihilation as a testing ground for parton shower simulations and jet finding algorithms.

  20. Structure and Mixing Characterization of Variable Density Transverse Jet Flows

    E-Print Network [OSTI]

    Gevorkyan, Levon

    2015-01-01

    4 Transverse Jet Mixing . . . . . . . . . . . . . . . . . .Jet TrajectoryTransverse Jet Structure and

  1. Nonaxisymmetric Poynting Jets

    E-Print Network [OSTI]

    Samuel E. Gralla; Ted Jacobson

    2015-07-29

    The relativistic plasma jets from a misaligned black hole-accretion disk system will not be axially symmetric. Here we analyze nonaxisymmetric, stationary, translation invariant jets in the force-free approximation where the field energy dominates the particle energy. We derive a stream equation for these configurations involving the flux function $\\psi$ for the transverse magnetic field, the linear velocity $v(\\psi)$ of field lines along the jet, and the longitudinal magnetic field $B_z(\\psi)$. The equations can be completely solved when $|v|=1$, and when $|v|jet that has vanishing electromagnetic pressure $\\tfrac{1}{2}(B^2-E^2)$ and requires no external pressure for confinement. We prove that such self-confinement is impossible when $B^2>E^2$. Finally, we write down specific solutions approximating numerical results for the nonaxisymmetric jet produced by a spinning black hole in an external, misaligned magnetic field.

  2. Ultrahigh Specific Impulse Nuclear Thermal Propulsion

    SciTech Connect (OSTI)

    Anne Charmeau; Brandon Cunningham; Samim Anghaie

    2009-02-09

    Research on nuclear thermal propulsion systems (NTP) have been in forefront of the space nuclear power and propulsion due to their design simplicity and their promise for providing very high thrust at reasonably high specific impulse. During NERVA-ROVER program in late 1950's till early 1970's, the United States developed and ground tested about 18 NTP systems without ever deploying them into space. The NERVA-ROVER program included development and testing of NTP systems with very high thrust (~250,000 lbf) and relatively high specific impulse (~850 s). High thrust to weight ratio in NTP systems is an indicator of high acceleration that could be achieved with these systems. The specific impulse in the lowest mass propellant, hydrogen, is a function of square root of absolute temperature in the NTP thrust chamber. Therefor optimizing design performance of NTP systems would require achieving the highest possible hydrogen temperature at reasonably high thrust to weight ratio. High hydrogen exit temperature produces high specific impulse that is a diret measure of propellant usage efficiency.

  3. Advanced hybrid vehicle propulsion system study

    SciTech Connect (OSTI)

    Schwarz, R.

    1982-05-01

    Results of a study of an advanced heat engine/electric automotive hybrid propulsion system are presented. The system uses a rotary stratified charge engine and an ac motor/controller in a parallel hybrid configuration. The three tasks of the study were (1) parametric studies involving five different vehicle types, (2) design trade-off studies to determine the influence of various vehicle and propulsion system parameters on system performance fuel economy and cost, and (3) a conceptual design establishing feasibility at the selected approach. Energy consumption for the selected system was .034 l/km (61.3 mpg) for the heat engine and .221 kWh/km (.356 kWh/mi) for the electric power system over a modified J227a schedule D driving cycle. Life cycle costs were 7.13 cents/km (11.5 cents/mi) at $2/gal gasoline and 7 cents/kWh electricity for 160,000 km (100,000 mi) life.

  4. Permanent magnet helicon source for ion propulsion Francis F. Chen

    E-Print Network [OSTI]

    Chen, Francis F.

    Permanent magnet helicon source for ion propulsion Francis F. Chen Electrical Engineering that great savings in size and weight can be obtained by using specially designed permanent magnets (PMs by at least two groups for generating ions for space propulsion: the HDLT concept at the Australian National

  5. FY2009 Annual Progress Report for Propulsion Materials

    SciTech Connect (OSTI)

    none,

    2010-01-16

    The Propulsion Materials program focuses on enabling and innovative materials technologies that are critical in improving the efficiency of advanced engines. Projects within the Propulsion Materials Program address materials concerns that directly impact the critical technical barriers in each of these programs—barriers such as fuel efficiency, thermal management, emissions reduction, and reduced manufacturing costs.

  6. Optimization of Chiral Structures for Microscale Propulsion Eric E. Keaveny,*,

    E-Print Network [OSTI]

    Shelley, Michael

    of flagellated cells,21-24 wave shapes in lubrication-layer propulsion and pumping,25,26 and effective slipOptimization of Chiral Structures for Microscale Propulsion Eric E. Keaveny,*, Shawn W. Walker in the construction of micro- and nanoscale biomimetic swimmers.5-13 These devices are powered by time

  7. Advances in Magnetized Plasma Propulsion and Radiation Shielding Robert Winglee

    E-Print Network [OSTI]

    Shepherd, Simon

    Advances in Magnetized Plasma Propulsion and Radiation Shielding Robert Winglee Department of Earth Propulsion (M2P2)3,4 . In this scheme a magnetic field attached to the spacecraft is expanded-mangetosphere, that is magnetic field inflated by the injection of plasma have several applications key to the exploration

  8. A comparison of propulsion systems for potential space mission applications

    SciTech Connect (OSTI)

    Harvego, E.A.; Sulmeisters, T.K.

    1987-01-01

    A derivative of the NERVA nuclear rocket engine was compared with a chemical propulsion system and a nuclear electric propulsion system to assess the relative capabilities of the different propulsion system options for three potential space missions. The missions considered were (1) orbital transfer from low earth orbit (LEO) to geosynchronous earth orbit (GEO), (2) LEO to a lunar base, and (3) LEO to Mars. The results of this comparison indicate that the direct-thrust NERVA-derivative nuclear rocket engine has the best performance characteristics for the missions considered. The combined high thrust and high specific impulse achievable with a direct-thrust nuclear stage permits short operating times (transfer times) comparable to chemical propulsion systems, but with considerably less required propellant. While nuclear-electric propulsion systems are more fuel efficient than either direct-nuclear or chemical propulsion, they are not stand-alone systems, since their relatively low thrust levels require the use of high-thrust ferry or lander stages in high gravity applications such as surface-to-orbit propulsion. The extremely long transfer times and inefficient trajectories associated with electric propulsion systems were also found to be a significant drawback.

  9. Particle Physics Phenomenology 8. QCD jets and jet algorithms

    E-Print Network [OSTI]

    Sjöstrand, Torbjörn

    Particle Physics Phenomenology 8. QCD jets and jet algorithms Torbj¨orn Sj¨ostrand Department k. All rotationally symmetric. SppS (CERN): need to separate beam jets from highp ones. First solution: cone jets in (, ) space, e.g. UA1. (Second solution: clustering like Durham

  10. A review of carbide fuel corrosion for nuclear thermal propulsion applications

    SciTech Connect (OSTI)

    Pelaccio, D.G.; El-Genk, M.S. [Univ. of New Mexico, Albuquerque, NM (United States). Inst. for Space Nuclear Power Studies; Butt, D.P. [Los Alamos National Lab., NM (United States)

    1993-12-01

    At the operation conditions of interest in nuclear thermal propulsion reactors, carbide materials have been known to exhibit a number of life limiting phenomena. These include the formation of liquid, loss by vaporization, creep and corresponding gas flow restrictions, and local corrosion and fuel structure degradation due to excessive mechanical and/or thermal loading. In addition, the radiation environment in the reactor core can produce a substantial change in its local physical properties, which can produce high thermal stresses and corresponding stress fractures (cracking). Time-temperature history and cyclic operation of the nuclear reactor can also accelerate some of these processes. The University of New Mexico`s Institute for Space Nuclear Power Studies, under NASA sponsorship has recently initiated a study to model the complicated hydrogen corrosion process. In support of this effort, an extensive review of the open literature was performed, and a technical expert workshop was conducted. This paper summarizes the results of this review.

  11. Hydrogen loops in existing reactors for testing fuel elements for nuclear propulsion

    SciTech Connect (OSTI)

    Olsen, C.S.; Welland, H.; Abraschoff, J. (Idaho National Engineering Laboratory, EG G Idaho Inc., P.O. Box 1625, Idaho Falls, Idaho 83415 (United States)); Thoms, K. (Oak Ridge National Laboratory, P.O. Box, Oak Ridge, Tennessee 37831-8087 (United States))

    1993-01-15

    The Space Exploration Initiative (SEI) has revitalized interest in adapting nuclear energy for power and propulsion. Prior to the selection of a nuclear thermal propulsion (NTP) system, extensive testing of the various proposed concepts will be required. In today's environmental, safety and health culture, full size rocket engine tests as were done under the Rover/NERVA program will be extremely difficult and expensive to perform and meet NASA's schedules. A different test strategy uses a hydrogen loop in an existing reactor to test a wide variety of single elements or clusters of elements for fuel qualification. This approach is expected to reduce operating and capital costs and expedite the testing schedule. This paper examines the potential of performing subscale tests in a hydrogen loop in an existing reactor such as the Advanced Test Reactor (ATR) at the Idaho National Engineering Laboratory or the High Flux Isotope Reactor (HFIR) at the Oak Ridge National Laboratory. The HFIR is expected to achieve power densities comparable to those achieved in ATR because of the 85 MWt power level and the high thermal and fast flux levels. The available length and diameter of the test region of FHIR are 60 cm and 10 cm whereas the available length and diameter of the test region of ATR are 120 cm and 12 cm respectively.

  12. Small Fast Spectrum Reactor Designs Suitable for Direct Nuclear Thermal Propulsion

    SciTech Connect (OSTI)

    Bruce G. Schnitzler; Stanley K. Borowski

    2012-07-01

    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. Past studies, in particular those in support of both the Strategic Defense Initiative (SDI) and Space Exploration Initiative (SEI), have shown nuclear thermal propulsion systems provide superior performance for high mass high propulsive delta-V missions. The recent NASA Design Reference Architecture (DRA) 5.0 Study re-examined mission, payload, and transportation system requirements for a human Mars landing mission in the post-2030 timeframe. Nuclear thermal propulsion was again identified as the preferred in-space transportation system. A common nuclear thermal propulsion stage with three 25,000-lbf thrust engines was used for all primary mission maneuvers. Moderately lower thrust engines may also have important roles. In particular, lower thrust engine designs demonstrating the critical technologies that are directly extensible to other thrust levels are attractive from a ground testing perspective. An extensive nuclear thermal rocket technology development effort was conducted from 1955-1973 under the Rover/NERVA Program. Both graphite and refractory metal alloy fuel types were pursued. Reactors and engines employing graphite based fuels were designed, built and ground tested. A number of fast spectrum reactor and engine designs employing refractory metal alloy fuel types were proposed and designed, but none were built. 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 graphite based fuel design incorporating lessons learned from the very successful technology development program. The SNRE was a nominal 16,000-lbf thrust engine originally intended for unmanned applications with relatively short engine operations and the engine and stage design were constrained to fit within the payload volume of the then planned space shuttle. The SNRE core design utilized hexagonal fuel elements and hexagonal structural support elements. The total number of elements can be varied to achieve engine designs of higher or lower thrust levels. Some variation in the ratio of fuel elements to structural elements is also possible. Options for SNRE-based engine designs in the 25,000-lbf thrust range were described in a recent (2010) Joint Propulsion Conference paper. The reported designs met or exceeded the performance characteristics baselined in the DRA 5.0 Study. Lower thrust SNRE-based designs were also described in a recent (2011) Joint Propulsion Conference paper. Recent activities have included parallel evaluation and design efforts on fast spectrum engines employing refractory metal alloy fuels. These efforts include evaluation of both heritage designs from the Argonne National Laboratory (ANL) and General Electric Company GE-710 Programs as well as more recent designs. Results are presented for a number of not-yet optimized fast spectrum engine options.

  13. Angular Scaling In Jets

    SciTech Connect (OSTI)

    Jankowiak, Martin; Larkoski, Andrew J.; /SLAC

    2012-02-17

    We introduce a jet shape observable defined for an ensemble of jets in terms of two-particle angular correlations and a resolution parameter R. This quantity is infrared and collinear safe and can be interpreted as a scaling exponent for the angular distribution of mass inside the jet. For small R it is close to the value 2 as a consequence of the approximately scale invariant QCD dynamics. For large R it is sensitive to non-perturbative effects. We describe the use of this correlation function for tests of QCD, for studying underlying event and pile-up effects, and for tuning Monte Carlo event generators.

  14. David Kortenkamp NASA Johnson Space Center

    E-Print Network [OSTI]

    Kortenkamp, David

    David Kortenkamp NASA Johnson Space Center David Kortenkamp NASA Johnson Space Center Distributed Systems David Kortenkamp NASA Johnson Space Center/Metrica Inc. Houston TX 77058 kortenkamp@jsc.nasa.gov http://www.traclabs.com/~korten David Kortenkamp NASA Johnson Space Center/Metrica Inc. Houston TX

  15. 60Dr. Gregory A. Dorais, NASA Ames Research Center Dr. David Kortenkamp, NASA Johnson Space Center NASA HCA Applications OutlineNASA HCA Applications Outline

    E-Print Network [OSTI]

    Kortenkamp, David

    60Dr. Gregory A. Dorais, NASA Ames Research Center Dr. David Kortenkamp, NASA Johnson Space Center NASA HCA Applications OutlineNASA HCA Applications Outline l 3T Control Architecture ­ architecture Satellite Assistant (under development) #12;61Dr. Gregory A. Dorais, NASA Ames Research Center Dr. David

  16. NASA Cold Land Processes Field Experiment

    E-Print Network [OSTI]

    NASA Cold Land Processes Field Experiment Overview and Preliminary Results NASA Cold Land Processes Field Experiment Overview and Preliminary Results NASA Cold Land ProcessesNASA Cold Land Processes Field properties using active and passive microwave remote sensing. NASA DC-8 Airborne Laboratory with AIRSAR

  17. Nonaxisymmetric Poynting Jets

    E-Print Network [OSTI]

    Gralla, Samuel E

    2015-01-01

    The relativistic plasma jets from a misaligned black hole-accretion disk system will not be axially symmetric. Here we analyze nonaxisymmetric, stationary, translation invariant jets in the force-free approximation where the field energy dominates the particle energy. We derive a stream equation for these configurations involving the flux function $\\psi$ for the transverse magnetic field, the linear velocity $v(\\psi)$ of field lines along the jet, and the longitudinal magnetic field $B_z(\\psi)$. The equations can be completely solved when $|v|=1$, and when $|v|E^2$. Finally, we write down specific solutions approximating numerical results for the nonaxisymmetric jet produced by a spinning black hole in an external, misaligned magnetic field.

  18. Jets with Reversing Buoyancy

    E-Print Network [OSTI]

    Pandya, R V R

    2015-01-01

    A jet of heavy fluid is injected upwards, at time $t=0$, into a lighter fluid and reaches a maximum height at time $t=t_i$ and then flows back around the upward flow. A similar flow situation occurs for a light fluid injected downward into a heavy one. In this paper an exact analytical expression for $t_i$ is derived. The expression remains valid for laminar and turbulent buoyant jets with or without swirl.

  19. High Power Electric Propulsion System for NEP: Propulsion and Trajectory Options

    SciTech Connect (OSTI)

    Koppel, Christophe R.; Duchemin, Olivier; Valentian, Dominique

    2006-01-20

    Recent US initiatives in Nuclear Propulsion lend themselves naturally to raising the question of the assessment of various options and particularly to propose the High Power Electric Propulsion Subsystem (HPEPS) for the Nuclear Electric Propulsion (NEP). The purpose of this paper is to present the guidelines for the HPEPS with respect to the mission to Mars, for automatic probes as well as for manned missions. Among the various options, the technological options and the trajectory options are pointed out. The consequences of the increase of the electrical power of a thruster are first an increase of the thrust itself, but also, as a general rule, an increase of the thruster performance due to its higher efficiency, particularly its specific impulse increase. The drawback is as a first parameter, the increase of the thruster's size, hence the so-called 'thrust density' shall be high enough or shall be drastically increased for ions thrusters. Due to the large mass of gas needed to perform the foreseen missions, the classical xenon rare gas is no more in competition, the total world production being limited to 20 -40 tons per year. Thus, the right selection of the propellant feeding the thruster is of prime importance. When choosing a propellant with lower molecular mass, the consequences at thruster level are an increase once more of the specific impulse, but at system level the dead mass may increase too, mainly because the increase of the mass of the propellant system tanks. Other alternatives, in rupture with respect to the current technologies, are presented in order to make the whole system more attractive. The paper presents a discussion on the thruster specific impulse increase that is sometime considered an increase of the main system performances parameter, but that induces for all electric propulsion systems drawbacks in the system power and mass design that are proportional to the thruster specific power increase (kW/N). The electric thruster specific impulse shall be optimized w.r.t. the mission. The trajectories taken into account in the paper are constrained by the allowable duration of the travel and the launcher size. The multi-arcs trajectories to Mars (using an optimized combination of chemical and Electric propulsion) are presented in detail. The compatibility with NEP systems that implies orbiting a sizeable nuclear reactor and a power generation system capable of converting thermal into electric power, with minimum mass and volumes fitting in with Ariane 5 or the Space Shuttle bay, is assessed.

  20. NASA/CP-2010-216215 Proceedings of the Second NASA Formal

    E-Print Network [OSTI]

    Muñoz, César A.

    April 2010 NASA/CP-2010-216215 Proceedings of the Second NASA Formal Methods Symposium Edited by César Muñoz NASA Langley Research Center, Hampton, Virginia #12;NASA STI Program . . . in Profile Since its founding, NASA has been dedicated to the advancement of aeronautics and space science. The NASA

  1. Meeting Report--NASA Radiation Biomarker Workshop

    E-Print Network [OSTI]

    Straume, Tore

    2008-01-01

    Tore Straume, Ph.D. , MS 236-7, NASA Ames Research Center,Running Title: NASA Radiation Biomarker Workshop Straume,Res. 156, 460-466 (2001). NASA Bioastronautics Roadmap (

  2. Test facilities for evaluating nuclear thermal propulsion systems

    SciTech Connect (OSTI)

    Beck, D.F.; Allen, G.C.; Shipers, L.R.; Dobranich, D.; Ottinger, C.A.; Harmon, C.D.; Fan, W.C. ); Todosow, M. )

    1992-09-22

    Interagency panels evaluating nuclear thermal propulsion (NTP) development options have consistently recognized the need for constructing a major new ground test facility to support fuel element and engine testing. This paper summarizes the requirements, configuration, and baseline performance of some of the major subsystems designed to support a proposed ground test complex for evaluating nuclear thermal propulsion fuel elements and engines being developed for the Space Nuclear Thermal Propulsion (SNTP) program. Some preliminary results of evaluating this facility for use in testing other NTP concepts are also summarized.

  3. WORKSHOP REPORT:Light-Duty Vehicles Technical Requirements and Gaps for Lightweight and Propulsion Materials

    Office of Energy Efficiency and Renewable Energy (EERE)

    WORKSHOP REPORT:Light-Duty Vehicles Technical Requirements and Gaps for Lightweight and Propulsion Materials

  4. Alkali metal Rankine cycle boiler technology challenges and some potential solutions for space nuclear power and propulsion applications

    SciTech Connect (OSTI)

    Stone, J.R.

    1994-07-01

    Alkali metal boilers are of interest for application to future space Rankine cycle power conversion systems. Significant progress on such boilers was accomplished in the 1960's and early 1970's, but development was not continued to operational systems since NASA's plans for future space missions were drastically curtailed in the early 1970's. In particular, piloted Mars missions were indefinitely deferred. With the announcement of the Space Exploration Initiative (SEI) in July 1989 by President Bush, interest was rekindled in challenging space missions and, consequently in space nuclear power and propulsion. Nuclear electric propulsion (NEP) and nuclear thermal propulsion (NTP) were proposed for interplanetary space vehicles, particularly for Mars missions. The potassium Rankine power conversion cycle became of interest to provide electric power for NEP vehicles and for 'dual-mode' NTP vehicles, where the same reactor could be used directly for propulsion and (with an additional coolant loop) for power. Although the boiler is not a major contributor to system mass, it is of critical importance because of its interaction with the rest of the power conversion system; it can cause problems for other components such as excess liquid droplets entering the turbine, thereby reducing its life, or more critically, it can drive instabilities-some severe enough to cause system failure. Funding for the SEI and its associated technology program from 1990 to 1993 was not sufficient to support significant new work on Rankine cycle boilers for space applications. In Fiscal Year 1994, funding for these challenging missions and technologies has again been curtailed, and planning for the future is very uncertain. The purpose of this paper is to review the technologies developed in the 1960's and 1970's in the light of the recent SEI applications. In this way, future Rankine cycle boiler programs may be conducted most efficiently.

  5. Form, function and flow in the plankton : jet propulsion and filtration by pelagic tunicates

    E-Print Network [OSTI]

    Sutherland, Kelly Rakow

    2010-01-01

    Trade-offs between filtration rate and swimming performance among several salp species with distinct morphologies and swimming styles were compared. Small-scale particle encounter at the salp filtering apparatus was also ...

  6. JET PROPULSION LABORATORY 1981 ANNUAL REPORT Qwer The tem:lln of the

    E-Print Network [OSTI]

    's Message 2 Deep Space Exploration 4 Telecommunicatlons Systems 18 Earth Observations 24 Energy of understand- ing of the solar system's major planet. New missions-the In- frared Astronomical Satellite Desert) Ul northern Iran IS seen In thIS color.-processed IIIDsalC of nnages taken Iry lPL's Shuttle

  7. Jet Propulsion Laboratory 1974-1975 Annual Report Cover The Manner 10 commemoratMl

    E-Print Network [OSTI]

    spectroscopy, drop dynamics, laser technol- ogy, and photovoltaic research. Major trends were beginning industry's capacity to utilize solar radiation in reducing the nation's dependence on fossil fuels

  8. Nondestructive Evaluation and Monitoring Projects NASA White...

    Office of Energy Efficiency and Renewable Energy (EERE) Indexed Site

    Nondestructive Evaluation and Monitoring Projects NASA White Sands Test Facility (WSTF) Nondestructive Evaluation and Monitoring Projects NASA White Sands Test Facility (WSTF)...

  9. Heat pipe cooled heat rejection subsystem modelling for nuclear electric propulsion. Final report

    SciTech Connect (OSTI)

    Moriarty, M.P.

    1993-11-01

    NASA LeRC is currently developing a FORTRAN based computer model of a complete nuclear electric propulsion (NEP) vehicle that can be used for piloted and cargo missions to the Moon or Mars. Proposed designs feature either a Brayton or a K-Rankine power conversion cycle to drive a turbine coupled with rotary alternators. Both ion and magnetoplasmodynamic (MPD) thrusters will be considered in the model. In support of the NEP model, Rocketdyne is developing power conversion, heat rejection, and power management and distribution (PMAD) subroutines. The subroutines will be incorporated into the NEP vehicle model which will be written by NASA LeRC. The purpose is to document the heat pipe cooled heat rejection subsystem model and its supporting subroutines. The heat pipe cooled heat rejection subsystem model is designed to provide estimate of the mass and performance of the equipment used to reject heat from Brayton and Rankine cycle power conversion systems. The subroutine models the ductwork and heat pipe cooled manifold for a gas cooled Brayton; the heat sink heat exchanger, liquid loop piping, expansion compensator, pump and manifold for a liquid loop cooled Brayton; and a shear flow condenser for a K-Rankine system. In each case, the final heat rejection is made by way of a heat pipe radiator. The radiator is sized to reject the amount of heat necessary.

  10. FY2011 Annual Progress Report for Propulsion Materials

    SciTech Connect (OSTI)

    Davis, Patrick B.; Schutte, Carol L.; Gibbs, Jerry L.

    2011-12-01

    Annual Progress Report for Propulsion Materials focusing on enabling and innovative materials technologies that are critical in improving the efficiency of advanced engines by providing enabling materials support for combustion, hybrid, and power electronics development.

  11. A doubly-fed machine for propulsion applications

    E-Print Network [OSTI]

    Tomovich, Michael S. (Michael Stephen)

    2014-01-01

    A doubly fed machine for propulsion applications is proposed, which, given the presence of AC and DC power sources, can be utilized in order to improve efficiency, weight, volume, and sizing of the rotor power electronics. ...

  12. Performance of a boundary layer ingesting propulsion system

    E-Print Network [OSTI]

    Plas, Angélique (Angélique Pascale)

    2006-01-01

    This thesis presents an assessment of the aerodynamic performance of an aircraft propulsion system, with embedded engines, in the presence of aircraft fuselage boundary layer ingestion (BLI). The emphasis is on defining ...

  13. Assessment of propfan propulsion systems for reduced environmental impact

    E-Print Network [OSTI]

    Peters, Andreas, Ph. D. Massachusetts Institute of Technology

    2010-01-01

    Current aircraft engine designs tend towards higher bypass ratio, low-speed fan designs for improved fuel burn, reduced emissions and noise. Alternative propulsion concepts include counter-rotating propfans (CRPs) which ...

  14. Numerical Study of Flexible Flapping Wing Propulsion , Mingjun Wei

    E-Print Network [OSTI]

    Wei, Mingjun

    Numerical Study of Flexible Flapping Wing Propulsion Tao Yang , Mingjun Wei New Mexico State in 1912.4 The Knoller-Betz effect was verified experimentally in a wind tunnel by Katzmayr in 1922

  15. Novel turbomachinery concepts for highly integrated airframe/propulsion systems

    E-Print Network [OSTI]

    Shah, Parthiv N

    2007-01-01

    Two novel turbomachinery concepts are presented as enablers to advanced flight missions requiring integrated airframe/propulsion systems. The first concept is motivated by thermal management challenges in low-to-high Mach ...

  16. Naval Nuclear Propulsion Plants | National Nuclear Security Administra...

    National Nuclear Security Administration (NNSA)

    and works in an office building. U.S. naval nuclear propulsion plants use a pressurized-water reactor design that has two basic systems: the primary system and the secondary...

  17. Porous material and process development for electrospray propulsion applications

    E-Print Network [OSTI]

    Arestie, Steven Mark

    2014-01-01

    Ion electrospray propulsion devices rely on the transportation of ionic liquid propellant to emission regions where ions are extracted at high velocities. One such method involves the use of porous substrates to passively ...

  18. FY2010 Annual Progress Report for Propulsion Materials

    SciTech Connect (OSTI)

    Davis, Patrick B.; Schutte, Carol L.; Gibbs, Jerry L.

    2011-01-01

    The Propulsion Materials Technology actively supports the energy security and reduction of greenhouse emissions goals of the Vehicle Technologies Program by developing advanced materials that enable development of higher efficiency powertrains for ground transportation. Propulsion Materials works closely with the other disciplines within the VT Program to identify the materials properties essential for the development of cost-effective, highly efficient, and environmentally friendly next-generation heavy and light duty powertrains.

  19. Design tool needs for space nuclear propulsion systems

    SciTech Connect (OSTI)

    Klein, A.C. (Oregon State Univ., Corvallis (United States)); Lewis, B.R. (Atom Analysis, Inc., Portland, OR (United States))

    1992-01-01

    The interest in a return trip for humans to the moon and a pioneering voyage to Mars has rekindled interest in the use of nuclear reactors to provide propulsion for both piloted and robotic space vehicles. Two types of nuclear reactor-based propulsion systems are currently envisioned: nuclear thermal propulsion (NTP) and nuclear electric propulsion (NEP). The former relies on the direct heating and exhaust of a propellant within the core of the reactor, while the latter utilizes ion thruster engines for propulsion, and the nuclear reactor supplies the large amount of electrical power required to drive the engines. Another direct contrast between the NTP and NEP concepts is the length of reactor operation. The NTP nuclear rocket core is required to produce large amounts of thermal power for relatively short bursts (on the order of minutes to hours), and the NEP reactor core operates for a much longer period of time (on the order of days to months) with a steady-state electrical power output. The design of these types of nuclear reactor systems requires the use of specific analysis tools, some of which already exist and others that need considerable development. The general areas in which design tools are needed in the development of systems for space nuclear propulsion include the following: (1) neutronics design - both steady-state and transient applications including thermal feedback effects; (2) thermal-hydraulics design - again, both steady-state and transient applications with coupling to and from the neutronics design codes; (3) materials analysis tools - due to the high temperatures and high stresses required for efficient propulsion operation, increased importance will be placed on understanding the material responses; and (4) systems analysis - these codes allow optimizaiton of the entire propulsion system.

  20. The first calculation of fractional jets

    E-Print Network [OSTI]

    Bertolini, Daniele

    In collider physics, jet algorithms are a ubiquitous tool for clustering particles into discrete jet objects. Event shapes offer an alternative way to characterize jets, and one can define a jet multiplicity event shape, ...

  1. Gudrun's (NLO) list pp->WW jet

    E-Print Network [OSTI]

    Huston, Joey

    Gudrun's (NLO) list 2->3 pp->WW jet pp->VVV pp->H + 2 jets 2->4 pp->4 jets pp->tT + 2jets p->tT bB pp->V+ 3 jets pp->VV + 2 jets pp->VVV + jet pp->WW bB From technology point-of-view start with massless cases such as + 2 jets then add progressively more difficult calculations (additional scales

  2. Jets in Particle Colliders Andrew Wong!

    E-Print Network [OSTI]

    Budker, Dmitry

    Jets in Particle Colliders Andrew Wong! #12;Topics · What are jets? · How are they produced? · What do we use to study jets? #12;What are jets? · Bunch of different jets #12;Pretty picture! #12;What's in a jet? · Hadrons ­ Kaons, Pions, Protons, Neutrons · Leptons ­ Mainly electrons and muons · These have

  3. Organic vapor jet printing system

    DOE Patents [OSTI]

    Forrest, Stephen R

    2012-10-23

    An organic vapor jet printing system includes a pump for increasing the pressure of an organic flux.

  4. Jet Fuel from Microalgal Lipids

    SciTech Connect (OSTI)

    Not Available

    2006-07-01

    A fact sheet on production of jet fuel or multi-purpose military fuel from lipids produced by microalgae.

  5. 2007 March 12 NASA Science Mission Directorate

    E-Print Network [OSTI]

    Preliminary list of adoption issues ROSES 2007 funding opportunities NASA Report to Unidata Policy Committee products within NASA · Make sure Unidata is aware of NASA funding opportunities · Promote links to NASA WMS Earth Sciences Data and Information Services Center (GES DISC) · Rainfall, solar irradiance, humidity

  6. Dr. David Kortenkamp NASA Johnson Space Center

    E-Print Network [OSTI]

    Kortenkamp, David

    Dr. David Kortenkamp NASA Johnson Space Center Dr. David Kortenkamp NASA Johnson Space Center Intelligent Robots for Space Applications Intelligent Robots for Space Applications Dr. David Kortenkamp NASA Johnson Space Center/Metrica Inc. Houston TX 77058 kortenkamp@jsc.nasa.gov http

  7. Origins Program Update Henry Throop, NASA HQ

    E-Print Network [OSTI]

    Throop, Henry

    Origins Program Update Henry Throop, NASA HQ Program officer: Origins of Solar Systems (OSS Overview · Origins is one of NASA's core research & analysis (R&A) programs, focusing on... · # 1, 2, 3: NASA Planetary Science Division (Henry Throop), $6M/yr · # 4, 5: NASA Astrophysics Division (Mario

  8. NASA/TM2009215726 Formally Verified Practical

    E-Print Network [OSTI]

    Muñoz, César A.

    NASA/TM­2009­215726 Formally Verified Practical Algorithms For Recovery From Loss of Separation of Aerospace, Hampton, Virginia June 2009 #12;The NASA STI Program Office . . . in Profile Since its founding, NASA has been dedicated to the advancement of aeronautics and space science. The NASA Scientific

  9. NASA Launches Next-Generation Communications Satellite

    E-Print Network [OSTI]

    Christian, Eric

    .nasa.gov Volume 9 Issue 1 February 2013 #12;T he first of NASA's three next-generation Tracking and Data Relay Space Launch Complex-41. After a three-month test phase, NASA will accept the spacecraft for additional rocket blasts off from Space Launch Complex-41 with NASA's Tracking and Data Relay Satellite (TDRS

  10. December 2003 NASA/TM--2003212809

    E-Print Network [OSTI]

    by NASA-sponsored contractors and grantees. · CONFERENCE PUBLICATION. Collected papers from scientific

  11. Feasibility of MHD submarine propulsion. Phase II, MHD propulsion: Testing in a two Tesla test facility

    SciTech Connect (OSTI)

    Doss, E.D.; Sikes, W.C.

    1992-09-01

    This report describes the work performed during Phase 1 and Phase 2 of the collaborative research program established between Argonne National Laboratory (ANL) and Newport News Shipbuilding and Dry Dock Company (NNS). Phase I of the program focused on the development of computer models for Magnetohydrodynamic (MHD) propulsion. Phase 2 focused on the experimental validation of the thruster performance models and the identification, through testing, of any phenomena which may impact the attractiveness of this propulsion system for shipboard applications. The report discusses in detail the work performed in Phase 2 of the program. In Phase 2, a two Tesla test facility was designed, built, and operated. The facility test loop, its components, and their design are presented. The test matrix and its rationale are discussed. Representative experimental results of the test program are presented, and are compared to computer model predictions. In general, the results of the tests and their comparison with the predictions indicate that thephenomena affecting the performance of MHD seawater thrusters are well understood and can be accurately predicted with the developed thruster computer models.

  12. Particle Multiplicity in Jets and Sub-jets with Jet Axis from Color Current

    E-Print Network [OSTI]

    Wlofgang Ochs; Redamy Perez Ramos

    2008-07-07

    We study the particle multiplicity in a jet or sub-jet as derived from an energy-multiplicity 2-particle correlation. This definition avoids the notion of a globally fixed jet axis and allows for the study of smaller jet cone openings in a more stable way. The results are sensitive to the mean color current $_{A_0} $ in the jet from primary parton $A_0$ which takes into account intermediate partonic processes in the sub-jet production where $C_F_{A_0} jet axis definition are computed for multiplicities in sub-jets with different opening angles and energies by including contributions from the Modified LLA (MLLA) and Next-to-MLLA to the leading order QCD results.

  13. NASA/TP-2006-214203 Logistics Lessons Learned in NASA Space Flight

    E-Print Network [OSTI]

    de Weck, Olivier L.

    NASA/TP-2006-214203 Logistics Lessons Learned in NASA Space Flight William A. (Andy) Evans, United 2006 #12;NASA STI Program ... in Profile Since its founding, NASA has been dedicated to the advancement of aeronautics and space science. The NASA scientific and technical information (STI) program plays a key part

  14. NASA Research Areas of Interest Released by NASA HQ February 2014

    E-Print Network [OSTI]

    Maxwell, Bruce D.

    NASA Research Areas of Interest Released by NASA HQ February 2014 NASA EPSCoR research priorities), the Office of the Chief Technologist and NASA's ten Centers. Each Mission Directorate, the Office efforts. Information about current NASA research solicitations can be found on NSPIRES at http

  15. Instabilities of rotating jets

    E-Print Network [OSTI]

    Zahniser, Russell, 1982-

    2004-01-01

    When a jet of water is in free fall, it rapidly breaks up into drops, since a cylinder of water is unstable. This and other problems involving the form of a volume of water bound by surface tension have yielded a wealth ...

  16. Vortex diode jet

    DOE Patents [OSTI]

    Houck, Edward D. (Idaho Falls, ID)

    1994-01-01

    A fluid transfer system that combines a vortex diode with a jet ejector to transfer liquid from one tank to a second tank by a gas pressurization method having no moving mechanical parts in the fluid system. The vortex diode is a device that has a high resistance to flow in one direction and a low resistance to flow in the other.

  17. Hadron Correlation in Jets

    E-Print Network [OSTI]

    Rudolph C. Hwa

    2007-01-18

    We review some recent experimental and theoretical work on the correlation among hadrons produced at intermediate $p_T$ at RHIC. The topics include: forward and backward asymmetry with and without trigger at mid-rapidity, associated-particle distribution on the near side, the $\\Omega$ puzzle and its solution, associated particles on the away side, and two-jet recombination at LHC.

  18. IEEE TRANSACTIONS ON MICROWAVE THEORY AND TECHNIQUES, VOL. 46, NO. 2, FEBRUARY 1998 1 A 850 GHz Waveguide Receiver Employing a

    E-Print Network [OSTI]

    Technology, Jet Propulsion Laboratory, California Institute of Technology, and was sponsored by NASA, Office@tacos.caltech.edu. B. Bumble and H.G. LeDuc are with the Center for Space Micro- electronics Technology, Jet Propulsion by Ellison et al. [1] and employs two circular non-contacting tuning elements [2], [3], magnetic field

  19. Multi-angle Imaging SpectroRadiometer (MISR) National Aeronautics and

    E-Print Network [OSTI]

    Space Flight Center Jet Propulsion Laboratory #12;About This Image The true-color image at left and natural activities. Exhaust from internal combustion engines makes carbon monoxide gas, nitrogen oxide gas and provided by NASA's Jet Propulsion Laboratory, Pasadena, California, measures the variation of surface

  20. Propulsion System Materials Program semiannual progress report for April 1995 through September 1995

    SciTech Connect (OSTI)

    NONE

    1996-04-01

    Significant accomplishments in fabricating ceramic components for the DOE, NASA, and DOD advanced heat engine programs have provided evidence that the operation of ceramic parts in high-temperature engine environments is feasible. These programs have also demonstrated that additional research is needed in materials and processing development, design methodology, and data base and life prediction before industry will have a sufficient technology base from which to produce reliable cost-effective ceramic engine components commercially. An assessment of needs was completed, and a 5-year program plan was developed with extensive input from private industry. During the course of the Propulsion System Materials Program, remarkable progress has been made in the development of reliable structural ceramics. However, further work is needed to reduce the cost of ceramics to facilitate their commercial introduction, especially in the highly cost-sensitive automotive market. To this end, the direction of the Propulsion System Materials Program is now shifting toward reducing the cost of ceramics to facilitate commercial introduction of ceramic components for near-term engine applications. In response to extensive input from industry, the plan is to extend the engine types which were previously supported to include near-term (5--10 years) applications in conventional automobile and diesel truck engines. To facilitate the rapid transfer of this technology to US industry, the major portion of the work is being done in the ceramic industry, with technological support from government laboratories, other industrial laboratories, and universities. A systematic approach to reducing the cost of components is envisioned. The work elements are as follows: economic cost modeling, ceramic machining, powder synthesis, alternative forming and densification processes, yield improvement, system design studies, standards development, low-expansion ceramics, and testing and data base development.

  1. Interacting Jets from Binary Protostars

    E-Print Network [OSTI]

    G. C. Murphy; T. Lery; S. O'Sullivan; D. Spicer; F. Bacciotti; A. Rosen

    2007-11-20

    We investigate potential models that could explain why multiple proto-stellar systems predominantly show single jets. During their formation, stars most frequently produce energetic outflows and jets. However, binary jets have only been observed in a very small number of systems. We model numerically 3D binary jets for various outflow parameters. We also model the propagation of jets from a specific source, namely L1551 IRS 5, known to have two jets, using recent observations as constraints for simulations with a new MHD code. We examine their morphology and dynamics, and produce synthetic emission maps. We find that the two jets interfere up to the stage where one of them is almost destroyed or engulfed into the second one. We are able to reproduce some of the observational features of L1551 such as the bending of the secondary jet. While the effects of orbital motion are negligible over the jets dynamical timeline, their interaction has significant impact on their morphology. If the jets are not strictly parallel, as in most observed cases, we show that the magnetic field can help the collimation and refocusing of both of the two jets.

  2. Flow cytometer jet monitor system

    DOE Patents [OSTI]

    Van den Engh, Ger (Seattle, WA)

    1997-01-01

    A direct jet monitor illuminates the jet of a flow cytometer in a monitor wavelength band which is substantially separate from the substance wavelength band. When a laser is used to cause fluorescence of the substance, it may be appropriate to use an infrared source to illuminate the jet and thus optically monitor the conditions within the jet through a CCD camera or the like. This optical monitoring may be provided to some type of controller or feedback system which automatically changes either the horizontal location of the jet, the point at which droplet separation occurs, or some other condition within the jet in order to maintain optimum conditions. The direct jet monitor may be operated simultaneously with the substance property sensing and analysis system so that continuous monitoring may be achieved without interfering with the substance data gathering and may be configured so as to allow the front of the analysis or free fall area to be unobstructed during processing.

  3. Reliability comparison of various nuclear propulsion configurations for Mars mission

    SciTech Connect (OSTI)

    Segna, D.R. [USDOE Richland Operations Office, WA (United States); Dagle, J.E. [Pacific Northwest Lab., Richland, WA (United States); Lyon, W.F. III [Westinghouse Hanford Co., Richland, WA (United States)

    1992-01-01

    Currently, trade-offs are being made among the various propulsion systems being considered for the Space Exploration Initiative (SEI) missions. It is necessary to investigate the reliability aspects as well as the efficiency, mass savings, and experience characteristics of the various configurations. Reliability is a very important factor for the SEI missions because of the long duration and because problems will be fixed onboard. The propulsion options that were reviewed consist of nuclear thermal propulsion (NTP), nuclear electric propulsion (NEP) and various configurations of each system. There were four configurations developed for comparison with the NTP as baselined in the Synthesis (1991): (1) NEP, (2) hybrid NEP/NTP, (3) hybrid with power beaming, and (4) NTP upper stage on the heavy lift launch vehicle (HLLV). The comparisons were based more or less on a qualitative review of complexity, stress levels and operations for each of the four configurations. Each configuration included a pressurized NEP and an NTP ascent stage propulsion system for the Mars mission.

  4. A Propellantless Propulsion Experiment Design and Testing Plan

    SciTech Connect (OSTI)

    Goodwin, David P. [United States Department of Energy, Office of High Energy Physics, SC-20/Germantown Building, 1000 Independence Ave SW, Washington, D.C. 20585-1290 (United States)

    2004-02-04

    A propellantless propulsion experiment design and testing plan are described. The concept was initially presented during the Space Technology and Applications International Forum of 2001 and the experiment was initially presented during the Joint Propulsion Conference of 2001. New information is provided on how the experiment relates to the Human Exploration of Development of Space, the results of peer reviews, a cost estimate performed by a major U.S. aerospace company, and an alternative magnet design to reduce the cost of the experiment and potentially improve the reliability of the system. Recent improvements in high power solid state switches and superconducting magnets may have made propellantless propulsion possible. Propulsion may occur during the non-steady state ramp-up of a very rapidly pulsed, high power magnet. Propulsion would not occur after the first 100 nanoseconds of each pulse, since the magnetic field will have reached steady state. The United States Department of Energy Office of High Energy Physics provided some of the funding for the developed a no maintenance superconducting magnet that can carry 2,000 amperes per square millimeter and a switch which can provide 100 nanosecond ramp-ups at a rate of 0.4 megahertz, and at 9,000 volts and 30 amperes.

  5. BIPOLAR JETS LAUNCHED FROM ACCRETION DISKS. II. THE FORMATION OF ASYMMETRIC JETS AND COUNTER JETS

    SciTech Connect (OSTI)

    Fendt, Christian; Sheikhnezami, Somayeh E-mail: nezami@mpia.de

    2013-09-01

    We investigate the jet launching from accretion disks, in particular the formation of intrinsically asymmetric jet/counter jet systems. We perform axisymmetric MHD simulations of the disk-jet structure on a bipolar computational domain covering both hemispheres. We apply various models such as asymmetric disks with (initially) different scale heights in each hemisphere, symmetric disks into which a local disturbance is injected, and jets launched into an asymmetric disk corona. We consider both a standard global magnetic diffusivity distribution and a novel local diffusivity model. Typical disk evolution first shows substantial disk warping and then results in asymmetric outflows with a 10%-30% mass flux difference. We find that the magnetic diffusivity profile is essential for establishing a long-term outflow asymmetry. We conclude that bipolar asymmetry in protostellar and extragalactic jets can indeed be generated intrinsically and maintained over a long time by disk asymmetries and the standard jet launching mechanism.

  6. Self-propulsion of V-shape micro-robot

    E-Print Network [OSTI]

    Vladimir A. Vladimirov

    2012-09-13

    In this paper we study the self-propulsion of a symmetric V-shape micro-robot (or V-robot) which consists of three spheres connected by two arms with an angle between them; the arms' lengths and the angle are changing periodically. Using an asymptotic procedure containing two-timing method and a distinguished limit, we obtain analytic expressions for the self-propulsion velocity and Lighthill's efficiency. The calculations show that a version of V-robot, aligned perpendicularly to the direction of self-swimming, is both the fastest one and the most efficient one. We have also shown that such $V$-robot is faster and more efficient than a linear three-sphere micro-robot. At the same time the maximal self-propulsion velocity of V-robots is significantly smaller than that of comparable microorganisms.

  7. A survey of processes for producing hydrogen fuel from different sources for automotive-propulsion fuel cells

    SciTech Connect (OSTI)

    Brown, L.F.

    1996-03-01

    Seven common fuels are compared for their utility as hydrogen sources for proton-exchange-membrane fuel cells used in automotive propulsion. Methanol, natural gas, gasoline, diesel fuel, aviation jet fuel, ethanol, and hydrogen are the fuels considered. Except for the steam reforming of methanol and using pure hydrogen, all processes for generating hydrogen from these fuels require temperatures over 1000 K at some point. With the same two exceptions, all processes require water-gas shift reactors of significant size. All processes require low-sulfur or zero-sulfur fuels, and this may add cost to some of them. Fuels produced by steam reforming contain {approximately}70-80% hydrogen, those by partial oxidation {approximately}35-45%. The lower percentages may adversely affect cell performance. Theoretical input energies do not differ markedly among the various processes for generating hydrogen from organic-chemical fuels. Pure hydrogen has severe distribution and storage problems. As a result, the steam reforming of methanol is the leading candidate process for on-board generation of hydrogen for automotive propulsion. If methanol unavailability or a high price demands an alternative process, steam reforming appears preferable to partial oxidation for this purpose.

  8. Advanced ignition and propulsion technology program

    SciTech Connect (OSTI)

    Oldenborg, R.; Early, J.; Lester, C.

    1998-11-01

    This is the final report of a three-year, Laboratory Directed Research and Development (LDRD) project at the Los Alamos National Laboratory (LANL). Reliable engine re-ignition plays a crucial role in enabling commercial and military aircraft to fly safely at high altitudes. This project addressed research elements critical to the optimization of laser-based igniter. The effort initially involved a collaborative research and development agreement with B.F. Goodrich Aerospace and Laser Fare, Inc. The work involved integrated experiments with theoretical modeling to provide a basic understanding of the chemistry and physics controlling the laser-induced ignition of fuel aerosols produced by turbojet engine injectors. In addition, the authors defined advanced laser igniter configurations that minimize laser packaging size, weight, complexity and power consumption. These innovative ignition concepts were shown to reliably ignite jet fuel aerosols over a broad range of fuel/air mixture and a t fuel temperatures as low as -40 deg F. The demonstrated fuel ignition performance was highly superior to that obtained by the state-of-the-art, laser-spark ignition method utilizing comparable laser energy. The authors also developed a laser-based method that effectively removes optically opaque deposits of fuel hydrocarbon combustion residues from laser window surfaces. Seven patents have been either issued or are pending that resulted from the technology developments within this project.

  9. Effluent treatment options for nuclear thermal propulsion system ground tests

    SciTech Connect (OSTI)

    Shipers, L.R.; Brockmann, J.E.

    1992-10-16

    A variety of approaches for handling effluent from nuclear thermal propulsion system ground tests in an environmentally acceptable manner are discussed. The functional requirements of effluent treatment are defined and concept options are presented within the framework of these requirements. System concepts differ primarily in the choice of fission-product retention and waste handling concepts. The concept options considered range from closed cycle (venting the exhaust to a closed volume or recirculating the hydrogen in a closed loop) to open cycle (real time processing and venting of the effluent). This paper reviews the strengths and weaknesses of different methods to handle effluent from nuclear thermal propulsion system ground tests.

  10. Handling effluent from nuclear thermal propulsion system ground tests

    SciTech Connect (OSTI)

    Shipers, L.R.; Allen, G.C.

    1992-09-09

    A variety of approaches for handling effluent from nuclear thermal propulsion system ground tests in an environmentally acceptable manner are discussed. The functional requirements of effluent treatment are defined and concept options are presented within the framework of these requirements. System concepts differ primarily in the choice of fission-product retention and waste handling concepts. The concept options considered range from closed cycle (venting the exhaust to a closed volume or recirculating the hydrogen in a closed loop) to open cycle (real time processing and venting of the effluent). This paper reviews the different methods to handle effluent from nuclear thermal propulsion system ground tests.

  11. Heavy Vehicle Propulsion Materials Program: Progress and Highlights

    SciTech Connect (OSTI)

    D. Ray Johnson; Sidney Diamond

    2000-06-19

    The Heavy Vehicle Propulsion Materials Program was begun in 1997 to support the enabling materials needs of the DOE Office of Heavy Vehicle Technologies (OHVT). The technical agenda for the program grew out of the technology roadmap for the OHVT and includes efforts in materials for: fuel systems, exhaust aftertreatment, valve train, air handling, structural components, electrochemical propulsion, natural gas storage, and thermal management. A five-year program plan was written in early 2000, following a stakeholders workshop. The technical issues and planned and ongoing projects are discussed. Brief summaries of several technical highlights are given.

  12. High performance path following for marine vehicles using azimuthing podded propulsion

    E-Print Network [OSTI]

    Greytak, Matthew B. (Matthew Bardeen)

    2006-01-01

    Podded propulsion systems offer greater maneuvering possibilities for marine vehicles than conventional shaft and rudder systems. As the propulsion unit rotates about its vertical axis to a specified azimuth angle, the ...

  13. Naval ship propulsion and electric power systems selection for optimal fuel consumption

    E-Print Network [OSTI]

    Sarris, Emmanouil

    2011-01-01

    Although propulsion and electric power systems selection is an important part of naval ship design, respective decisions often have to be made without detailed ship knowledge (resistance, propulsors, etc.). Propulsion and ...

  14. Summer Undergraduate Research Opportunities in the Electric Propulsion and Plasmadynamics Laboratory (EPPDyL)*

    E-Print Network [OSTI]

    Summer Undergraduate Research Opportunities in the Electric Propulsion and Plasmadynamics with electronic instrumentation is desirable. MAGNETIC NOZZLES ­ Aid in the construction of a magnetic nozzle experiment for plasma propulsion applications. Student will work with a large vacuum chamber, thrust stand

  15. Bipolar Electrochemical Mechanism for the Propulsion of Catalytic Nanomotors in Hydrogen Peroxide Solutions

    E-Print Network [OSTI]

    Bipolar Electrochemical Mechanism for the Propulsion of Catalytic Nanomotors in Hydrogen Peroxide the bipolar electrochemical propulsion mechanism for bimetallic nanorods. Introduction Catalyic molecular nonbiological schemes for making micro/nanoscale ma- chines involve externally applied magnetic2 or electrical

  16. Ram jet engine

    SciTech Connect (OSTI)

    Crispin, B.; Pohl, W.D.; Thomaier, D.; Voss, N.

    1983-11-29

    In a ram jet engine, a tubular combustion chamber is divided into a flame chamber followed by a mixing chamber. The ram air is supplied through intake diffusers located on the exterior of the combustion chamber. The intake diffusers supply combustion air directly into the flame chamber and secondary air is conveyed along the exterior of the combustion chambers and then supplied directly into the mixing chamber.

  17. Beam/Jet Trajectories April 1, 2009

    E-Print Network [OSTI]

    McDonald, Kirk

    Beam/Jet Trajectories April 1, 2009 #12;Hg Jet Target Geometry Solenoid Axis Hg Jet Proton Beam BEAM CROSS rJET Previous results: Radius 5mm, beam =67mrad crossing = 33mrad #12;Optimized Target Energy, GeV Optimized Target Radius #12;Beam Angle and Jet/Beam Crossing Angle 0 20 40 60 80 100 120 140

  18. JET Forward Programme & Opportunities for Collaboration

    E-Print Network [OSTI]

    JET Forward Programme & Opportunities for Collaboration Lorne Horton JET Exploitation Manager Contract for the Opera.on of the JET Facili.es Co-Funded by Euratom #12;L.D. Horton 2 FESAC Strategic Planning Panel 8 July 2014 - What makes JET unique! - Plans for JET exploitation

  19. Rotating Detonation Wave Propulsion: Experimental Challenges, Modeling, and Engine Concepts (Invited)

    E-Print Network [OSTI]

    Texas at Arlington, University of

    Rotating Detonation Wave Propulsion: Experimental Challenges, Modeling, and Engine Concepts energy release from detonations for propulsion or as a power source.1a This interest actually predates. The possibility of practical propulsion and power generation systems was even met with skep- ticism.12

  20. JOURNAL OF PROPULSION AND POWER Vol. 22, No. 6, NovemberDecember 2006

    E-Print Network [OSTI]

    Dame, where he considers problems in reactive fluid mechanics, high-speed flows, propulsion, energeticJOURNAL OF PROPULSION AND POWER Vol. 22, No. 6, November­December 2006 Review of Multiscale to detonation-driven propulsion systems are discussed. It is suggested that a failure of most existing

  1. High-speed propulsion of flexible nanowire motors: Theory and experiments On Shun Pak,a

    E-Print Network [OSTI]

    Lauga, Eric

    hydrodynamic interaction with the fluid medium. The critical role of flexibility in this mode of propulsion and their promise for biomedical applications. 1 Introduction Micro/nano-scale propulsion in fluids is challenging to their propulsion mechanisms, externally pow- ered propellers can be further categorized into three groups (see

  2. Magnetic Propulsion of Intense Lithium Streams in a Tokamak Magnetic Field

    E-Print Network [OSTI]

    Zakharov, Leonid E.

    Magnetic Propulsion of Intense Lithium Streams in a Tokamak Magnetic Field Leonid E. Zakharov the theory of magnetic propulsion of liquid lithium streams and their stability in tokamaks takes into account the propulsion e#11;ect, viscosity and the drag force due to magnetic pumping

  3. Velocity Fluctuations in Helical Propulsion: How Small Can a Propeller Be

    E-Print Network [OSTI]

    Rangarajan, Govindan

    applied rotating magnetic field. The method of helical propulsion becomes especially important at smallerVelocity Fluctuations in Helical Propulsion: How Small Can a Propeller Be Arijit Ghosh,,# Debadrita propulsion is at the heart of locomotion strategies utilized by various natural and artificial swimmers. We

  4. Divergence of a Propulsive Plasma Flow Expanding through a Magnetic Nozzle

    E-Print Network [OSTI]

    Choueiri, Edgar

    Divergence of a Propulsive Plasma Flow Expanding through a Magnetic Nozzle IEPC-2009-260 Presented frequency waves have renewed interest in magnetic nozzles for plasma propulsion applications in space.1 at the 31st International Electric Propulsion Conference, University of Michigan · Ann Arbor, Michigan · USA

  5. Ground test facilities for evaluating nuclear thermal propulsion engines and fuel elements

    SciTech Connect (OSTI)

    Allen, G.C.; Beck, D.F.; Harmon, C.D.; Shipers, L.R.

    1992-08-01

    Interagency panels evaluating nuclear thermal propulsion development options have consistently recognized the need for constructing a major new ground test facility to support fuel element and engine testing. This paper summarizes the requirements, configuration, and design issues of a proposed ground test complex for evaluating nuclear thermal propulsion engines and fuel elements being developed for the Space Nuclear Thermal Propulsion (SNTP) program. 2 refs.

  6. Selected Items in Jet Algorithms

    E-Print Network [OSTI]

    Giuseppe Bozzi

    2008-08-06

    I provide a very brief overview of recent developments in jet algorithms, mostly focusing on the issue of infrared-safety.

  7. Photon + jets at D0

    E-Print Network [OSTI]

    Lars Sonnenschein

    2009-06-15

    Photon plus jet production has been studied by the D0 experiment in Run II of the Fermilab Tevatron Collider at a centre of mass energy of sqrt{s}=1.96 TeV. Measurements of the inclusive photon, inclusive photon plus jet, photon plus heavy flavour jet cross sections and double parton interactions in photon plus three jet events are presented. They are based on integrated luminosities between 0.4 fb$^-1 and 1.0 fb^-1. The results are compared to perturbative QCD calculations in various approximations.

  8. August 2002 NASA/TM--2002211612

    E-Print Network [OSTI]

    Richardson, John

    August 2002 NASA/TM--2002­211612 Pickup Ions at Dione and Enceladus E. Sittler, R.E. Johnson, S. Jurac, J. Richardson, M. McGrath, F. Crary, D. Young, and J.E. Nordholt #12;The NASA STI Program Office ... in Profile Since its founding, NASA has been dedicated to the advancement of aeronautics and space science

  9. NASA VLSI 2007 Mohanty, Vadlamudi and

    E-Print Network [OSTI]

    Mohanty, Saraju P.

    NASA VLSI 2007 Mohanty, Vadlamudi and Kougianos 1 A Universal Voltage Level Converter for Multi University of North Texas dhruva@unt.edu #12;NASA VLSI 2007 Mohanty, Vadlamudi and Kougianos 2 Agenda Custom layout design at 90nm technology Conclusion and future works #12;NASA VLSI 2007 Mohanty, Vadlamudi

  10. www.sunearthday.nasa.gov Public Outreach

    E-Print Network [OSTI]

    Lawrence, Rick L.

    www.sunearthday.nasa.gov Public Outreach: Make andTake Activities WhatYou'll Need Solar Clock About Administration www. nasa.gov Related Websites "From Stargazers to Starships" ­ More Information on Sundials: #12 ¡Cuttobottom ofpage Discard Discard #12;Instructions (from http://www-spof.gsfc.nasa.gov/stargaze/ Sundial

  11. NASA/TM2013218033 Rewriting Modulo SMT

    E-Print Network [OSTI]

    Muñoz, César A.

    NASA/TM­2013­218033 Rewriting Modulo SMT Camilo Rocha Escuela Colombiana de Ingenier´ia, Bogot´a, Colombia Jos´e Meseguer University of Illinois at Urbana-Champaign, Urbana, IL, USA C´esar A. Mu~noz NASA Langley Research Center, Hampton, VA, USA August 2013 #12;NASA STI Program . . . in Profile Since its

  12. NASA Launches Next-Generation Communications Satellite

    E-Print Network [OSTI]

    Christian, Eric

    NASA Launches Next-Generation Communications Satellite Pg 3 Triumph Over Tragedy: Columbia's Last Mission Pg 6 Goddard Day of Remembrance Pg 9 National Aeronautics and Space Administration www.nasa.gov Volume 9 Issue 1 February 2013 #12;T he first of NASA's three next-generation Tracking and Data Relay

  13. Magnetic propulsion of liquid Li in tokamaks 1

    E-Print Network [OSTI]

    Zakharov, Leonid E.

    Magnetic propulsion of liquid Li in tokamaks 1 Leonid E. Zakharov, Princeton University, Princeton of liquid lithium, with the tokamak magnetic field is discussed as a mechanism a) for creating fast moving (plasma facing) Li streams along the inner wall of tokamak and b) for mixing the liquid in a closed volume

  14. Mars mission performance enhancement with hybrid nuclear propulsion

    SciTech Connect (OSTI)

    Dagle, J.E.; Noffsinger, K.E. [Pacific Northwest Lab., Richland, WA (United States); Segna, D.R. [USDOE Richland Operations Office, WA (United States)

    1992-01-01

    Nuclear electric propulsion (NEP), compared with chemical and nuclear thermal propulsion (NTP), can effectively deliver the same mass to Mars using much less propellant, consequently requiring less mass delivered to Earth orbit. The lower thrust of NEP requires a spiral trajectory near planetary bodies, which significantly increases the travel time. Although the total travel time is long, the portion of the flight time spent during interplanetary transfer is shorter, because the vehicle is thrusting for much longer periods of time. This has led to the supposition that NEP, although very attractive for cargo missions, is not suitable for piloted missions to Mars. However, with the application of a hybrid application of a hybrid approach to propulsion, the benefits of NEP can be utilized while drastically reducing the overall travel time required. Development of a dual-mode system, which utilizes high-thrust NTP to propel the spacecraft from the planetary gravitational influence and low-thrust NEP to accelerate in interplanetary space, eliminates the spiral trajectory and results in a much faster transit time than could be obtained by either NEP or NTP alone. This results in a mission profile with a lower initial mass in low Earth orbit. In addition, the propulsion system would have the capability to provide electrical power for mission applications.

  15. Advanced hybrid nuclear propulsion Mars mission performance enhancement

    SciTech Connect (OSTI)

    Dagle, J.E.; Noffsinger, K.E.; Segna, D.R.

    1992-02-01

    Nuclear electric propulsion (NEP), compared with chemical and nuclear thermal propulsion (NTP), can effectively deliver the same mass to Mars using much less propellant, consequently requiring less mass delivered to Earth orbit. The lower thrust of NEP requires a spiral trajectory near planetary bodies, which significantly increases the travel time. Although the total travel time is long, the portion of the flight time spent during interplanetary transfer is shorter, because the vehicle is thrusting for much longer periods of time. This has led to the supposition that NEP, although very attractive for cargo missions, is not suitable for piloted missions to Mars. However, with the application of a hybrid approach to propulsion, the benefits of NEP can be utilized while drastically reducing the overall travel time required. Development of a dual-mode system, which utilizes high-thrust NTP to propel the spacecraft from the planetary gravitational influence and low-thrust NEP to accelerate in interplanetary space, eliminates the spiral trajectory and results in a much faster transit time than could be obtained by either NEP or NTP alone. This results in a mission profile with a lower initial mass in low Earth orbit. In addition, the propulsion system would have the capability to provide electrical power for mission applications.

  16. Energy cost and muscular activity required for propulsion during walking

    E-Print Network [OSTI]

    Kram, Rodger

    of 53% of normal walking, 2) the mean EMG of the medial gas- trocnemius (MG) during the propulsive phase are the individual roles of the ankle extensor muscles in producing forward propul- sion? Energetics. Past research, we applied constant levels of external horizontal force at the waist. Our rationale for this part

  17. Department of Aeronautics and Astronautics Field Exam on Space Propulsion

    E-Print Network [OSTI]

    de Weck, Olivier L.

    and to the wall heat flux that may require active cooling. (c) Changes to the engine mass/power ratio (the !engine with power level P. · The fraction of the lost power (1-)P that is deposited on the wall is also nearly a spacecraft (payload/structure + propulsion/power system + propellant) hovering during a time ! at a constant

  18. Propulsive Forces on the Flagellum during Locomotion of Chlamydomonas reinhardtii

    E-Print Network [OSTI]

    Pless, Robert

    and the flagellum were analyzed in the context of low-Reynolds-number fluid mechanics. Wild-type uniflagellate cellsPropulsive Forces on the Flagellum during Locomotion of Chlamydomonas reinhardtii P. V. Bayly, * B. L. Lewis, E. C. Ranz, R. J. Okamoto, R. B. Pless,§ and S. K. Dutcher Department of Mechanical

  19. Numerical Study of Flexible Flapping Wing Propulsion and Mingjun Wei

    E-Print Network [OSTI]

    Wei, Mingjun

    Numerical Study of Flexible Flapping Wing Propulsion Tao Yang and Mingjun Wei New Mexico State highly flexible flapping wings interacting with fluid flows. Here, the fluid motion, solid motion necessary flapping mechanism, control cells are implemented in solid area (i.e., the wing) as "skeleton

  20. International Electric Propulsion Conference IEPC-2007-153

    E-Print Network [OSTI]

    King, Lyon B.

    30th International Electric Propulsion Conference IEPC-2007-153 1 Confinement time in an electron and magnetic fields of a Hall-effect thruster with the goal of understanding the mechanism(s) responsible for anomalous cross-field mobility. A low-density electron plasma is confined using vacuum electric and magnetic

  1. Emissions and Performance Tradeoffs for Advanced Marine Diesel Propulsion

    E-Print Network [OSTI]

    Stefanopoulou, Anna

    geometry turbocharger (v). The variable geometry turbocharger allows the improvement of the steady of turbocharged diesel en- gines render them common practice for the vast ma- jority of ocean freighters and o shore vehicles. In ma- rine propulsion, the turbocharger, the engine, and the propeller operation

  2. AC 2007-504: NASA OPPORTUNITIES FOR FACULTY AT MINORITY INSTITUTIONS: REFLECTIONS OF NASA ADMINISTRATOR FELLOWS

    E-Print Network [OSTI]

    Everett, Louis J.

    AC 2007-504: NASA OPPORTUNITIES FOR FACULTY AT MINORITY INSTITUTIONS: REFLECTIONS OF NASA. leverett@utep.edu http://research.utep.edu/pacelab Paul Racette, NASA As an adventurous adolescent, Paul sensing and instrument calibration. For these efforts and accomplishments Paul received the NASA Medal

  3. NASA and Afterschool Programs: Connecting to the Future What NASA Has to Offer

    E-Print Network [OSTI]

    Hammer, David

    NASA and Afterschool Programs: Connecting to the Future What NASA Has to Offer David Hammer and Janet Coffey University of Maryland, College Park When people think of what NASA has to offer science education, one natural starting place is knowledge: NASA scientists have a lot of it, from basic concepts

  4. Buoyant jet behavior in confined regions

    E-Print Network [OSTI]

    Fry, David J.

    1981-01-01

    Previous confined jet studies have emphasized the behavior of non-buoyant jets inside ducts or near plane boundaries (Coanda effect). Buoyancy, however, is a major factor in the confined jet behavior experienced in many ...

  5. Jet shapes with the broadening axis

    E-Print Network [OSTI]

    Larkoski, Andrew James

    Broadening is a classic jet observable that probes the transverse momentum structure of jets. Traditionally, broadening has been measured with respect to the thrust axis, which is aligned along the (hemisphere) jet momentum ...

  6. Miniconference on astrophysical jets P. M. Bellan

    E-Print Network [OSTI]

    Bellan, Paul M.

    Miniconference on astrophysical jets P. M. Bellan Applied Physics, California Institute 9 May 2005 This miniconference brought together observers of astrophysical jets, analytic and numerical modelers of both astrophysical jets and spheromaks, and laboratory experimentalists. The purpose

  7. JETS IN e+e- ANNIHILATION

    E-Print Network [OSTI]

    Cooper, Susan Catherine.

    2010-01-01

    io U s, Data Monte Carlo, ~zz Jet Model Monte Carlo, - Phaseener-jy for data (points), jet model (solid curve) and pnaotAXIS The quarKs and hence the jet axis should have the same

  8. On impinging near-field granular jets

    E-Print Network [OSTI]

    Arbelaez, D.; Zohdi, T. I.; Dornfeld, D. A.

    2009-01-01

    evolution models in abrasive jet micromachining. Wear 2008;SIMULATION OF GRANULAR JETS 26. Cheng X, Varas G, Citron D,behavior in a granular jet: emergence of a liquid with zero

  9. Searching for Jets in Heavy Ion Collisions

    E-Print Network [OSTI]

    Salur, Sevil

    2008-01-01

    measurements with full jet reconstruction in heavy ionDirect measurement of jets in s N N = 200 GeV Heavy Ion5–12, 2008 Searching for Jets in Heavy Ion Collisions Sevil

  10. Nuclear electric propulsion /NEP/ spacecraft for the outer planet orbiter mission

    SciTech Connect (OSTI)

    Garrison, P.W.; Nock, K.T.

    1982-01-01

    The design, operating features, and a possible Neptune orbit for the spacecraft powered by the SP-100 nuclear electric propulsion (NEP) system under study by NASA and the DOE are described. The system features a reactor and a payload situated on opposite ends of a 0.5 m diam, 11 m long astromast. Mercury-ion thrusters are located beneath the reactor for side thrusting, and no contamination of the payload or obstruction of the viewing angles for scientific objectives occurs with the system, which would not degrade in performance even under high insolation during near-sun maneuvers. Results of a theoretical study of earth escapes are presented to show that an NEP powered spiral trajectory out of a 700 km Shuttle orbit and using a Triton gravity assist would be superior to departing from a 300 km orbit with a Centaur boost. The mission profile includes a 1249 kg Galileo payload. The SP-100 has a 1.4 MWth reactor with UO2 fuel tiles and weighs 19,904 kg.

  11. Study of a heat rejection system for the Nuclear Electric Propulsion (NEP) spacecraft. Final report

    SciTech Connect (OSTI)

    Ernest, D.M.

    1982-11-01

    Two different heat pipe radiator elements, one intended for use with the power conversion subsystem of the NASA funded nuclear electric propulsion (NEP) spacecraft, and one intended for use with the DOE funded space power advanced reactor (SPAR) system were tested and evaluated. The NEP stainless steel/sodium heat pipe was 4.42 meters long and had a 1 cm diameter. Thermal performance testing at 920 K showed a non-limited power level of 3560 watts, well in excess of the design power of 2600 watts. This test verified the applicability of screen arteries for use in long radiator heat pipes. The SPAR titanium/potassium heat pipe was 5.5 meters long and had a semicircular crossection with a 4 cm diameter. Thermal performance testing at 775 K showed a maximum power level of 1.86 kW, somewhat short of the desired 2.6 kW beginning of life design requirement. The reduced performance was shown to be the result of the inability of the evaporator wall wick (shot blasted evaporator wall) to handle the required liquid flow.

  12. Brayton power conversion system parametric design modelling for nuclear electric propulsion. Final report

    SciTech Connect (OSTI)

    Ashe, T.L.; Otting, W.D.

    1993-11-01

    The parametrically based closed Brayton cycle (CBC) computer design model was developed for inclusion into the NASA LeRC overall Nuclear Electric Propulsion (NEP) end-to-end systems model. The code is intended to provide greater depth to the NEP system modeling which is required to more accurately predict the impact of specific technology on system performance. The CBC model is parametrically based to allow for conducting detailed optimization studies and to provide for easy integration into an overall optimizer driver routine. The power conversion model includes the modeling of the turbines, alternators, compressors, ducting, and heat exchangers (hot-side heat exchanger and recuperator). The code predicts performance to significant detail. The system characteristics determined include estimates of mass, efficiency, and the characteristic dimensions of the major power conversion system components. These characteristics are parametrically modeled as a function of input parameters such as the aerodynamic configuration (axial or radial), turbine inlet temperature, cycle temperature ratio, power level, lifetime, materials, and redundancy.

  13. Heat pipe radiation cooling (HPRC) for high-speed aircraft propulsion. Phase 2 (feasibility) final report

    SciTech Connect (OSTI)

    Martin, R.A.; Merrigan, M.A.; Elder, M.G.; Sena, J.T.; Keddy, E.S.; Silverstein, C.C.

    1994-03-25

    The National Aeronautics and Space Administration (NASA), Los Alamos National Laboratory (Los Alamos), and CCS Associates are conducting the Heat Pipe Radiation Cooling (HPRC) for High-Speed Aircraft Propulsion program to determine the advantages and demonstrate the feasibility of using high-temperature heat pipes to cool hypersonic engine components. This innovative approach involves using heat pipes to transport heat away from the combustor, nozzle, or inlet regions, and to reject it to the environment by thermal radiation from adjacent external surfaces. HPRC is viewed as an alternative (or complementary) cooling technique to the use of pumped cryogenic or endothermic fuels to provide regenerative fuel or air cooling of the hot surfaces. The HPRC program has been conducted through two phases, an applications phase and a feasibility phase. The applications program (Phase 1) included concept and assessment analyses using hypersonic engine data obtained from US engine company contacts. The applications phase culminated with planning for experimental verification of the HPRC concept to be pursued in a feasibility program. The feasibility program (Phase 2), recently completed and summarized in this report, involved both analytical and experimental studies.

  14. X-Ray Propulsor: Physical Principle for an Electromagnetic Propellantless Propulsion System

    E-Print Network [OSTI]

    Martins, Alexandre A

    2012-01-01

    In this work we are going to develop a physical model that explains how propulsion may be developed in a vacuum by the collision of electrons with an anode. Instead of using principles related to the conservation of mechanical momentum to achieve propulsion, like all the current propulsion systems do, the present system achieves propulsion by using principles related to the conservation of electromagnetic momentum. The complete physical model will be provided and comparison with preliminary experimental results will be performed. These results are important since they show that it is possible to achieve a radical different propulsion system with many advantages.

  15. Low-Cost, Lightweight Solar Concentrator

    Office of Energy Efficiency and Renewable Energy (EERE) Indexed Site

    from Jet Propulsion Laboratory Project Leader: Dr. Gani Ganapathi gani.b.ganapathi@jpl.nasa.gov Printed with a renewable-source ink on paper containing at least 50% wastepaper,...

  16. Rover Technology Development and Infusion for the 2009 Mars Science Laboratory Mission

    E-Print Network [OSTI]

    Volpe, Richard

    Rover Technology Development and Infusion for the 2009 Mars Science Laboratory Mission Richard Volpe and Stephen Peters Jet Propulsion Laboratory California Institute of Technology Pasadena, CA 91103 email: {firstname.lastname}@jpl.nasa.gov Keywords: Spacecraft Autonomy, Planetary Robotics, Technology

  17. Cassini's Earthly Benefits BENEFITS OF INTERNATIONAL COOPERATION

    E-Print Network [OSTI]

    Waliser, Duane E.

    's goal is to perform close-up studies of Saturn, its rings, moons and magnetic environment. Satun the Cassini/Huygens spacecraft. In the U.S., the mission is managed by NASA's Jet Propulsion Laboratory

  18. Top Jets at the LHC

    E-Print Network [OSTI]

    Almeida, L.G.

    2009-01-01

    Top Jets at the LHC Leandro G. Almeida, Seung J. Lee, GiladSB-08-37; WIS/17/08-SEPT-DPP Top Jets at the LHC Leandro G.p T hadronically-decaying top quarks at the Large Hadron

  19. OPENING ANGLES OF COLLAPSAR JETS

    SciTech Connect (OSTI)

    Mizuta, Akira; Ioka, Kunihito

    2013-11-10

    We investigate the jet propagation and breakout from the stellar progenitor for gamma-ray burst (GRB) collapsars by performing two-dimensional relativistic hydrodynamic simulations and analytical modeling. We find that the jet opening angle is given by ?{sub j} ? 1/5?{sub 0} and infer the initial Lorentz factor of the jet at the central engine, ?{sub 0}, is a few for existing observations of ?{sub j}. The jet keeps the Lorentz factor low inside the star by converging cylindrically via collimation shocks under the cocoon pressure and accelerates at jet breakout before the free expansion to a hollow-cone structure. In this new picture, the GRB duration is determined by the sound crossing time of the cocoon, after which the opening angle widens, reducing the apparent luminosity. Some bursts violating the maximum opening angle ?{sub j,{sub max}} ? 1/5 ? 12° imply the existence of a baryon-rich sheath or a long-acting jet. We can explain the slopes in both Amati and Yonetoku spectral relations using an off-centered photosphere model, if we make only one assumption that the total jet luminosity is proportional to the initial Lorentz factor of the jet. We also numerically calibrate the pre-breakout model (Bromberg et al.) for later use.

  20. NASA

    National Nuclear Security Administration (NNSA)

    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: Alternative Fuels Data Center Homesum_a_epg0_fpd_mmcf_m.xls" ,"Available from WebQuantity of NaturalDukeWakefield Municipal GasAdministration Medal01 Sandia4) AugustA.MOX Adventure614583 ................75; i-

  1. https://zulu.ssc.nasa.gov/mrsid/ Gary Parker

    E-Print Network [OSTI]

    Parker, Gary

    https://zulu.ssc.nasa.gov/mrsid/ Gary Parker 2008 Bill Dietrich, Tetsuji Muto, Chuck Nittrouer, Joel Rowland Rudy Slingerland #12; NASA World Wind #12; Australia https://zulu.ssc.nasa.gov/mrsid/ #12; https://zulu.ssc.nasa.gov/mrsid/ #12; https://zulu.ssc.nasa.gov/mrsid/ #12;https://zulu.ssc.nasa

  2. Exoplanet Science from NASA’s Kepler Mission

    SciTech Connect (OSTI)

    Steffen, Jason

    2012-09-12

    NASA's exoplanet mission is the world's premier instrument for the discovery and study of planets orbiting distant stars. As the nominal mission comes to a close, Kepler has discovered nearly 2500 planet candidates, confirmed dozens of multi-planet systems, provided important insights into the orbital architectures of planetary systems, identified specific systems that challenge theories of planet formation and dynamical evolution, has revolutionized our understanding of stellar interiors, and is gearing to measure the frequency of Earth-like planets in the habitable zones of Sun-like stars in its extended mission phase. I present the most recent results from the Kepler mission.

  3. Dear Prospective NASA EPSCoR Researchers: The NASA EPSCoR Cooperative Agreement Notice is released each year on the NASA NSPIRES

    E-Print Network [OSTI]

    Dear Prospective NASA EPSCoR Researchers: The NASA EPSCoR Cooperative Agreement Notice is released each year on the NASA NSPIRES web site. The timing of this release is highly variable, so please check the NASA website frequently for updates. The Hawaii Space Grant Consortium (HSGC) is required by NASA

  4. NASA @ APS | Argonne National Laboratory

    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: Alternative Fuels Data Center Homesum_a_epg0_fpd_mmcf_m.xls" ,"Available from WebQuantityBonneville Power Administration wouldMass map shines light on77 PAGEMissionStressMoveMuncrief Ames019NAPL CalculatorNASA @

  5. Polar features in the flagellar propulsion of E. coli bacteria

    E-Print Network [OSTI]

    Bianchi, S; Lepore, A; Di Leonardo, R

    2015-01-01

    E. coli bacteria swim following a run and tumble pattern. In the run state all flagella join in a single helical bundle that propels the cell body along approximately straight paths. When one or more flagellar motors reverse direction the bundle unwinds and the cell randomizes its orientation. This basic picture represents an idealization of a much more complex dynamical problem. Although it has been shown that bundle formation can occur at either pole of the cell, it is still unclear whether this two run states correspond to asymmetric propulsion features. Using holographic microscopy we record the 3D motions of individual bacteria swimming in optical traps. We find that most cells possess two run states characterised by different propulsion forces, total torque and bundle conformations. We analyse the statistical properties of bundle reversal and compare the hydrodynamic features of forward and backward running states. Our method is naturally multi-particle and opens up the way towards controlled hydrodynam...

  6. Cooperative Self-Propulsion of Active and Passive Rotors

    E-Print Network [OSTI]

    Yaouen Fily; Aparna Baskaran; M. Cristina Marchetti

    2011-10-26

    Using minimal models for low Reynolds number passive and active rotors in a fluid, we characterize the hydrodynamic interactions among rotors and the resulting dynamics of a pair of interacting rotors. This allows us to treat in a common framework passive or externally driven rotors, such as magnetic colloids driven by a rotating magnetic field, and active or internally driven rotors, such as sperm cells confined at boundaries. The hydrodynamic interaction of passive rotors is known to contain an azimuthal component \\sim 1/r^2 to dipolar order that can yield the recently discovered "cooperative self-propulsion" of a pair of rotors of opposite vorticity. While this interaction is identically zero for active rotors as a consequence of torque balance, we show that a \\sim 1/r^4 azimuthal component of the interaction arises in active systems to octupolar order. Cooperative self-propulsion, although weaker, can therefore also occur for pairs of active rotors.

  7. Assessment of Space Nuclear Thermal Propulsion Facility and Capability Needs

    SciTech Connect (OSTI)

    James Werner

    2014-07-01

    The development of a Nuclear Thermal Propulsion (NTP) system rests heavily upon being able to fabricate and demonstrate the performance of a high temperature nuclear fuel as well as demonstrating an integrated system prior to launch. A number of studies have been performed in the past which identified the facilities needed and the capabilities available to meet the needs and requirements identified at that time. Since that time, many facilities and capabilities within the Department of Energy have been removed or decommissioned. This paper provides a brief overview of the anticipated facility needs and identifies some promising concepts to be considered which could support the development of a nuclear thermal propulsion system. Detailed trade studies will need to be performed to support the decision making process.

  8. A comparison between synthetic jets and continuous jets B.L. Smith, G.W. Swift

    E-Print Network [OSTI]

    Smith, Barton L.

    A comparison between synthetic jets and continuous jets B.L. Smith, G.W. Swift Abstract Experimental measurements and flow visualiza- tion of synthetic jets and continuous jets with matched Reynolds numbers are described. Although they have the same profile shape, synthetic jets are wider and slower than

  9. Numerical Simulations for Jet-Proton Interaction

    E-Print Network [OSTI]

    McDonald, Kirk

    inside the jet. Setup of the Simulation of the Circular Jet downstream upstream #12;3 Sergei's result at the Initial Time Energy deposition at x=0 plane, the pressure unit is bar upstream downstream #12;4 Results of the Simulation of the Elliptic Jet downstream upstream #12;7 Jet surface at 0 and 140 microsecond Results from

  10. The interaction between two radial jets 

    E-Print Network [OSTI]

    Gruber, Thomas Clifton

    1993-01-01

    Arrays of impinging jets are used in industry for heat and mass transfer processes. A new type of jet was recently developed which could be utilized in such arrays. This jet is the radial jet and it offers the advantages of variable net force...

  11. Latest Jets Results from the Tevatron

    E-Print Network [OSTI]

    Christina Mesropian

    2011-06-15

    A comprehensive overview of the latest aspects of jet physics in proton-antiproton collisions at $\\sqrt{s}=$1.96 TeV is presented. In particular, measurements of the inclusive jet production, dijet and multi-jet production, and jet substructure studies are discussed.

  12. Jet energy calibration at the LHC

    E-Print Network [OSTI]

    Ariel Schwartzman

    2015-09-17

    Jets are one of the most prominent physics signatures of high energy proton proton (p-p) collisions at the Large Hadron Collider (LHC). They are key physics objects for precision measurements and searches for new phenomena. This review provides an overview of the reconstruction and calibration of jets at the LHC during its first Run. ATLAS and CMS developed different approaches for the reconstruction of jets, but use similar methods for the energy calibration. ATLAS reconstructs jets utilizing input signals from their calorimeters and use charged particle tracks to refine their energy measurement and suppress the effects of multiple p-p interactions (pileup). CMS, instead, combines calorimeter and tracking information to build jets from particle flow objects. Jets are calibrated using Monte Carlo (MC) simulations and a residual in situ calibration derived from collision data is applied to correct for the differences in jet response between data and Monte Carlo. Large samples of dijet, Z+jets, and photon+jet events at the LHC allowed the calibration of jets with high precision, leading to very small systematic uncertainties. Both ATLAS and CMS achieved a jet energy calibration uncertainty of about 1% in the central detector region and for jets with transverse momentum pT>100 GeV. At low jet pT, the jet energy calibration uncertainty is less than 4%, with dominant contributions from pileup, differences in energy scale between quark and gluon jets, and jet flavor composition.

  13. Propellantless propulsion in magnetic fields by partially shielded current

    E-Print Network [OSTI]

    Bergamin, L; Pinchook, A

    2006-01-01

    A new device for propellantless propulsion in presence of a magnetic field is discussed. The functional principle shares some features with electrodynamic tethers. However, the tether structure is replaced by a closed wire, which is partially shielded from the magnetic field by means of a superconductor. Therefore, it does not depend on the presence of a plasma. We show that even a relatively small device can yield interesting propulsivet forces for drag compensation or for orbital transfers.

  14. Water cooled steam jet

    DOE Patents [OSTI]

    Wagner, E.P. Jr.

    1999-01-12

    A water cooled steam jet for transferring fluid and preventing vapor lock, or vaporization of the fluid being transferred, has a venturi nozzle and a cooling jacket. The venturi nozzle produces a high velocity flow which creates a vacuum to draw fluid from a source of fluid. The venturi nozzle has a converging section connected to a source of steam, a diffuser section attached to an outlet and a throat portion disposed there between. The cooling jacket surrounds the venturi nozzle and a suction tube through which the fluid is being drawn into the venturi nozzle. Coolant flows through the cooling jacket. The cooling jacket dissipates heat generated by the venturi nozzle to prevent vapor lock. 2 figs.

  15. Micromachined chemical jet dispenser

    DOE Patents [OSTI]

    Swierkowski, S.P.

    1999-03-02

    A dispenser is disclosed for chemical fluid samples that need to be precisely ejected in size, location, and time. The dispenser is a micro-electro-mechanical systems (MEMS) device fabricated in a bonded silicon wafer and a substrate, such as glass or silicon, using integrated circuit-like fabrication technology which is amenable to mass production. The dispensing is actuated by ultrasonic transducers that efficiently produce a pressure wave in capillaries that contain the chemicals. The 10-200 {micro}m diameter capillaries can be arranged to focus in one spot or may be arranged in a larger dense linear array (ca. 200 capillaries). The dispenser is analogous to some ink jet print heads for computer printers but the fluid is not heated, thus not damaging certain samples. Major applications are in biological sample handling and in analytical chemical procedures such as environmental sample analysis, medical lab analysis, or molecular biology chemistry experiments. 4 figs.

  16. Micromachined chemical jet dispenser

    DOE Patents [OSTI]

    Swierkowski, Steve P. (Livermore, CA)

    1999-03-02

    A dispenser for chemical fluid samples that need to be precisely ejected in size, location, and time. The dispenser is a micro-electro-mechanical systems (MEMS) device fabricated in a bonded silicon wafer and a substrate, such as glass or silicon, using integrated circuit-like fabrication technology which is amenable to mass production. The dispensing is actuated by ultrasonic transducers that efficiently produce a pressure wave in capillaries that contain the chemicals. The 10-200 .mu.m diameter capillaries can be arranged to focus in one spot or may be arranged in a larger dense linear array (.about.200 capillaries). The dispenser is analogous to some ink jet print heads for computer printers but the fluid is not heated, thus not damaging certain samples. Major applications are in biological sample handling and in analytical chemical procedures such as environmental sample analysis, medical lab analysis, or molecular biology chemistry experiments.

  17. Water cooled steam jet

    DOE Patents [OSTI]

    Wagner, Jr., Edward P. (Idaho Falls, ID)

    1999-01-01

    A water cooled steam jet for transferring fluid and preventing vapor lock, or vaporization of the fluid being transferred, has a venturi nozzle and a cooling jacket. The venturi nozzle produces a high velocity flow which creates a vacuum to draw fluid from a source of fluid. The venturi nozzle has a converging section connected to a source of steam, a diffuser section attached to an outlet and a throat portion disposed therebetween. The cooling jacket surrounds the venturi nozzle and a suction tube through which the fluid is being drawn into the venturi nozzle. Coolant flows through the cooling jacket. The cooling jacket dissipates heat generated by the venturi nozzle to prevent vapor lock.

  18. Full fuel-cycle comparison of forklift propulsion systems.

    SciTech Connect (OSTI)

    Gaines, L. L.; Elgowainy, A.; Wang, M. Q.; Energy Systems

    2008-11-05

    Hydrogen has received considerable attention as an alternative to fossil fuels. The U.S. Department of Energy (DOE) investigates the technical and economic feasibility of promising new technologies, such as hydrogen fuel cells. A recent report for DOE identified three near-term markets for fuel cells: (1) Emergency power for state and local emergency response agencies, (2) Forklifts in warehousing and distribution centers, and (3) Airport ground support equipment markets. This report examines forklift propulsion systems and addresses the potential energy and environmental implications of substituting fuel-cell propulsion for existing technologies based on batteries and fossil fuels. Industry data and the Argonne Greenhouse Gases, Regulated Emissions, and Energy Use in Transportation (GREET) model are used to estimate full fuel-cycle emissions and use of primary energy sources, back to the primary feedstocks for fuel production. Also considered are other environmental concerns at work locations. The benefits derived from using fuel-cell propulsion are determined by the sources of electricity and hydrogen. In particular, fuel-cell forklifts using hydrogen made from the reforming of natural gas had lower impacts than those using hydrogen from electrolysis.

  19. Advancements in Dense Plasma Focus (DPF) for Space Propulsion

    SciTech Connect (OSTI)

    Thomas, Robert [Department of Aerospace Engineering, University of Illinois at Urbana - Champaign, Urbana, Illinois 61801 (United States); Yang Yang; Miley, G.H. [Department of Nuclear, Plasma, and Radiological Engineering, University of Illinois at Urbana-- Champaign, Urbana, Illinois 61801 (United States); Mead, F.B. [AFRL/PRSP, 10 E. Saturn Blvd., Edwards AFB CA 93524-7680 (United States)

    2005-02-06

    The development of a dense plasma focus (DPF) propulsion device using p-11B is described. A propulsion system of this type is attractive because of its high thrust-to-weight ratio capabilities at high specific impulses. From a fuel standpoint, p-11B is advantageous because of the aneutronic nature of the reaction, which is favorable for the production of thrust since the charged particles can be channeled by a magnetic field. Different fusion mechanisms are investigated and their implication to the p-11B reaction is explored. Three main requirements must be satisfied to reach breakeven for DPF fusion: a high Ti/Te ratio ({approx}20), an order of magnitude higher pinch lifetime, and the reflection and absorption of at least 50% radiation. Moreover, a power re-circulation method with high efficiency must be available for the relatively low Q value of the DPF fusion reactor. A possible direct energy conversion scheme using magnetic field compression is discussed. DPF parameters are estimated for thrust levels of 1000 kN and 500 kN, and possible propulsion applications are discussed, along with developmental issues.

  20. Meteorology of Jupiter's equatorial hot spots and plumes from Cassini David S. Choi a,

    E-Print Network [OSTI]

    the possibility that the scooter clouds may be more illustrative of the actual jet stream speed at these latitudes velocity of the wave leads to underestimates of the true jet stream speed. Ó 2013 Elsevier Inc. All rights Jet Propulsion Laboratory, California Institute of Technology, Pasadena, CA 91011, USA d NASA Goddard

  1. NASA ADMINISTRATOR'S SYMPOSIUM Risk and Exploration

    E-Print Network [OSTI]

    Rhoads, James

    NASA ADMINISTRATOR'S SYMPOSIUM Risk and Exploration E A R T H , S E A A N D T H E S TA R S STEVEN J, NASA administrator's symposium, September 26-29, 2004, Naval Postgraduate School Monterey, California 2005 910'.9--dc22 2005004470 #12;Risk and Exploration E A R T H , S E A A N D T H E S TA R S NASA

  2. Jets and Jet-like correlations in STAR

    E-Print Network [OSTI]

    Alice Ohlson; for the STAR Collaboration

    2012-10-08

    The propagation and modification of hard-scattered partons in the QGP can be studied using various types of jet and jet-like correlation measurements. The STAR detector with its full azimuthal and large pseudorapidity acceptance, as well as its wide transverse momentum (pT) coverage, is well-suited for these measurements. At mid-rapidity, azimuthal correlations of charged hadrons with the axis of a reconstructed trigger jet are used to study the modification of jet shapes and associated hadron yields from p+p to Au+Au. Dihadron correlations with back-to-back high-pT hadron pairs are used to investigate dijets and fragmentation biases. STAR's increased particle identification capabilities due to the Time-Of-Flight detector are utilized to investigate the differences between jet-related and bulk-related particle production. Dihadron correlations with identified trigger particles provide experimental tests of simple recombination theories. The comprehensive set of STAR jet-quenching measurements can be used to further constrain theories of parton energy loss at RHIC.

  3. CDF/PHYS/JET/CDFR/6419 Version 1.0

    E-Print Network [OSTI]

    Galtieri, Lina

    CDF/PHYS/JET/CDFR/6419 Version 1.0 June 19, 2003 Systematic Uncertainties Associated with Jet. Schmitt Jet Corrections Group Abstract We present an estimate of the systematic uncertainties on the jet jets, as well as for raw jets are given. 1 Introduction In order to convert the jet E T measured

  4. NASA Net Zero Energy Buildings Roadmap

    Energy Savers [EERE]

    gas LCA with guidance from EMD * Step 5. Consider purchase of regional utility "green power" Invest in newly installed offsite RE NZEB Proficiencies for NASA CP-1:...

  5. Fragmentation inside an identified jet

    E-Print Network [OSTI]

    Procura, Massimiliano

    Using Soft?Collinear Effective Theory (SCET) we derive factorization formulae for semi?inclusive processes where a light hadron h fragments from a jet whose invariant mass is measured. Our analysis yields a novel “fragmenting ...

  6. Radial flow pulse jet mixer

    DOE Patents [OSTI]

    VanOsdol, John G.

    2013-06-25

    The disclosure provides a pulse jet mixing vessel for mixing a plurality of solid particles. The pulse jet mixing vessel is comprised of a sludge basin, a flow surface surrounding the sludge basin, and a downcoming flow annulus between the flow surface and an inner shroud. The pulse jet mixing vessel is additionally comprised of an upper vessel pressurization volume in fluid communication with the downcoming flow annulus, and an inner shroud surge volume separated from the downcoming flow annulus by the inner shroud. When the solid particles are resting on the sludge basin and a fluid such as water is atop the particles and extending into the downcoming flow annulus and the inner shroud surge volume, mixing occurs by pressurization of the upper vessel pressurization volume, generating an inward radial flow over the flow surface and an upwash jet at the center of the sludge basin.

  7. Jet production at hadron colliders

    E-Print Network [OSTI]

    Jouttenus, Teppo T. (Teppo Tapani)

    2012-01-01

    Hadronic jets feature in many final states of interest in modern collider experiments. They form a significant Standard Model background for many proposed new physics processes and also probe QCD interactions at several ...

  8. Fragmentation inside an identified jet

    SciTech Connect (OSTI)

    Procura, Massimiliano; Stewart, Iain W.

    2011-05-23

    Using Soft-Collinear Effective Theory (SCET) we derive factorization formulae for semi-inclusive processes where a light hadron h fragments from a jet whose invariant mass is measured. Our analysis yields a novel 'fragmenting jet function' G{sub i}{sup h}(s,z) that depends on the jet invariant mass {radical}(s), and on the fraction z of the large light-cone momentum components of the hadron and the parent parton i. We show that G{sub i}{sup h}(s,z) can be computed in terms of perturbatively calculable coefficients, J{sub ij}(s,z/x), integrated against standard non-perturbative fragmentation functions, D{sub j}{sup h}(x). Our analysis yields a simple replacement rule that allows any factorization theorem depending on a jet function J{sub i} to be converted to a semi-inclusive process with a fragmenting hadron h.

  9. Aeroacoustics of volcanic jets: Acoustic power estimation and jet velocity dependence

    E-Print Network [OSTI]

    Matoza, Robin S; Fee, D; Neilsen, Tracianne B; Gee, Kent L; Ogden, Darcy E

    2013-01-01

    of noise from a military jet aircraft during ground run-up,Radiated by Subsonic Air Jets, David W. Taylor Model Basin,analysis of model-scale jet noise, J. Acoust. Soc. Am. ,

  10. Aeroacoustics of volcanic jets: Acoustic power estimation and jet velocity dependence

    E-Print Network [OSTI]

    Matoza, Robin S; Fee, D; Neilsen, Tracianne B; Gee, Kent L; Ogden, Darcy E

    2013-01-01

    e.g. , the exhaust from jet engines and rockets) [Kundu andow) issuing out of the jet engine or rocket. Other sourcesSupersonic jet noise characteristics and propagation: Engine

  11. Jet Quenching with Parton evolution

    E-Print Network [OSTI]

    Luan Cheng; Enke Wang

    2009-10-08

    We report the evolution effects on jet energy loss with detailed balance. The initial conditions and parton evolution based on perturbative QCD in the chemical non-equilibrated medium and Bjorken expanding medium at RHIC are determined. The parton evolution affect the jet energy loss evidently. This will increase the energy and propagating distance dependence of the parton energy loss and will affect the shape of suppression of moderately high P_{T} hadron spectra.

  12. Convectively generated zonal jets by thunderstorms on Jupiter

    E-Print Network [OSTI]

    Zhang, Xi Arthur; Showman, Adam

    2011-01-01

    formation of equatorial jets in freely decaying shallowof moist convection with zonal jets on Jupiter and Saturn,Generation of equatorial jets by large-scale latent heating

  13. Numerical simulations of volcanic jets: Importance of vent overpressure

    E-Print Network [OSTI]

    Ogden, Darcy E.; Wohletz, Kenneth H.; Glatzmaier, Gary A.; Brodsky, Emily E.

    2008-01-01

    Laboratory studies of volcanic jets, J. Geophys. Res. , 89(Analysis of supersonic air jets, Phys. Rev. , 76(5), 662 –and dynamics of supersonic jets, Astron. Astrophys. , 113(

  14. JETS OF NUCLEAR MATTER FROM HIGH ENERGY HEAVY ION COLLISIONS

    E-Print Network [OSTI]

    Stocker, H.

    2013-01-01

    of California. LBL-11774 Jets of Nuclear Matter from Highclusters. Strongly correlated jets of nuclear matter areExperimental analysis of the jet phenomena is in progress.

  15. PROTOSTELLAR JETS ENCLOSED BY LOW-VELOCITY OUTFLOWS (Journal...

    Office of Scientific and Technical Information (OSTI)

    PROTOSTELLAR JETS ENCLOSED BY LOW-VELOCITY OUTFLOWS Citation Details In-Document Search Title: PROTOSTELLAR JETS ENCLOSED BY LOW-VELOCITY OUTFLOWS A protostellar jet and outflow...

  16. Stopping Cooling Flows with Jets

    E-Print Network [OSTI]

    Fabrizio Brighenti; William G. Mathews

    2006-01-24

    We describe 2D gasdynamical models of jets that carry mass as well as energy to the hot gas in galaxy clusters. These flows have many attractive attributes for solving the galaxy cluster cooling flow problem: Why the hot gas temperature and density profiles resemble cooling flows but show no spectral evidence of cooling to low temperatures. Using an approximate model for the cluster A1795, we show that mass-carrying jets can reduce the overall cooling rate to or below the low values implied by X-ray spectra. Biconical subrelativistic jets, described with several ad hoc parameters, are assumed to be activated when gas flows toward or cools near a central supermassive black hole. As the jets proceed out from the center they entrain more and more ambient gas. The jets lose internal pressure by expansion and are compressed by the ambient cluster gas, becoming rather difficult to observe. For a wide variety of initial jet parameters and several feedback scenarios the global cooling can be suppressed for many Gyrs while maintaining cluster temperature profiles similar to those observed. The intermittancy of the feedback generates multiple generations of X-ray cavities similar to those observed in the Perseus Cluster and elsewhere.

  17. Numerical Simulations of Bouncing Jets

    E-Print Network [OSTI]

    Bonito, Andrea; Lee, Sanghyun

    2015-01-01

    Bouncing jets are fascinating phenomenons occurring under certain conditions when a jet impinges on a free surface. This effect is observed when the fluid is Newtonian and the jet falls in a bath undergoing a solid motion. It occurs also for non-Newtonian fluids when the jets falls in a vessel at rest containing the same fluid. We investigate numerically the impact of the experimental setting and the rheological properties of the fluid on the onset of the bouncing phenomenon. Our investigations show that the occurrence of a thin lubricating layer of air separating the jet and the rest of the liquid is a key factor for the bouncing of the jet to happen. The numerical technique that is used consists of a projection method for the Navier-Stokes system coupled with a level set formulation for the representation of the interface. The space approximation is done with adaptive finite elements. Adaptive refinement is shown to be very important to capture the thin layer of air that is responsible for the bouncing.

  18. Integrated null-flux suspension and multiphase propulsion system for magnetically-levitated vehicles

    DOE Patents [OSTI]

    Rote, D.M.; He, J.; Johnson, L.R.

    1994-01-04

    A propulsion and stabilization system are described comprising a series of coils mounted vertically on the walls of the guideway to provide suspension, lateral guidance, and propulsion of a magnetically levitated vehicle. This system further allows for altering the magnetic field effects by changing the relative position of the loops comprising the coils either longitudinally and/or vertically with resulting changes in the propulsion, the vertical stability, and the suspension. 8 figures.

  19. Integrated null-flux suspension and multiphase propulsion system for magnetically-levitated vehicles

    DOE Patents [OSTI]

    Rote, Donald M. (Lagrange, IL); He, Jianliang (Woodridge, IL); Johnson, Larry R. (Naperville, IL)

    1994-01-01

    A propulsion and stabilization system comprising a series of FIG. 8 coils mounted vertically on the walls of the guideway to provide suspension, lateral guidance and propulsion of a magnetically levitated vehicle. This system further allows for altering the magnetic field effects by changing the relative position of the loops comprising the FIG. 8 coils either longitudinally and/or vertically with resulting changes in the propulsion, the vertical stability, and the suspension.

  20. Integrated null-flux suspension and multiphase propulsion system for magnetically-levitated vehicles

    DOE Patents [OSTI]

    Rote, D.M.; He, Jianliang; Johnson, L.R.

    1992-01-01

    This report discusses a propulsion and stabilization system comprising a series of figure 8 coils mounted vertically on the walls of the guideway to provide suspension, lateral guidance and propulsion of a magnetically levitated vehicle. This system further allows for altering the magnetic field effects by changing the relative position of the loops comprising the figure 8 coils either longitudinally and/or vertically with resulting changes in the propulsion, the vertical stability, and the suspension.

  1. 2014 Propulsion Materials R&D Annual Report | Department of Energy

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

    The Propulsion Materials Program actively supports the energy security and reduction of greenhouse emissions goals of VTO by investigating and identifying the materials properties...

  2. NASA/TM2009000000 From Verified Models to Verifiable

    E-Print Network [OSTI]

    Muñoz, César A.

    NASA/TM­2009­000000 From Verified Models to Verifiable Code Leonard Lensink L.Lensink@cs.ru.nl Radboud University Nijmegen, The Netherlands C´esar Mu~noz cesar.a.munoz@nasa.gov NASA Langley Research, Hampton, Virginia, USA June 2009 #12;NASA STI Program . . . in Profile Since its founding, NASA has been

  3. #MSL #NASAsocial @NASA's first-ever multi-center @NASASocial

    E-Print Network [OSTI]

    Waliser, Duane E.

    #MSL #NASAsocial @NASA's first-ever multi-center @NASASocial @NASAAmes @NASAGlenn @NASAGoddard @NASAJPL @NASA_Johnson @NASAKennedy @NASA_Langley NASA TV Broadcast -- Speaker Program Friday, Aug. 3, 2012 Live from JPL, 9:30 to 11:30 a.m. PDT (12:30 to 2:30 p.m. EDT) Featuring: · Charlie Bolden, NASA

  4. David Kortenkamp NASA Johnson Space Center/Metrica Inc.

    E-Print Network [OSTI]

    Kortenkamp, David

    David Kortenkamp NASA Johnson Space Center/Metrica Inc. David Kortenkamp NASA Johnson Space Center to Control Coupled, Dynamical Life Support Systems David Kortenkamp NASA Johnson Space Center/Metrica Inc. Houston TX 77058 kortenkamp@jsc.nasa.gov http://www.traclabs.com/~korten David Kortenkamp NASA Johnson

  5. Plasma jet ignition device

    DOE Patents [OSTI]

    McIlwain, Michael E. (Franklin, MA); Grant, Jonathan F. (Wayland, MA); Golenko, Zsolt (North Reading, MA); Wittstein, Alan D. (Fairfield, CT)

    1985-01-15

    An ignition device of the plasma jet type is disclosed. The device has a cylindrical cavity formed in insulating material with an electrode at one end. The other end of the cylindrical cavity is closed by a metal plate with a small orifice in the center which plate serves as a second electrode. An arc jumping between the first electrode and the orifice plate causes the formation of a highly-ionized plasma in the cavity which is ejected through the orifice into the engine cylinder area to ignite the main fuel mixture. Two improvements are disclosed to enhance the operation of the device and the length of the plasma plume. One improvement is a metal hydride ring which is inserted in the cavity next to the first electrode. During operation, the high temperature in the cavity and the highly excited nature of the plasma breaks down the metal hydride, liberating hydrogen which acts as an additional fuel to help plasma formation. A second improvement consists of a cavity insert containing a plurality of spaced, metal rings. The rings act as secondary spark gap electrodes reducing the voltage needed to maintain the initial arc in the cavity.

  6. Resolving the jet in Cygnus A

    E-Print Network [OSTI]

    U. Bach; T. P. Krichbaum; E. Middelberg; W. Alef; J. A. Zensus

    2008-12-09

    Our previous studies revealed a good kinematic model for the jet of Cygnus A, but the counter-jet speed is still not well constrained. The central engine and part of the counter-jet of Cyg A are likely to be obscured by free-free absorbing material, presumably a thick torus. At mm-wavelengths, the absorber becomes optically thin, which provides a more detailed view into the inner nuclear region. Knowing the speed of jet and counter-jet and their flux density ratio allows to determine the jet Lorentz factors and orientation. Therefore we started to monitor Cyg A with global VLBI at 43GHz in Oct. 2007. Our first epoch reveals a previously unseen gap between both jets. This could be either a sign for a new counter-jet component that is slowly separating or we start to see the very inner acceleration region of the jet which is not efficiently radiating at radio wavelengths. Further more the image shows transversely resolved jet structures at distances beyond ~0.5pc which facilitate more detailed investigations addressing jet stratification. Analysis of the resolved jet structure shows that the initially wide jet (opening angle ~10deg) collimates within the first parsec into a edge-brightened jet with an opening angle of ~3deg.

  7. The First Calculation of Fractional Jets

    E-Print Network [OSTI]

    Daniele Bertolini; Jesse Thaler; Jonathan R. Walsh

    2015-05-14

    In collider physics, jet algorithms are a ubiquitous tool for clustering particles into discrete jet objects. Event shapes offer an alternative way to characterize jets, and one can define a jet multiplicity event shape, which can take on fractional values, using the framework of "jets without jets". In this paper, we perform the first analytic studies of fractional jet multiplicity $\\tilde{N}_{\\rm jet}$ in the context of $e^+e^-$ collisions. We use fixed-order QCD to understand the $\\tilde{N}_{\\rm jet}$ cross section at order $\\alpha_s^2$, and we introduce a candidate factorization theorem to capture certain higher-order effects. The resulting distributions have a hybrid jet algorithm/event shape behavior which agrees with parton shower Monte Carlo generators. The $\\tilde{N}_{\\rm jet}$ observable does not satisfy ordinary soft-collinear factorization, and the $\\tilde{N}_{\\rm jet}$ cross section exhibits a number of unique features, including the absence of collinear logarithms and the presence of soft logarithms that are purely non-global. Additionally, we find novel divergences connected to the energy sharing between emissions, which are reminiscent of rapidity divergences encountered in other applications. Given these interesting properties of fractional jet multiplicity, we advocate for future measurements and calculations of $\\tilde{N}_{\\rm jet}$ at hadron colliders like the LHC.

  8. 93Dr. Gregory A. Dorais, NASA Ames Research Center Dr. David Kortenkamp, NASA Johnson Space Center ConclusionsConclusions

    E-Print Network [OSTI]

    Kortenkamp, David

    93Dr. Gregory A. Dorais, NASA Ames Research Center Dr. David Kortenkamp, NASA Johnson Space Center and practical. #12;94Dr. Gregory A. Dorais, NASA Ames Research Center Dr. David Kortenkamp, NASA Johnson Space with respect to a change in autonomy? #12;95Dr. Gregory A. Dorais, NASA Ames Research Center Dr. David

  9. Jets in heavy ion collisions at RHIC

    E-Print Network [OSTI]

    Jan Kapitan

    2009-11-25

    Full jet reconstruction in heavy-ion collisions enables a complete study of the modification of jet structure due to energy loss in hot and dense QCD matter, but is challenging due to the high multiplicity environment. The STAR and PHENIX collaborations at RHIC have recently presented measurements of fully reconstructed jets from p+p, Cu+Cu and Au+Au collisions at $\\sqrt{s_\\mathrm{NN}} = 200 \\mathrm{GeV}$. We review the first results on inclusive jet spectra, di-jets and fragmentation functions and discuss their implications on understanding of jet quenching.

  10. Analysis of the Space Propulsion System Problem Using RAVEN

    SciTech Connect (OSTI)

    diego mandelli; curtis smith; cristian rabiti; andrea alfonsi

    2014-06-01

    This paper presents the solution of the space propulsion problem using a PRA code currently under development at Idaho National Laboratory (INL). RAVEN (Reactor Analysis and Virtual control ENviroment) is a multi-purpose Probabilistic Risk Assessment (PRA) software framework that allows dispatching different functionalities. It is designed to derive and actuate the control logic required to simulate the plant control system and operator actions (guided procedures) and to perform both Monte- Carlo sampling of random distributed events and Event Tree based analysis. In order to facilitate the input/output handling, a Graphical User Interface (GUI) and a post-processing data-mining module are available. RAVEN allows also to interface with several numerical codes such as RELAP5 and RELAP-7 and ad-hoc system simulators. For the space propulsion system problem, an ad-hoc simulator has been developed and written in python language and then interfaced to RAVEN. Such simulator fully models both deterministic (e.g., system dynamics and interactions between system components) and stochastic behaviors (i.e., failures of components/systems such as distribution lines and thrusters). Stochastic analysis is performed using random sampling based methodologies (i.e., Monte-Carlo). Such analysis is accomplished to determine both the reliability of the space propulsion system and to propagate the uncertainties associated to a specific set of parameters. As also indicated in the scope of the benchmark problem, the results generated by the stochastic analysis are used to generate risk-informed insights such as conditions under witch different strategy can be followed.

  11. Filament attachment dynamics in actin-based propulsion

    E-Print Network [OSTI]

    J. I. Katz; A. E. Carlsson

    2005-05-26

    Theory and experiment have established that F-actin filaments are strongly attached to the intracellular parasites (such as Listeria) they propel with ``comet tails''. We consider the implications of these observations for propulsion. By calculating the motion produced in various models of attachment and comparing to experiment we demonstrate that the attachment must be sliding rather than hinged. By modeling experiments on ActA-coated spheres we draw conclusions regarding the interaction between F-actin and their surfaces that may also be applicable to living systems.

  12. Nature-inspired microfluidic propulsion using magnetic actuation

    E-Print Network [OSTI]

    Khaderi, S N; Anderson, P D; Ioan, D; Toonder, J M J den; Onck, P R

    2009-01-01

    In this work we mimic the efficient propulsion mechanism of natural cilia by magnetically actuating thin films in a cyclic but non-reciprocating manner. By simultaneously solving the elasto-dynamic, magnetostatic and fluid mechanics equations, we show that the amount of fluid propelled is proportional to the area swept by the cilia. By using the intricate interplay between film magnetization and applied field we are able to generate a pronounced asymmetry and associated flow. We delineate the functional response of the system in terms of three dimensionless parameters that capture the relative contribution of elastic, inertial, viscous and magnetic forces.

  13. ADVANCED RADIOISOTOPE HEAT SOURCE AND PROPULSION SYSTEMS FOR PLANETARY EXPLORATION

    SciTech Connect (OSTI)

    R. C. O'Brien; S. D. Howe; J. E. Werner

    2010-09-01

    The exploration of planetary surfaces and atmospheres may be enhanced by increasing the range and mobility of a science platform. Fundamentally, power production and availability of resources are limiting factors that must be considered for all science and exploration missions. A novel power and propulsion system is considered and discussed with reference to a long-range Mars surface exploration mission with in-situ resource utilization. Significance to applications such as sample return missions is also considered. Key material selections for radioisotope encapsulation techniques are presented.

  14. N Jettiness: An Inclusive Event Shape to Veto Jets

    E-Print Network [OSTI]

    Stewart, Iain

    Jet vetoes are essential in many analyses at the LHC and Tevatron. Typical signals have a specific number of hard jets or leptons, while backgrounds have additional jets. Vetoing undesired jets efficiently discriminates ...

  15. Search for Heavy Majorana Neutrinos in Same-Sign mumu+jets and ee+jets Events in pp Collisions at sqrt(s) = 7 GeV

    E-Print Network [OSTI]

    Giordano, Ferdinando

    2013-01-01

    4.4 Jet Reconstruction . . . . . . . . . . . . . . . . .5.2.5 Jet selection . . . . . .4.4.2 Anti-k T cone jet clustering algorithm . . . 4.4.3 Jet

  16. Jet energy scale setting with "photon+Jet" events at LHC energies. Event rates, Pt structure of jet

    E-Print Network [OSTI]

    D. V. Bandourin; V. F. Konoplianikov; N. B. Skachkov

    2000-12-15

    In this paper the study of "photon+Jet" events is continued, aimed at jet energy scale setting and hadron calorimeter calibration at LHC energies. The event number distribution over Pt and pseudorapidity eta in the barrel region of the photon is presented. The features of "photon+Jet" events in CMS detector |eta|<1.4 are exposed. Pt structure of the region in the eta-phi space inside and beyond jet is also shown.

  17. Jets from Jets: Re-clustering as a tool for large radius jet reconstruction and grooming at the LHC

    E-Print Network [OSTI]

    Benjamin Nachman; Pascal Nef; Ariel Schwartzman; Maximilian Swiatlowski; Chaowaroj Wanotayaroj

    2014-12-11

    Jets with a large radius $R\\gtrsim 1$ and grooming algorithms are widely used to fully capture the decay products of boosted heavy particles at the Large Hadron Collider (LHC). Unlike most discriminating variables used in such studies, the jet radius is usually not optimized for specific physics scenarios. This is because every jet configuration must be calibrated, insitu, to account for detector response and other experimental effects. One solution to enhance the availability of large-$R$ jet configurations used by the LHC experiments is {\\it jet re-clustering}. Jet re-clustering introduces an intermediate scale $rjets are calibrated and used as the inputs to reconstruct large radius jets. In this paper we systematically study and propose new jet re-clustering configurations and show that re-clustered large radius jets have essentially the same jet mass performance as large radius groomed jets. Jet re-clustering has the benefit that no additional large-R calibration is necessary, allowing the re-clustered large radius parameter to be optimized in the context of specific precision measurements or searches for new physics.

  18. NASA agreements advance Mars exploration, Los Alamos Rover instrument...

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

    NASA agreements advance Mars exploration NASA agreements advance Mars exploration, Los Alamos Rover instrument a key component Los Alamos National Laboratory is coordinating with...

  19. NASA Marshall Space Flight Center Improves Cooling System Performance...

    Office of Environmental Management (EM)

    Marshall Space Flight Center Improves Cooling System Performance NASA Marshall Space Flight Center Improves Cooling System Performance NASA Marshall Space Flight Center Improves...

  20. NASA ADVISORY COUNCIL National Aeronautics and Space Administration

    E-Print Network [OSTI]

    Rathbun, Julie A.

    NASA ADVISORY COUNCIL National Aeronautics and Space Administration Washington, DC 20546 Hon Aeronautics and Space Administration Washington, DC 20546 Dear Dr. Griffin: The NASA Advisory Council met

  1. Gravity waves from vortex dipoles and jets 

    E-Print Network [OSTI]

    Wang, Shuguang

    2009-05-15

    The dissertation first investigates gravity wave generation and propagation from jets within idealized vortex dipoles using a nonhydrostatic mesoscale model. Several initially balanced and localized jets induced by vortex dipoles are examined here...

  2. Beamed Core Antimatter Propulsion: Engine Design and Optimization

    E-Print Network [OSTI]

    Ronan Keane; Wei-Ming Zhang

    2012-05-16

    A conceptual design for beamed core antimatter propulsion is reported, where electrically charged annihilation products directly generate thrust after being deflected and collimated by a magnetic nozzle. Simulations were carried out using the Geant4 (Geometry and tracking) software toolkit released by the CERN accelerator laboratory for Monte Carlo simulation of the interaction of particles with matter and fields. Geant permits a more sophisticated and comprehensive design and optimization of antimatter engines than the software environment for simulations reported by prior researchers. The main finding is that effective exhaust speeds Ve ~ 0.69c (where c is the speed of light) are feasible for charged pions in beamed core propulsion, a major improvement over the Ve ~ 0.33c estimate based on prior simulations. The improvement resulted from optimization of the geometry and the field configuration of the magnetic nozzle. Moreover, this improved performance is realized using a magnetic field on the order of 10 T at the location of its highest magnitude. Such a field could be produced with today's technology, whereas prior nozzle designs anticipated and required major advances in this area. The paper also briefly reviews prospects for production of the fuel needed for a beamed core engine.

  3. Polar features in the flagellar propulsion of E. coli bacteria

    E-Print Network [OSTI]

    S. Bianchi; F. Saglimbeni; A. Lepore; R. Di Leonardo

    2015-06-30

    E. coli bacteria swim following a run and tumble pattern. In the run state all flagella join in a single helical bundle that propels the cell body along approximately straight paths. When one or more flagellar motors reverse direction the bundle unwinds and the cell randomizes its orientation. This basic picture represents an idealization of a much more complex dynamical problem. Although it has been shown that bundle formation can occur at either pole of the cell, it is still unclear whether this two run states correspond to asymmetric propulsion features. Using holographic microscopy we record the 3D motions of individual bacteria swimming in optical traps. We find that most cells possess two run states characterised by different propulsion forces, total torque and bundle conformations. We analyse the statistical properties of bundle reversal and compare the hydrodynamic features of forward and backward running states. Our method is naturally multi-particle and opens up the way towards controlled hydrodynamic studies of interacting swimming cells.

  4. Nuclear rockets: High-performance propulsion for Mars

    SciTech Connect (OSTI)

    Watson, C.W.

    1994-05-01

    A new impetus to manned Mars exploration was introduced by President Bush in his Space Exploration Initiative. This has led, in turn, to a renewed interest in high-thrust nuclear thermal rocket propulsion (NTP). The purpose of this report is to give a brief tutorial introduction to NTP and provide a basic understanding of some of the technical issues in the realization of an operational NTP engine. Fundamental physical principles are outlined from which a variety of qualitative advantages of NTP over chemical propulsion systems derive, and quantitative performance comparisons are presented for illustrative Mars missions. Key technologies are described for a representative solid-core heat-exchanger class of engine, based on the extensive development work in the Rover and NERVA nuclear rocket programs (1955 to 1973). The most driving technology, fuel development, is discussed in some detail for these systems. Essential highlights are presented for the 19 full-scale reactor and engine tests performed in these programs. On the basis of these tests, the practicality of graphite-based nuclear rocket engines was established. Finally, several higher-performance advanced concepts are discussed. These have received considerable attention, but have not, as yet, developed enough credibility to receive large-scale development.

  5. Jet energy scale setting with "photon+Jet" events at LHC energies. Generalities, selection rules

    E-Print Network [OSTI]

    D. V. Bandourin; V. F. Konoplianikov; N. B. Skachkov

    2000-12-14

    "photon+Jet" events, based on the q~q-> g+photon and qg-> q+photon subprocesses, are proposed for jet energy scale setting and hadron calorimeter calibration at LHC energies. General features and selection criteria of "photon+Jet" events that would provide a good photon Pt - jet Pt balance are described. CMS detector geometry is taken as the basement.

  6. ALMOST JET STRUCTURES AND FIRST JET-EXTENSIONS OF FIBRED MANIFOLDS

    E-Print Network [OSTI]

    Pasquero, Stefano

    ALMOST JET STRUCTURES AND FIRST JET-EXTENSIONS OF FIBRED MANIFOLDS Paola Morando Dipartimento di conditions for a manifold M to be diffeomorphic to the first jet­extension j1(N) of a fibred manifold N O are given in terms of almost jet structures, i.e. pairs (S, A), where S is a suitable type (2, 1) tensor

  7. Turbulent Jets SUMMARY: This chapter is concerned with turbulent jets, namely their overall

    E-Print Network [OSTI]

    Cushman-Roisin, Benoit

    Chapter 9 Turbulent Jets SUMMARY: This chapter is concerned with turbulent jets, namely their overall shape and velocity structure. The first jets being considered are those penetrating in homogeneous terminology. Continuous Intermittent injection injection Momentum only Jet Puff Buoyancy only Plume Thermal

  8. Jets and Orography: Idealized Experiments with Tip-Jets and Lighthill Blocking

    E-Print Network [OSTI]

    Jets and Orography: Idealized Experiments with Tip-Jets and Lighthill Blocking P.B. Rhines issue on Jets 15 June 2006 #12;2 ABSTRACT In this note we describe some qualitative features of the generation of jet-like concentrated circulations, wakes and blocks by simple mountain-like orography, both

  9. Improved e-Jet Printing -TFOT Improved e-Jet Printing

    E-Print Network [OSTI]

    Rogers, John A.

    Improved e-Jet Printing - TFOT Home Sections News Articles Forums About Us Improved e-Jet Printing at the University of Illinois have developed a technology that provides higher resolution and more versatility in e-jet printing. As opposed to conventional ink-jet printers, where heat or mechanical vibrations are used

  10. Experimental studies of unbiased gluon jets from e^+e^? annihilations using the jet boost algorithm

    E-Print Network [OSTI]

    Wilson, Graham Wallace; Abbiendi, G.; Ainsley, C.; Å kesson, P. F.; Alexander, G.; Allison, J.; Amaral, P.; Anagnostou, G.; Anderson, K.J.; Arcelli, S.; Asai, S.; Axen, D.; Azuelos, G.; Bailey, I.; Barberio, E.

    2004-02-25

    We present the first experimental results based on the jet boost algorithm, a technique to select unbiased samples of gluon jets in e^+e^? annihilations, i.e. gluon jets free of biases introduced by event selection or jet finding criteria. Our...

  11. The 33st International Electric Propulsion Conference, The George Washington University, USA October 6 10, 2013

    E-Print Network [OSTI]

    Walker, Mitchell

    The 33st International Electric Propulsion Conference, The George Washington University, USA, 30332, USA Abstract: Accurate measurement of ion charge flux in the plume of spacecraft electric.walker@ae.gatech.edu #12;The 33st International Electric Propulsion Conference, The George Washington University, USA

  12. Design, fabrication and analysis of a body-caudal fin propulsion system for a microrobotic fish

    E-Print Network [OSTI]

    Wood, Robert

    Design, fabrication and analysis of a body-caudal fin propulsion system for a microrobotic fish Kyu and fabrica- tion of a centimeter-scale propulsion system for a robotic fish. The key to the design are customized to provide the necessary work output for the microrobotic fish. The flexure joints, electrical

  13. 2006-01-0443 Engine-in-the-Loop Testing for Evaluating Hybrid Propulsion

    E-Print Network [OSTI]

    Peng, Huei

    improvements are necessary for diesel propulsion systems to address the rapid escalation of fuel prices of the conventional and hybrid propulsion options provides detailed insight into fuel economy ­ emissions tradeoffs at the vehicle level. INTRODUCTION Diesel engines are particularly suited for medium-duty vehicles due

  14. 2011 International Workshop on Detonation for Propulsion November 14-15, 2011

    E-Print Network [OSTI]

    Texas at Arlington, University of

    on detonation waves related to propulsion is presented in this paper. A brief historical review of the early detonation wave engines (RDE) are reviewed. System integration studies for both PDE- and RDE-based propulsion of detonation waves to hypersonic flow simulation and power generation. Introduction Pulse Detonation Engine

  15. JOURNAL OF PROPULSION AND POWER Vol. 20, No. 2, MarchApril 2004

    E-Print Network [OSTI]

    Papamoschou, Dimitri

    JOURNAL OF PROPULSION AND POWER Vol. 20, No. 2, March­April 2004 Engine Cycle and Exhaust Configuration for Quiet Supersonic Propulsion Dimitri Papamoschou University of California, Irvine, Irvine number of instability waves that produce intense downward sound radiation. Subscale experiments show that

  16. ASPECTS OF SENSORY CUES AND PROPULSION IN MARINE ZOOPLANKTON HYDRODYNAMIC DISTURBANCES

    E-Print Network [OSTI]

    colleagues (Environmental Fluid Mechanics and Biology graduate students) for their input and adviceASPECTS OF SENSORY CUES AND PROPULSION IN MARINE ZOOPLANKTON HYDRODYNAMIC DISTURBANCES A Thesis Institute of Technology December 2009 #12;ASPECTS OF SENSORY CUES AND PROPULSION IN MARINE ZOOPLANKTON

  17. The 33st International Electric Propulsion Conference, The George Washington University, USA October 6 10, 2013

    E-Print Network [OSTI]

    King, Lyon B.

    The 33st International Electric Propulsion Conference, The George Washington University, USA Electric Propulsion Conference, The George Washington University · Washington, D.C. · USA October 6 ­ 10-NTf2. The magnetic properties of the fluid were exploited to create self-assembling array of peaks

  18. The 32nd International Electric Propulsion Conference, Wiesbaden, Germany September 11 15, 2011

    E-Print Network [OSTI]

    International Electric Propulsion Conference, Wiesbaden, Germany September 11 ­ 15, 2011 2 magnetic fieldThe 32nd International Electric Propulsion Conference, Wiesbaden, Germany September 11 ­ 15, 2011 1 Effect of Magnetic Shielding on Plasma Plume of the Cylindrical Hall Thrusters IEPC-2011-175 Presented

  19. The 32nd International Electric Propulsion Conference, Wiesbaden, Germany September 11 15, 2011

    E-Print Network [OSTI]

    The 32nd International Electric Propulsion Conference, Wiesbaden, Germany September 11 ­ 15, 2011 1 Electric Propulsion Conference, Wiesbaden · Germany September 11 ­ 15, 2011 K. Matyash1 , Max and possibly to the spoke phenomenon. Nomenclature B = magnetic field e = electron charge E = electric field m

  20. The 29th International Electric Propulsion Conference, Princeton University, October 31 November 4, 2005

    E-Print Network [OSTI]

    Walker, Mitchell

    The 29th International Electric Propulsion Conference, Princeton University, October 31 ­ November International Electric Propulsion Conference, Princeton University, October 31 ­ November 4, 2005 James H magnetic field transient with the vacuum facility. The thrust stand has been revamped to allow for active

  1. International Electric Propulsion Conference, Florence, Italy September 17-20, 2007

    E-Print Network [OSTI]

    Walker, Mitchell

    The 30th International Electric Propulsion Conference, Florence, Italy September 17-20, 2007 1-236 Presented at the 30th International Electric Propulsion Conference, Florence, Italy September 17-20, 2007 b = annulus outer diameter c = speed of light B = perturbed magnetic field B0 = equilibrium magnetic

  2. Principles of Rotating Plasma in Plasma Propulsion Systems N. J. Fisch

    E-Print Network [OSTI]

    Principles of Rotating Plasma in Plasma Propulsion Systems N. J. Fisch Department of Astrophysical Sciences Princeton University 33rd International Electric Propulsion Conference (IEPC2013 in crossed electric and magnetic fields. This talk reviews at a tutorial level some of the interesting

  3. International Electric Propulsion Conference, Princeton University, October 31 November 4, 2005

    E-Print Network [OSTI]

    King, Lyon B.

    The 29th International Electric Propulsion Conference, Princeton University, October 31 ­ November-effect Thruster IEPC-2005-274 Presented at the 29th International Electric Propulsion Conference, Princeton electron plasma in a pristine environment. A purely radial magnetic field is applied with a crossed

  4. An Analysis of Energy Balance in a Helicon Plasma Source for Space Propulsion

    E-Print Network [OSTI]

    An Analysis of Energy Balance in a Helicon Plasma Source for Space Propulsion by Justin Matthew;An Analysis of Energy Balance in a Helicon Plasma Source for Space Propulsion by Justin Matthew Pucci are optical radiation emission, wall losses due to poor magnetic confinement, and poor antenna-plasma coupling

  5. The Rotational Propulsion Characteristics of Scaled-up Helical Microswimmers with different heads and magnetic positioning

    E-Print Network [OSTI]

    of the cut-off frequency. The rotational propulsion characteristics of helical swimmers with a magnetic headThe Rotational Propulsion Characteristics of Scaled-up Helical Microswimmers with different heads and magnetic positioning Tiantian Xu1, Gilgueng Hwang2, Nicolas Andreff3 and St´ephane R´egnier1 Abstract

  6. Control Engineering Practice 15 (2007) 149162 Hierarchical control of aircraft propulsion systems: Discrete

    E-Print Network [OSTI]

    Ray, Asok

    2007-01-01

    , and domain knowledge of gas turbine engine propulsion. ARTICLE IN PRESS wwwControl Engineering Practice 15 (2007) 149­162 Hierarchical control of aircraft propulsion systems: Discrete event supervisor approach Murat Yasar, Asok Rayà Mechanical and Nuclear Engineering Department

  7. The 32nd International Electric Propulsion Conference, Wiesbaden, Germany September 11 15, 2011

    E-Print Network [OSTI]

    The 32nd International Electric Propulsion Conference, Wiesbaden, Germany September 11 ­ 15, 2011 1-247 Presented at the 32nd International Electric Propulsion Conference, Wiesbaden · Germany September 11 ­ 15 energy ions flowing at large angles with respect to the thruster centerline. It was suggested

  8. Strategic Control of Transverse Jet Shear Layer Instabilities J. Davitian,

    E-Print Network [OSTI]

    M'Closkey, Robert T.

    engines, dilution jet injection in gas turbine combustors, thrust vectoring jets, and turbine blade filmStrategic Control of Transverse Jet Shear Layer Instabilities J. Davitian, C. Hendrickson, D jet in crossflow or transverse jet. Jet nozzles that are flush as well as elevated with respect

  9. Technology survey and performance scaling for the design of high power nuclear electric power and propulsion systems

    E-Print Network [OSTI]

    White, Daniel B., Jr

    2011-01-01

    High power nuclear electric propulsion systems have the capability to enable many next-generation space exploration applications. To date, use of electric primary propulsion in flight systems has been limited to low-power, ...

  10. Advanced thermally stable jet fuels

    SciTech Connect (OSTI)

    Schobert, H.H.

    1999-01-31

    The Pennsylvania State University program in advanced thermally stable coal-based jet fuels has five broad objectives: (1) Development of mechanisms of degradation and solids formation; (2) Quantitative measurement of growth of sub-micrometer and micrometer-sized particles suspended in fuels during thermal stressing; (3) Characterization of carbonaceous deposits by various instrumental and microscopic methods; (4) Elucidation of the role of additives in retarding the formation of carbonaceous solids; (5) Assessment of the potential of production of high yields of cycloalkanes by direct liquefaction of coal. Future high-Mach aircraft will place severe thermal demands on jet fuels, requiring the development of novel, hybrid fuel mixtures capable of withstanding temperatures in the range of 400--500 C. In the new aircraft, jet fuel will serve as both an energy source and a heat sink for cooling the airframe, engine, and system components. The ultimate development of such advanced fuels requires a thorough understanding of the thermal decomposition behavior of jet fuels under supercritical conditions. Considering that jet fuels consist of hundreds of compounds, this task must begin with a study of the thermal degradation behavior of select model compounds under supercritical conditions. The research performed by The Pennsylvania State University was focused on five major tasks that reflect the objectives stated above: Task 1: Investigation of the Quantitative Degradation of Fuels; Task 2: Investigation of Incipient Deposition; Task 3: Characterization of Solid Gums, Sediments, and Carbonaceous Deposits; Task 4: Coal-Based Fuel Stabilization Studies; and Task 5: Exploratory Studies on the Direct Conversion of Coal to High Quality Jet Fuels. The major findings of each of these tasks are presented in this executive summary. A description of the sub-tasks performed under each of these tasks and the findings of those studies are provided in the remainder of this volume (Sections 1 through 5).

  11. The Remote Photogrammetric Survey and Engineering Analysis of the Divertor Structure during JET’s Remote Tile Exchange

    E-Print Network [OSTI]

    The Remote Photogrammetric Survey and Engineering Analysis of the Divertor Structure during JET’s Remote Tile Exchange

  12. Theoretical and Experimental Simulation of Accident Scenarios of the JET Cryogenic Components Part II: The JET LHCD Cryopump

    E-Print Network [OSTI]

    Theoretical and Experimental Simulation of Accident Scenarios of the JET Cryogenic Components Part II: The JET LHCD Cryopump

  13. Jet physics at HERA, Tevatron and LHC

    E-Print Network [OSTI]

    C. Royon

    2008-11-10

    In this short report, we discuss the Jet Physics results and perspectives at HERA, Tevatron and LHC.

  14. Jets in relativistic heavy ion collisions

    SciTech Connect (OSTI)

    Wang, Xin-Nian; Gyulassy, M.

    1990-09-01

    Several aspects of hard and semihard QCD jets in relativistic heavy ion collisions are discussed, including multiproduction of minijets and the interaction of a jet with dense nuclear matter. The reduction of jet quenching effect in deconfined phase of nuclear matter is speculated to provide a signature of the formation of quark gluon plasma. HIJING Monte Carlo program which can simulate events of jets production and quenching in heavy ion collisions is briefly described. 35 refs., 13 figs.

  15. WORKSHOP REPORT: Trucks and Heavy-Duty Vehicles Technical Requirements and Gaps for Lightweight and Propulsion Materials

    Office of Energy Efficiency and Renewable Energy (EERE)

    WORKSHOP REPORT: Trucks and Heavy-Duty Vehicles Technical Requirements and Gaps for Lightweight and Propulsion Materials

  16. Monte Carlo Tools for Jet Quenching

    E-Print Network [OSTI]

    Korinna Zapp

    2011-09-07

    A thorough understanding of jet quenching on the basis of multi-particle final states and jet observables requires new theoretical tools. This talk summarises the status and propects of the theoretical description of jet quenching in terms of Monte Carlo generators.

  17. Probing nuclear matter with jet conversions 

    E-Print Network [OSTI]

    Liu, W.; Fries, Rainer J.

    2008-01-01

    We discuss the flavor of leading jet partons as a valuable probe of nuclear matter. We point out that the coupling of jets to nuclear matter naturally leads to an alteration of jet chemistry even at high transverse momentum PT. In particular...

  18. Jet operators on fields Piotr Kowalski*

    E-Print Network [OSTI]

    Kowalski, Piotr

    Jet operators on fields Piotr Kowalski-Champaign Abstract We classify jet operators in the sense of Buium [Bu ] on a field of an arbitrary of the Frobenius map. 1 Introduction In [Bu ], Buium introduced jet operators on rings; they are natural

  19. Searching for Jets in Heavy Ion Collisions

    E-Print Network [OSTI]

    Sevil Salur

    2008-09-09

    Jet quenching measurements using leading particles and their correlations suffer from known biases, which can be removed via direct reconstruction of jets in central heavy ion collisions. In this talk, we discuss several modern jet reconstruction algorithms and background subtraction techniques that are appropriate to heavy ion collisions.

  20. Shuttle Spinoffs www.nasa.gov

    E-Print Network [OSTI]

    : Homeowners are insulating their homes with the same lightweight, flexible aerogel NASA uses to insulate: Rescue squads use a new handheld cutter to remove accident victims from wrecked vehicles. Based

  1. Use of High-Power Brayton Nuclear Electric Propulsion (NEP) for a 2033 Mars Round-Trip Mission

    SciTech Connect (OSTI)

    McGuire, Melissa L. [Space Propulsion and Mission Analysis Office (Code: PBM), NASA Glenn Research Center, MS 500-103, 21000 Brookpark Rd., Cleveland, Ohio 44135 (United States); Martini, Michael C.; Packard, Thomas W. [Space Propulsion and Mission Analysis Office (Code: PBM), NASA Glenn Research Center, MS 500-103, 21000 Brookpark Rd., Cleveland, Ohio 44135 (United States); Analex Corporation, 1100 Apollo Drive, Brook Park, OH 44142 (United States); Weglian, John E. [Space Propulsion and Mission Analysis Office (Code: PBM), NASA Glenn Research Center, MS 500-103, 21000 Brookpark Rd., Cleveland, Ohio 44135 (United States); Ohio Aerospace Institute, 22800 Cedar Point Rd., Brook Park, OH 44142 (United States); Gilland, James H. [Ohio Aerospace Institute, 22800 Cedar Point Rd., Brook Park, OH 44142 (United States)

    2006-01-20

    The Revolutionary Aerospace Systems Concepts (RASC) team, led by the NASA Langley Research Center, is tasked with exploring revolutionary new approaches to enabling NASA to achieve its strategic goals and objectives in future missions. This paper provides the details from the 2004-2005 RASC study of a point-design that uses a high-power nuclear electric propulsion (NEP) based space transportation architecture to support a manned mission to Mars. The study assumes a high-temperature liquid-metal cooled fission reactor with a Brayton power conversion system to generate the electrical power required by magnetoplasmadynamic (MPD) thrusters. The architecture includes a cargo vehicle with an NEP system providing 5 MW of electrical power and a crewed vehicle with an NEP system with two reactors providing a combined total of 10 MW of electrical power. Both vehicles use a low-thrust, high-efficiency (5000 sec specific impulse) MPD system to conduct a spiral-out of the Earth gravity well, a low-thrust heliocentric trajectory, and a spiral-in at Mars with arrival late in 2033. The cargo vehicle carries two moon landers to Mars and arrives shortly before the crewed vehicle. The crewed vehicle and cargo vehicle rendezvous in Mars orbit and, over the course of the 60-day stay, the crew conducts nine-day excursions to Phobos and Deimos with the landers. The crewed vehicle then spirals out of Martian orbit and returns via a low-thrust trajectory to conduct an Earth flyby. The crew separates from the vehicle prior to Earth flyby and aerobrakes for a direct-entry landing.

  2. The Particle Content of Extragalactic Jets

    E-Print Network [OSTI]

    David S. De Young

    2006-05-31

    Recent x-ray and radio data from radio sources in galaxy clusters are used to show that the pdV work required to inflate the radio lobes exceeds all other energy estimates deduced from the radio emission. If the required jet energy density has an isotropic pressure, then in almost all cases the jet cannot be confined by an external medium. This problem can be resolved with jets dominated by cold protons, but even here the accompanying energy density in relativistic electons can cause decollimation. Electron-positron jets cannot solve this problem unless they are highly beamed with unusual energy distributions. Poynting flux jets may be a viable alternative.

  3. Jet energy scale setting with "photon+Jet" events at LHC energies. Selection of events with a clean "photon+Jet" topology and photon Pt - jet Pt disbalance

    E-Print Network [OSTI]

    D. V. Bandourin; V. F. Konoplyanikov; N. B. Skachkov

    2001-04-27

    It is shown in the paper that Pt activity limitation (modulus of the vector sum) of all particle beyond "photon+Jet" system Pt^out leads to the noticeable photon Pt - jet Pt disbalance decreasing. On a simultaneous restriction of the cluster Pt and Pt^out from above it is possible to reach an acceptable balance between photon Pt - jet Pt with a sufficient number of the photon Pt - jet Pt events for the jet energy scale setting and hadron calorimeter calibratiom of the CMS detector at LHC.

  4. The Structure and Dynamics of GRB Jets

    E-Print Network [OSTI]

    Jonathan Granot

    2006-10-12

    There are several lines of evidence which suggest that the relativistic outflows in gamma-ray bursts (GRBs) are collimated into narrow jets. The jet structure has important implications for the true energy release and the event rate of GRBs, and can constrain the mechanism responsible for the acceleration and collimation of the jet. Nevertheless, the jet structure and its dynamics as it sweeps up the external medium and decelerates, are not well understood. In this review I discuss our current understanding of GRB jets, stressing their structure and dynamics.

  5. Convective Heat Transfer Coefficients of Automatic Transmission Fluid Jets with Implications for Electric Machine Thermal Management: Preprint

    SciTech Connect (OSTI)

    Bennion, Kevin; Moreno, Gilberto

    2015-09-29

    Thermal management for electric machines (motors/ generators) is important as the automotive industry continues to transition to more electrically dominant vehicle propulsion systems. Cooling of the electric machine(s) in some electric vehicle traction drive applications is accomplished by impinging automatic transmission fluid (ATF) jets onto the machine's copper windings. In this study, we provide the results of experiments characterizing the thermal performance of ATF jets on surfaces representative of windings, using Ford's Mercon LV ATF. Experiments were carried out at various ATF temperatures and jet velocities to quantify the influence of these parameters on heat transfer coefficients. Fluid temperatures were varied from 50 degrees C to 90 degrees C to encompass potential operating temperatures within an automotive transaxle environment. The jet nozzle velocities were varied from 0.5 to 10 m/s. The experimental ATF heat transfer coefficient results provided in this report are a useful resource for understanding factors that influence the performance of ATF-based cooling systems for electric machines.

  6. Shear Layer Instabilities and Mixing in Variable Density Transverse Jet Flows

    E-Print Network [OSTI]

    Getsinger, Daniel

    2012-01-01

    of the Jet in Crossflow . . . . . . . . . . . . . . .The Variable Density Jet in Crossflow . . . . . . . . .The Single-Phase Jet in Crossflow . . . . . . .

  7. NASA Centennial Challenges were initiated in 2005 to directly engage

    E-Print Network [OSTI]

    Waliser, Duane E.

    competitions for infusion into NASA missions. Enable Challenge competitors to develop and/or expand business

  8. October 2010 NASA/CR2010-216861

    E-Print Network [OSTI]

    October 2010 NASA/CR­2010-216861 Optimizing Air Transportation Service to Metroplex Airports Part Mason University, Fairfax, Virginia #12;NASA STI Program . . . in Profile Since its founding, NASA has been dedicated to the advancement of aeronautics and space science. The NASA scientific and technical

  9. Three NASA Application Domains for Integrated Planning, Scheduling and Execution

    E-Print Network [OSTI]

    Kortenkamp, David

    Three NASA Application Domains for Integrated Planning, Scheduling and Execution David Kortenkamp. NASA Johnson Space Center { ER2 Houston, TX 77058 kortenkamp@jsc.nasa.gov Abstract This paper describes three application domains for in- tegrating planning, scheduling and execution at NASA Johnson Space

  10. February 2013 NASA/TM2013-217969

    E-Print Network [OSTI]

    Maddalon, Jeffrey M.

    February 2013 NASA/TM­2013-217969 Perspectives on Unmanned Aircraft Classification for Civil, Poquoson, Virginia #12;NASA STI Program . . . in Profile Since its founding, NASA has been dedicated to the advancement of aeronautics and space science. The NASA scientific and technical information (STI) program

  11. NASA/TP--2006214434 Examination of the Armagh Observatory

    E-Print Network [OSTI]

    NASA/TP--2006­214434 Examination of the Armagh Observatory Annual Mean Temperature Record, 1844, Alabama July 2006 #12;The NASA STI Program Office...in Profile Since its founding, NASA has been dedicated to the advancement of aeronautics and space science. The NASA Scientific and Technical Information (STI) Program

  12. NASA/TP--2006214196 Haughton-Mars Project Expedition 2005

    E-Print Network [OSTI]

    de Weck, Olivier L.

    NASA/TP--2006­214196 Haughton-Mars Project Expedition 2005 Final Report Prof. Olivier de Weck: Press F1 key (Windows) or Help key (Mac) for help January 2006 #12;NASA STI Program ... in Profile Since its founding, NASA has been dedicated to the advancement of aeronautics and space science. The NASA

  13. October 2008 NASA/TM-2008-215356

    E-Print Network [OSTI]

    Butler, Ricky W.

    October 2008 NASA/TM-2008-215356 A Formal Framework for the Analysis of Algorithms That Recover National Institute of Aerospace, Hampton, Virginia #12;The NASA STI Program Office . . . in Profile Since its founding, NASA has been dedicated to the advancement of aeronautics and space science. The NASA

  14. October 2010 NASA/CR2010-216860

    E-Print Network [OSTI]

    October 2010 NASA/CR­2010-216860 Optimizing Air Transportation Service to Metroplex Airports Part 1;NASA STI Program . . . in Profile Since its founding, NASA has been dedicated to the advancement of aeronautics and space science. The NASA scientific and technical information (STI) program plays a key part

  15. November 2007 NASA/TM-2007-215088

    E-Print Network [OSTI]

    Butler, Ricky W.

    November 2007 NASA/TM-2007-215088 The ANMLite Language and Logic for Specifying Planning Problems National Institute of Aerospace, Hampton, Virginia #12;The NASA STI Program Office . . . in Profile Since its founding, NASA has been dedicated to the advancement of aeronautics and space science. The NASA

  16. November 2006 NASA/TM-2006-214518

    E-Print Network [OSTI]

    Muñoz, César A.

    November 2006 NASA/TM-2006-214518 An Abstract Plan Preparation Language Ricky W. Butler Langley;The NASA STI Program Office . . . in Profile Since its founding, NASA has been dedicated to the advancement of aeronautics and space science. The NASA Scientific and Technical Information (STI) Program

  17. Learning From NASA Mishaps: What Separates Success From Failure?

    E-Print Network [OSTI]

    Rhoads, James

    1 Learning From NASA Mishaps: What Separates Success From Failure? Project Management Challenge Call? NASA Mishap. An unplanned event that results in at least one of the following: ­ Injury to non-NASA personnel, caused by NASA operations. ­ Damage to public or private property (including foreign property

  18. National Aeronautics and Space Administration www.nasa.gov

    E-Print Network [OSTI]

    National Aeronautics and Space Administration www.nasa.gov Produced in 2011 by the NASA Astrobiology Program to commemorate 50 years of Exobiology and Astrobiology at NASA. #2 Issue #12;Astrobiology A History of Exobiology and Astrobiology at NASA This is the story of life in the Universe--or at least

  19. National Aeronautics and Space Administration www.nasa.gov

    E-Print Network [OSTI]

    Christian, Eric

    National Aeronautics and Space Administration www.nasa.gov Volume 2 Issue 18 October 2006 GoddardViewNASA at: http://www.nasa.gov/centers/goddard/news/index.html Managing Editor: Trusilla Steele Editor via e-mail at alittle@pop100.gsfc.nasa.gov. Ideas for new stories are welcome but will be published

  20. February 2013 NASA/TM-2013-217804

    E-Print Network [OSTI]

    Butler, Ricky W.

    February 2013 NASA/TM-2013-217804 The Simplified Aircraft-Based Paired Approach with the ALAS Research Center, Hampton, Virginia #12;NASA STI Program . . . in Profile Since its founding, NASA has been dedicated to the advancement of aeronautics and space science. The NASA scientific and technical information

  1. Montana NASA EPSCoR 2015 Research Group Program

    E-Print Network [OSTI]

    Maxwell, Bruce D.

    Montana NASA EPSCoR 2015 Research Group Program Call for Pre-proposals Introductory Note: This NASA that NASA will soon be issuing a Cooperative Agreement Notice (CAN) for the federal fiscal year 2015 EPSCo proposals for potential funding under this CAN. Awards will be for three years. NASA funding for a selected

  2. August 2014 NASA/TM-2014-218511

    E-Print Network [OSTI]

    Maddalon, Jeffrey M.

    August 2014 NASA/TM-2014-218511 A Review of Current and Prospective Factors for Classification. Verstynen Whirlwind Engineering LLC, Poquoson, Virginia #12;NASA STI Program . . . in Profile Since its founding, NASA has been dedicated to the advancement of aeronautics and space science. The NASA scientific

  3. October 2006 NASA/CR-2006-214298

    E-Print Network [OSTI]

    Muñoz, César A.

    October 2006 NASA/CR-2006-214298 NIA Report No. 2006-01 A High-Level Formalization of Floating of Aerospace, Hampton, Virginia #12;The NASA STI Program Office . . . in Profile Since its founding, NASA has been dedicated to the advancement of aeronautics and space science. The NASA Scientific and Technical

  4. NASA/TM2014218280 Analysis of Well-Clear Boundary

    E-Print Network [OSTI]

    Muñoz, César A.

    NASA/TM­2014­218280 Analysis of Well-Clear Boundary Models for the Integration of UAS in the NAS Research Center, Hampton, Virginia June 2014 #12;NASA STI Program . . . in Profile Since its founding, NASA has been dedicated to the advancement of aeronautics and space science. The NASA scientific

  5. January 2014 NASA/TM2014-218155

    E-Print Network [OSTI]

    Muñoz, César A.

    January 2014 NASA/TM­2014-218155 A Well-Clear Volume Based on Time to Entry Point Anthony J Center, Hampton, Virginia #12;NASA STI Program . . . in Profile Since its founding, NASA has been dedicated to the advancement of aeronautics and space science. The NASA scientific and technical information

  6. February 2007 NASA/TM-2007-214539

    E-Print Network [OSTI]

    Maddalon, Jeffrey M.

    February 2007 NASA/TM-2007-214539 Preliminary Considerations for Classifying Hazards of Unmanned NASA STI Program Office ... in Profile Since its founding, NASA has been dedicated to the advancement of aeronautics and space science. The NASA Scientific and Technical Information (STI) Program Office plays a key

  7. February 2008 NASA/TM-2008-215108

    E-Print Network [OSTI]

    Butler, Ricky W.

    February 2008 NASA/TM-2008-215108 A Primer on Architectural Level Fault Tolerance Ricky W. Butler Langley Research Center, Hampton, Virginia #12;The NASA STI Program Office . . . in Profile Since its founding, NASA has been dedicated to the advancement of aeronautics and space science. The NASA Scientific

  8. November 2014 NASA/TM2014-218548

    E-Print Network [OSTI]

    Muñoz, César A.

    November 2014 NASA/TM­2014-218548 A Formally-Verified Decision Procedure for Univariate Polynomial, Virginia #12;NASA STI Program . . . in Profile Since its founding, NASA has been dedicated to the advancement of aeronautics and space science. The NASA scientific and technical information (STI) program

  9. NASA DESK GUIDE TABLE OF DISCIPLINARY OFFENSES AND PENALTIES

    E-Print Network [OSTI]

    Christian, Eric

    NASA DESK GUIDE FOR TABLE OF DISCIPLINARY OFFENSES AND PENALTIES Version 3 Office of Human Capital Management NASA Headquarters SREF-3000-0020 August 2008 #12;NASA Desk Guide for Table of Disciplinary #41 and offense #46. #12;NASA Desk Guide for Table of Disciplinary Offenses and Penalties ­ Version 3

  10. National Aeronautics and Space Administration www.nasa.gov

    E-Print Network [OSTI]

    Christian, Eric

    National Aeronautics and Space Administration www.nasa.gov Volume 4, Issue 11 June 2008 GoddardViewNASA Composite Carrier for Hubble Servicing Mission Pg 4 NASA Technology Contributes to National Security Pg 6 One Million People Going to the Moon ­ 2 NASA Exhibit Pays Tribute to Fallen Heroes of Spaceflight

  11. 2012 Montana NASA EPSCoR Faculty Connections Program

    E-Print Network [OSTI]

    Maxwell, Bruce D.

    2012 Montana NASA EPSCoR Faculty Connections Program Montana NASA EPSCoR has been awarded funding and funding to arrange travel to a NASA research center with the goal of developing new collaborations, projects, and proposals to foster the growth of NASA related funded research at Montana institutions

  12. NASA TM-2012-217361 Evaluating Shielding Approaches to Reduce

    E-Print Network [OSTI]

    Rathbun, Julie A.

    NASA TM-2012-217361 Evaluating Shielding Approaches to Reduce Space Radiation Cancer Risks Francis A. Cucinotta NASA Lyndon B. Johnson Space Center Houston, Texas Myung-Hee Y. Kim U.S.R.A., Division, Texas May 2012 #12;THE NASA STI PROGRAM OFFICE . . . IN PROFILE Since its founding, NASA has been

  13. NASA/TP2009213146REVISION A International Space Station

    E-Print Network [OSTI]

    analysis. · CONTRACTOR REPORT. Scientific and technical findings by NASA-sponsored contractors and grantees

  14. NASA/TM2002217743 Title of My Paper

    E-Print Network [OSTI]

    analysis. · CONTRACTOR REPORT. Scientific and technical findings by NASA-sponsored contractors and grantees

  15. NASA/TM2012-217585 Air Traffic Management Technology

    E-Print Network [OSTI]

    analysis. CONTRACTOR REPORT. Scientific and technical findings by NASA-sponsored contractors and grantees

  16. NASA/TP2014216648/REV1 Small Spacecraft Technology

    E-Print Network [OSTI]

    analysis. CONTRACTOR REPORT. Scientific and technical findings by NASA-sponsored contractors and grantees

  17. Jets and Underlying Events at LHC Energies

    E-Print Network [OSTI]

    A. G. Agócs; G. G. Barnaföldi; P. Lévai

    2010-11-24

    Jet-matter interaction remains a central question and a theoretical challenge in heavy-ion physics and might become important in high-multiplicity events in proton-proton collisions at LHC energies. Full jet measurement at LHC offer the proper tool to investigate energy loss process and fragmentation of hard parton in the medium. Since jet reconstruction will be constrained to small cone sizes, then study of the connection between jets and surrounding environment provides a further possibility to extend our exploration. We study jets at s = (14 TeV)^2 and pp collisions at s = (7 TeV)^2. We analyze the flavor components in jet-like environments. We introduce a definition for surrounding cones/belts and investigate flavor dependence and correlation of different hadron species produced in jets. Here, we focus on proton-triggered correlations. Our analysis can be extended for heavy ion collisions.

  18. Nuclear electric propulsion operational reliability and crew safety study

    SciTech Connect (OSTI)

    Karns, J.J.; Fragola, J.R.; Kahan, L.; Pelaccio, D. (Science Applications International Corporation, 8 W 40th St., 14th Floor, New York, New York 10018 (United States))

    1993-01-20

    The central purpose of this analysis is to assess the achievability'' of a nuclear electric propulsion (NEP) system in a given mission. Achievability'' is a concept introduced to indicate the extent to which a system that meets or achieves its design goals might be implemented using the existing technology base. In the context of this analysis, the objective is to assess the achievability of an NEP system for a manned Mars mission as it pertains to operational reliability and crew safety goals. By varying design parameters, then examining the resulting system achievability, the design and mission risk drivers can be identified. Additionally, conceptual changes in design approach or mission strategy which are likely to improve overall achievability of the NEP system can be examined.

  19. Macroscopic and direct light propulsion of bulk graphene material

    E-Print Network [OSTI]

    Zhang, Tengfei; Wu, Yingpeng; Xiao, Peishuang; Yi, Ningbo; Lu, Yanhong; Ma, Yanfeng; Huang, Yi; Zhao, Kai; Yan, Xiao-Qing; Liu, Zhi-Bo; Tian, Jian-Guo; Chen, Yongsheng

    2015-01-01

    It has been a great challenge to achieve the direct light manipulation of matter on a bulk scale. In this work, the direct light propulsion of matter was observed on a macroscopic scale for the first time using a bulk graphene based material. The unique structure and properties of graphene and the morphology of the bulk graphene material make it capable of not only absorbing light at various wavelengths but also emitting energetic electrons efficiently enough to drive the bulk material following Newtonian mechanics. Thus, the unique photonic and electronic properties of individual graphene sheets are manifested in the response of the bulk state. These results offer an exciting opportunity to bring about bulk scale light manipulation with the potential to realize long-sought proposals in areas such as the solar sail and space transportation driven directly by sunlight.

  20. Application of the enabler to nuclear electric propulsion

    SciTech Connect (OSTI)

    Pierce, B.L. (Westinghouse Electric Corporation Advanced Energy Systems P.O Box 158 Madison, PA 15663-0158 (US))

    1991-01-01

    This paper describes a power system concept that provides the electric power for a baseline electric propulsion system for a piloted mission to Mars. A 10-MWe space power system is formed by coupling an Enabler reactor with a simple non-recuperated closed Brayton cycle. The Enabler reactor is a gas-cooled reactor based on proven reactor technology developed under the NERVA/Rover programs. The selected power cycle, which uses a helium-xenon mixture at 1920 K at the turbine inlet, is diagramed and described. The specific mass of the power system over the power range from 5 to 70 MWe is given. The impact of operating life on the specific mass of a 10-MWe system is also shown.

  1. Heavy Vehicle Propulsion Materials: Recent Progress and Future Plans

    SciTech Connect (OSTI)

    D. Ray Johnson; Sidney Diamond

    2001-05-14

    The Heavy Vehicle Propulsion Materials Program provides enabling materials technology for the U.S. DOE Office of Heavy Vehicle Technologies (OHVT). The technical agenda for the program is based on an industry assessment and the technology roadmap for the OHVT. A five-year program plan was published in 2000. Major efforts in the program are materials for diesel engine fuel systems, exhaust aftertreatment, and air handling. Additional efforts include diesel engine valve-train materials, structural components, and thermal management. Advanced materials, including high-temperature metal alloys, intermetallics, cermets, ceramics, amorphous materials, metal- and ceramic-matrix composites, and coatings, are investigated for critical engine applications. Selected technical issues and planned and ongoing projects as well as brief summaries of several technical highlights are given.

  2. Critical technologies for reactors used in nuclear electric propulsion

    SciTech Connect (OSTI)

    Bhattacharyya, S.K. (Argonne National Lab., IL (United States))

    1993-01-01

    Nuclear electric Propulsion (NEP) systems are expected to play a significant role in the exploration and exploitation of space. Unlike nuclear thermal propulsion (NTP) systems in which the hot reactor coolant is directly discharged from nozzles to provide the required thrust, NEP systems include electric power generation and conditioning units that in turn are used to drive electric thrusters. These thrusters accelerate sub atomic particles to produce thrust. The major advantage of NEP systems is the ability to provide very high specific impulses ([approximately]5000 s) that minimize the requirement for propellants. In addition, the power systems used in NEP could pro vide the dual purpose of also providing power for the missions at the destination. This synergism can be exploited in shared development costs. The NEP systems produce significantly lower thrust that NTP systems and are generally more massive. Both systems have their appropriate roles in a balanced space program. The technology development needs of NEP systems differ in many important ways from the development needs for NTP systems because of the significant differences in the operating conditions of the systems. The NEP systems require long-life reactor power systems operating at power levels that are considerably lower than those for NTP systems. In contrast, the operational lifetime of an NEP system (years) is orders of magnitude longer than the operational lifetime of NTP systems (thousands of second). Thus, the critical issue of NEP is survivability and reliable operability for very long times at temperatures that are considerably more modest than the temperatures required for effective NTP operations but generally much higher than those experienced in terrestrial reactors.

  3. The jets of the Vela pulsar

    E-Print Network [OSTI]

    O. Kargaltsev; G. G. Pavlov; M. A. Teter; D. Sanwal

    2003-06-09

    Chandra observations of the Vela pulsar-wind nebula (PWN) have revealed a jet in the direction of the pulsar's proper motion, and a counter-jet in the opposite direction, embedded in diffuse nebular emission. The jet consists of a bright, 8''-long inner jet, between the pulsar and the outer arc, and a dim, curved outer jet that extends up to 100'' in approximately the same direction. From the analysis of thirteen Chandra observations spread over about 2.5 years we found that this outer jet shows particularly strong variability, changing its shape and brightness. We observed bright blobs in the outer jet moving away from the pulsar with apparent speeds (0.3-0.6)c and fading on time-scales of days to weeks. The spectrum of the outer jet fits a power-law model with a photon index of 1.3\\pm0.1. The X-ray emission of the outer jet can be interpreted as synchrotron radiation of ultrarelativistic electrons/positrons. This interpretation allows one to estimate the magnetic field, ~100 microGauss, maximum energy of X-ray emitting electrons, ~2\\times 10^{14} eV, and energy injection rate, ~8\\times 10^{33} erg/s, for the outer jet. In the summed PWN image we see a dim, 2'-long outer counter-jet, which also shows a power-law spectrum with photon ined of 1.2-1.5. Southwest of the jet/counter-jet an extended region of diffuse emission is seen. Relativistic particles responsible for this radiation are apparently supplied by the outer jet.

  4. Jet Dipolarity: Top Tagging with Color Flow

    SciTech Connect (OSTI)

    Hook, Anson; Jankowiak, Martin; /SLAC /Stanford U., Phys. Dept.; Wacker, Jay G.; /SLAC

    2011-08-12

    A new jet observable, dipolarity, is introduced that can distinguish whether a pair of subjets arises from a color singlet source. This observable is incorporated into the HEPTopTagger and is shown to improve discrimination between top jets and QCD jets for moderate to high p{sub T}. The impressive resolution of the ATLAS and CMS detectors means that a typical QCD jet at the LHC deposits energy in {Omicron}(10-100) calorimeter cells. Such fine-grained calorimetry allows for jets to be studied in much greater detail than previously, with sophisticated versions of current techniques making it possible to measure more than just the bulk properties of jets (e.g. event jet multiplicities or jet masses). One goal of the LHC is to employ these techniques to extend the amount of information available from each jet, allowing for a broader probe of the properties of QCD. The past several years have seen significant progress in developing such jet substructure techniques. A number of general purpose tools have been developed, including: (i) top-tagging algorithms designed for use at both lower and higher p{sub T} as well as (ii) jet grooming techniques such as filtering, pruning, and trimming, which are designed to improve jet mass resolution. Jet substructure techniques have also been studied in the context of specific particle searches, where they have been shown to substantially extend the reach of traditional search techniques in a wide variety of scenarios, including for example boosted Higgses, neutral spin-one resonances, searches for supersymmetry, and many others. Despite these many successes, however, there is every reason to expect that there remains room for refinement of jet substructure techniques.

  5. MOA: Magnetic Field Oscillating Amplified Thruster and its Application for Nuclear Electric and Thermal Propulsion

    SciTech Connect (OSTI)

    Frischauf, Norbert [QASAR Technologie(s) GmbH, Johann Gottekgasse 39, A-1230, Vienna (Austria); Hettmer, Manfred; Grassauer, Andreas; Bartusch, Tobias [QASAR Technologie(s) GmbH, Johann Gottekgasse 39, A-1230, Vienna (Austria); Koudelka, Otto [Institute of Communication Networks and Satellite Communication, Graz University of Technology, Inffeldgasse 12/I, A-8010 Graz (Austria)

    2006-07-01

    More than 60 years after the later Nobel laureate Hannes Alfven had published a letter stating that oscillating magnetic fields can accelerate ionised matter via magneto-hydrodynamic interactions in a wave like fashion, the technical implementation of Alfven waves for propulsive purposes has been proposed, patented and examined for the first time by a group of inventors. The name of the concept, utilising Alfven waves to accelerate ionised matter for propulsive purposes, is MOA - Magnetic field Oscillating Amplified thruster. Alfven waves are generated by making use of two coils, one being permanently powered and serving also as magnetic nozzle, the other one being switched on and off in a cyclic way, deforming the field lines of the overall system. It is this deformation that generates Alfven waves, which are in the next step used to transport and compress the propulsive medium, in theory leading to a propulsion system with a much higher performance than any other electric propulsion system. Based on computer simulations, which were conducted to get a first estimate on the performance of the system, MOA is a highly flexible propulsion system, whose performance parameters might easily be adapted, by changing the mass flow and/or the power level. As such the system is capable to deliver a maximum specific impulse of 13116 s (12.87 mN) at a power level of 11.16 kW, using Xe as propellant, but can also be attuned to provide a thrust of 236.5 mN (2411 s) at 6.15 kW of power. While space propulsion is expected to be the prime application for MOA and is supported by numerous applications such as Solar and/or Nuclear Electric Propulsion or even as an 'afterburner system' for Nuclear Thermal Propulsion, other terrestrial applications can be thought of as well, making the system highly suited for a common space-terrestrial application research and utilisation strategy. (authors)

  6. 30 JULY 2010 VOL 329 SCIENCE www.sciencemag.org508 CREDITS:(MAIN)NASA/JPL-CALTECH;NASA/JPL

    E-Print Network [OSTI]

    Arizona, University of

    30 JULY 2010 VOL 329 SCIENCE www.sciencemag.org508 NEWSFOCUS CREDITS:(MAIN)NASA/JPL-CALTECH;NASA for such rocks to pass through without exploding. The strange rock was exactly the kind of thing NASA sent, NASA scientists didn't see it until Opportunity had driven 200 meters beyond it. They hit reverse

  7. 9Dr. Gregory A. Dorais, NASA Ames Research Center Dr. David Kortenkamp, NASA Johnson Space Center Human-Centered

    E-Print Network [OSTI]

    Kortenkamp, David

    9Dr. Gregory A. Dorais, NASA Ames Research Center Dr. David Kortenkamp, NASA Johnson Space Center-based Reasoning Related WorkRelated Work #12;10Dr. Gregory A. Dorais, NASA Ames Research Center Dr. David Kortenkamp, NASA Johnson Space Center Autonomous Control SystemsAutonomous Control Systems l Brings to table

  8. Nonlinear Dynamics of Coiling in Viscoelastic Jets

    E-Print Network [OSTI]

    Trushant Majmudar; Matthieu Varagnat; William Hartt; Gareth McKinley

    2010-12-09

    Instabilities in free surface continuous jets of non-Newtonian fluids, although relevant for many industrial processes, remain less well understood in terms of fundamental fluid dynamics. Inviscid, and viscous Newtonian jets have been studied in great detail; buckling instability in viscous jets leads to regular periodic coiling of the jet that exhibits a non-trivial frequency dependence with the height of the fall. Very few experimental or theoretical studies exist for continuous viscoelastic jets beyond the onset of the first instability. Here, we present a systematic study of the effects of viscoelasticity on the dynamics of free surface continuous jets of surfactant solutions that form worm-like micelles. We observe complex nonlinear spatio-temporal dynamics of the jet and uncover a transition from periodic to doubly-periodic or quasi-periodic to a multi-frequency, possibly chaotic dynamics. Beyond this regime, the jet dynamics smoothly crosses over to exhibit the "leaping shampoo effect" or the Kaye effect. This enables us to view seemingly disparate jetting dynamics as one coherent picture of successive instabilities and transitions between them. We identify the relevant scaling variables as the dimensionless height, flow rate, and the elasto-gravity number and present a regime map of the dynamics of the jet in terms of these parameters.

  9. QCD resummation for light-particle jets

    E-Print Network [OSTI]

    Hsiang-nan Li; Zhao Li; C. -P. Yuan

    2013-04-08

    We construct an evolution equation for the invariant-mass distribution of light-quark and gluon jets in the framework of QCD resummation. The solution of the evolution equation exhibits a behavior consistent with Tevatron CDF data: the jet distribution vanishes in the small invariant-mass limit, and its peak moves toward the high invariant-mass region with the jet energy. We also construct an evolution equation for the energy profile of the light-quark and gluon jets in the similar framework. The solution shows that the energy accumulates faster within a light-quark jet cone than within a gluon jet cone. The jet energy profile convoluted with hard scattering and parton distribution functions matches well with the Tevatron CDF and the large-hadron-collider (LHC) CMS data. Moreover, comparison with the CDF and CMS data implies that jets with large (small) transverse momentum are mainly composed of the light-quark (gluon) jets. At last, we discuss the application of the above solutions for the light-particle jets to the identification of highly-boosted heavy particles produced at LHC.

  10. JOURNAL OF PROPULSION AND POWER Vol. 22, No. 2, MarchApril 2006

    E-Print Network [OSTI]

    Thole, Karen A.

    to predict. The interaction of jets-in-crossflow, which is representative of film cooling, results in a shear is highly dependent on the jet-to-crossflow mass and momentum flux ratios. Film-cooling performance

  11. Advanced Thermally Stable Jet Fuels

    SciTech Connect (OSTI)

    A. Boehman; C. Song; H. H. Schobert; M. M. Coleman; P. G. Hatcher; S. Eser

    1998-01-01

    The Penn State program in advanced thermally stable jet fuels has five components: 1) development of mechanisms of degradation and solids formation; 2) quantitative measurement of growth of sub-micrometer and micrometer-sized particles during thermal stressing; 3) characterization of carbonaceous deposits by various instrumental and microscopic methods; 4) elucidation of the role of additives in retarding the formation of carbonaceous solids; and 5) assessment of the potential of producing high yields of cycloalkanes and hydroaromatics from coal.

  12. Fluid jet electric discharge source

    DOE Patents [OSTI]

    Bender, Howard A. (Ripon, CA)

    2006-04-25

    A fluid jet or filament source and a pair of coaxial high voltage electrodes, in combination, comprise an electrical discharge system to produce radiation and, in particular, EUV radiation. The fluid jet source is composed of at least two serially connected reservoirs, a first reservoir into which a fluid, that can be either a liquid or a gas, can be fed at some pressure higher than atmospheric and a second reservoir maintained at a lower pressure than the first. The fluid is allowed to expand through an aperture into a high vacuum region between a pair of coaxial electrodes. This second expansion produces a narrow well-directed fluid jet whose size is dependent on the size and configuration of the apertures and the pressure used in the reservoir. At some time during the flow of the fluid filament, a high voltage pulse is applied to the electrodes to excite the fluid to form a plasma which provides the desired radiation; the wavelength of the radiation being determined by the composition of the fluid.

  13. VELOCITY FIELD OF A ROUND TURBULENT TRANSVERSE JET Suman Muppidi

    E-Print Network [OSTI]

    Mahesh, Krishnan

    - bulent jet in a laminar crossflow. The velocity ratio is 5.7 and the Reynolds number is 5000. Mean Jets in crossflow, also called `transverse jets' are defined as the flow field where a jet of fluid enters and interacts with a crossflowing fluid. Examples of jets in crossflow are fuel injectors

  14. CDF/PHYS/JET/PUBLIC/7898 Page 1 of 12

    E-Print Network [OSTI]

    Field, Richard

    CDF/PHYS/JET/PUBLIC/7898 Page 1 of 12 Jet Physics and the Underlying Event at the Tevatron Rick, Florida, 32611, USA Abstract: Tevatron Run 2 results on the inclusive jet cross section (MidPoint and KT algorithm) and the b-jet and bb ­jet cross section (MidPoint algorithm) are presented and compared

  15. CDF/PUB/JET/PUBLIC/7728 Page 1 of 6

    E-Print Network [OSTI]

    Field, Richard

    CDF/PUB/JET/PUBLIC/7728 Page 1 of 6 JET PHYSICS IN RUN 2 AT CDF Rick Field1 (for the CDF Run 2 results on the inclusive jet cross section (KT algorithm) and the b-jet cross section (Mid the direction of the leading jet to isolate regions of - space that are very sensitive to the "beam

  16. In Situ Jet Energy Calibration In Atlas Based On

    E-Print Network [OSTI]

    Hupkes, Hermen Jan

    In Situ Jet Energy Calibration In Atlas Based On Z+Jet Events By Hermen Jan Hupkes 252 Ge; IN SITU JET ENERGY CALIBRATION IN ATLAS BASED ON Z+JET EVENTS Hermen Jan Hupkes Mathematisch Instituut #12; #12; Contents 1 Introduction 1 2 The Atlas Detector 7 3 Jet Measurements in Atlas 11 3

  17. In Situ Jet Energy Calibration In Atlas Based On

    E-Print Network [OSTI]

    Hupkes, Hermen Jan

    In Situ Jet Energy Calibration In Atlas Based On Z+Jet Events By Hermen Jan Hupkes 252 Ge SITU JET ENERGY CALIBRATION IN ATLAS BASED ON Z+JET EVENTS Hermen Jan Hupkes Mathematisch Instituut #12;#12;Contents 1 Introduction 1 2 The Atlas Detector 7 3 Jet Measurements in Atlas 11 3

  18. The design and feasibility of a 10 mN chemical space propulsion thruster

    E-Print Network [OSTI]

    Bruccoleri, Alexander Robert

    2009-01-01

    This thesis discusses the design of a ten milli Newton chemical propulsion system for providing approximately 200 m/s delta velocity to a five kg satellite. The nozzle is the focus of the experimental work, which involves ...

  19. Definition, Expansion and Screening of Architectures for Planetary Exploration Class Nuclear Electric Propulsion and Power Systems

    E-Print Network [OSTI]

    Definition, Expansion and Screening of Architectures for Planetary Exploration Class Nuclear, expansion and screening of Nuclear Electric Propulsion and Power concepts capable of achieving planetary left blank 2 #12;Definition, Expansion and Screening of Architectures for Planetary Exploration Class

  20. Vehicle Technologies Office: 2013 Propulsion Materials R&D Annual Progress Report

    Broader source: Energy.gov [DOE]

    This report describes the progress made during 2013 on the research and development projects funded by the Propulsion Materials subprogram in the Vehicle Technologies Office. Past year's reports are listed on the Annual Progress Reports page.

  1. Underwater Propulsion at Intermediate Re: Comparative Analyses of a Marine Pteropod and a Freshwater Cladoceran

    E-Print Network [OSTI]

    Underwater Propulsion at Intermediate Re: Comparative Analyses of a Marine Pteropod of Mechanical Engineering, Johns Hopkins University Introduction Results: Flow Fields Objective Methods. Pteropods stroke flexible wings in a complicated pattern to swim with a smoother, more fluid motion. Goal

  2. Fabrication and characterization of sintered porous glass emitters for electrospray propulsion

    E-Print Network [OSTI]

    Xie, Julie

    2014-01-01

    Ionic electrospray thrusters are promising candidates for CubeSat propulsion systems in space, due to their low power requirement and small form factor. Current technology has demonstrated thrust levels of 10 - 40[mu]N, ...

  3. Submarine propulsion shaft life : probabilistic prediction and extension through prevention of water ingress

    E-Print Network [OSTI]

    Jonart, Douglas E. (Douglas Edward)

    2014-01-01

    Submarine propulsion shafts have demonstrated acceptable reliability performance when inspected and refurbished at least every 6 years. Designers wish to extend the inspection interval to 12 years without sacrificing ...

  4. An impulse framework for hydrodynamic force analysis : fish propulsion, water entry of spheres, and marine propellers

    E-Print Network [OSTI]

    Epps, Brenden P

    2010-01-01

    This thesis presents an impulse framework for analyzing the hydrodynamic forces on bodies in flow. This general theoretical framework is widely applicable, and it is used to address the hydrodynamics of fish propulsion, ...

  5. A fully microfabricated two-dimensional electrospray array with applications to space propulsion

    E-Print Network [OSTI]

    Gassend, Blaise L. P. (Blaise Laurent Patrick), 1978-

    2007-01-01

    This thesis presents the design, fabrication and testing of a fully-integrated planar electrospray thruster array, which could lead to more efficient and precise thrusters for space propulsion applications. The same ...

  6. Importance of Nuclear DataImportance of Nuclear Data to the Naval Nuclear Propulsion Program

    E-Print Network [OSTI]

    Danon, Yaron

    Importance of Nuclear DataImportance of Nuclear Data to the Naval Nuclear Propulsion Program Don of Evaluated Criticality Safety Benchmark Experiments," NEA/NSC/DOC(95)03, 2009. #12;MC21 Analysis of LEU COMP

  7. Turbulent fluid jet excavation in cohesive soil : with particular application to jet grouting

    E-Print Network [OSTI]

    Ho, Chu Eu

    2005-01-01

    This thesis reviews the jet grouting methodology, and the current state of practice and research. Current methods of prediction of jet grout diameters are highly empirical and site specific, and do not take into account ...

  8. Studies of jet mass in dijet and W/Z + jet events

    E-Print Network [OSTI]

    Baringer, Philip S.; Bean, Alice; Benelli, Gabriele; Kenny, R. P. III; Murray, Michael J.; Noonan, Danny; Sanders, Stephen J.; Stringer, Robert W.; Tinti, Gemma; Wood, Jeffrey Scott; Chatrchyan, S.; Khachatryan, V.; Sirunyan, A. M.; Tumasyan, A.; Adam, W.; Aguilo, E.; Bergauer, T.

    2013-05-17

    Invariant mass spectra for jets reconstructed using the anti-k T and CambridgeAachen algorithms are studied for different jet “grooming” techniques in data corresponding to an integrated luminosity of 5 fb(?1), recorded with the CMS detector...

  9. Radio polarization study in protostellar jet

    E-Print Network [OSTI]

    Cécere, Mariana; Araudo, Anabella T; De Colle, Fabio; Esquivel, Alejandro; Carrasco-González, Carlos; Rodríguez, Luis F

    2015-01-01

    Synchrotron radiation is commonly observed associated with shocks of different velocities, ranging from relativistic shocks associated with, e.g., active galactic nuclei, gamma-ray bursts or microquasars to weakly- or non-relativistic flows as those observed e.g. in supernovae and supernova remnants. Recent observations of polarization in protostellar jets are important not only because they extend the range over which the acceleration process works, but also because they allow to measure directly the jet and interstellar magnetic field structure and intensity, thus giving insights on the jet ejection mechanism itself. In this paper, we compute for the first time polarized (synchrotron) and non polarized (thermal-X-ray) synthetic emission maps from axisymmetrical simulations of magnetized protostellar jets. We consider models with different jet velocities and variability, as well as models with toroidal or helical magnetic field. Our simulations show that variable, low-density jets with velocities ~ 1000km/s ...

  10. Jet impact on a soap film

    E-Print Network [OSTI]

    Geoffroy Kirstetter; Christophe Raufaste; Franck Celestini

    2012-08-17

    We experimentally investigate the impact of a liquid jet on a soap film. We observe that the jet never breaks the film and that two qualitatively different steady regimes may occur. The first one is a refraction-like behavior obtained at small incidence angles when the jet crosses the film and is deflected by the film-jet interaction. For larger incidence angles, the jet is absorbed by the film, giving rise to a new class of flow in which the jet undulates along the film with a characteristic wavelength. Besides its fundamental interest, this study presents a new way to guide a micro-metric flow of liquid in the inertial regime and to probe foam stability submitted to violent perturbations at the soap film scale.

  11. Experimental treatment of Quark and Gluon Jets

    E-Print Network [OSTI]

    Sona Pochybova

    2011-07-01

    The separate study of quark and gluon jets is vital for the interpretation of multiple variables behaviour observed in both high-energy hadron and heavy-ion collisions in the present and future experiments. We propose a set of jet-energy dependent cuts to be used to distinguish between quark and gluon jets experimentally based on a Monte-Carlo study of their properties. Further, we introduce the possibility to calibrate these cuts via gamma-jet and multi-jet events, which represent clean production channels for quark and gluon jets, respectively. The calibration can happen on real data and thus, reduces the dependence of the method performance on Monte-Carlo model predictions.

  12. Magnetic Propulsion of Intense Lithium Streams in a Tokamak Magnetic Field

    SciTech Connect (OSTI)

    Leonid E. Zakharov

    2002-03-13

    The paper gives the theory of magnetic propulsion of liquid lithium streams and their stability in tokamaks. In the approximation of a thin flowing layer the MHD equations are reduced to one integro-differential equation which takes into account the propulsion effect, viscosity and the drag force due to magnetic pumping and other interactions with the magnetic field. A criterion is obtained for the stabilization of the ''sausage'' instability of the streams by centrifugal force.

  13. Propulsion of a molecular machine by asymmetric distribution of reaction--products

    E-Print Network [OSTI]

    Ramin Golestanian; Tanniemola B. Liverpool; Armand Ajdari

    2007-01-09

    A simple model for the reaction-driven propulsion of a small device is proposed as a model for (part of) a molecular machine in aqueous media. Motion of the device is driven by an asymmetric distribution of reaction products. The propulsive velocity of the device is calculated as well as the scale of the velocity fluctuations. The effects of hydrodynamic flow as well as a number of different scenarios for the kinetics of the reaction are addressed.

  14. Coupling of twin rectangular supersonic jets

    E-Print Network [OSTI]

    Raman, G.; Taghavi, Ray

    1998-01-01

    J. Fluid Mech. (1998), vol. 354, pp. 123{146. Printed in the United Kingdom c? 1998 Cambridge University Press 123 Coupling of twin rectangular supersonic jets By GANESH RAMAN 1 AND RAY TAGHAVI 2 1 NYMA, Inc., Experimental Fluid Dynamics Section... on twin supersonic jets that screech at a discrete frequency. The present fundamental research program on twin-jet coupling was undertaken to resolve numerous issues underlined by Tam & Seiner (1987), and Morris (1990). Tam & Seiner (1987) pointed...

  15. Nonlinear compressions in merging plasma jets

    SciTech Connect (OSTI)

    Messer, S.; Case, A.; Wu, L.; Brockington, S.; Witherspoon, F. D.

    2013-03-15

    We investigate the dynamics of merging supersonic plasma jets using an analytic model. The merging structures exhibit supersonic, nonlinear compressions which may steepen into full shocks. We estimate the distance necessary to form such shocks and the resulting jump conditions. These theoretical models are compared to experimental observations and simulated dynamics. We also use those models to extrapolate behavior of the jet-merging compressions in a Plasma Jet Magneto-Inertial Fusion reactor.

  16. Jets, frames, and their Cartan geometry

    E-Print Network [OSTI]

    Michael Grasseau

    2006-03-24

    Jets frames, that is a generalisation of ordinary frames on a manifold, are described in a language similar to that of gauge theory. This is achieved by constructing the Cartan geometry of a manifold with respect to the diffeomorphism symmetry. This point of vue allows to give new insights and interpretations in the theory of jet frames, in particular by making an interpolation between ordinary gauge theory concepts and pure jet ones.

  17. In-Medium Properties of Jets

    E-Print Network [OSTI]

    Fuqiang Wang

    2007-07-05

    Modifications of jet-like azimuthal correlations have revealed novel properties of the medium created in relativistic heavy-ion collisions. Experimental results on jet-like 2- and 3-particle correlations, specificly "punch-through" at high transverse momentum, broadening at low and modest transverse momentum, and particularly the possible experimental evidence for conical flow, are reviewed. Future prospects of jet-like correlations and their physics potential are discussed.

  18. Simple scaling laws for astrophysical jets

    E-Print Network [OSTI]

    M. Huarte-Espinosa; S. Mendoza

    2006-07-15

    The idea of a unified model for all astrophysical jets has been considered for quite some time. We present here a few scaling laws relevant to all type of astrophysical jets, analogous to those of \\citet{sams96} which are widely used for astrophysical black holes. We use Buckingham's $ \\Pi $ theorem of dimensional analysis to obtain a family of dimensional relations among the physical quantities associated to astrophysical jets.

  19. Influence of eddydriven jet latitude on North Atlantic jet persistence and blocking frequency in CMIP3 integrations

    E-Print Network [OSTI]

    Hartmann, Dennis

    Influence of eddydriven jet latitude on North Atlantic jet persistence and blocking frequency Atlantic jet latitude is analyzed in 45 CMIP3 integrations. It is demonstrated that models that place the jet equatorward of its observed position have more positively skewed jet latitude distributions, while

  20. Increasing jet entrainment, mixing and spreading

    DOE Patents [OSTI]

    Farrington, R.B.

    1994-08-16

    A free jet of air is disturbed at a frequency that substantially matches natural turbulences in the free jet to increase the entrainment, mixing, and spreading of air by the free jet, for example in a room or other enclosure. The disturbances are created by pulsing the flow of air that creates the free jet at the desired frequency. Such pulsing of the flow of air can be accomplished by sequentially occluding and opening a duct that confines and directs the flow of air, such as by rotating a disk on an axis transverse to the flow of air in the duct. 11 figs.

  1. Jet energy calibration at the LHC

    E-Print Network [OSTI]

    Schwartzman, Ariel

    2015-01-01

    Jets are one of the most prominent physics signatures of high energy proton proton (p-p) collisions at the Large Hadron Collider (LHC). They are key physics objects for precision measurements and searches for new phenomena. This review provides an overview of the reconstruction and calibration of jets at the LHC during its first Run. ATLAS and CMS developed different approaches for the reconstruction of jets, but use similar methods for the energy calibration. ATLAS reconstructs jets utilizing input signals from their calorimeters and use charged particle tracks to refine their energy measurement and suppress the effects of multiple p-p interactions (pileup). CMS, instead, combines calorimeter and tracking information to build jets from particle flow objects. Jets are calibrated using Monte Carlo (MC) simulations and a residual in situ calibration derived from collision data is applied to correct for the differences in jet response between data and Monte Carlo. Large samples of dijet, Z+jets, and photon+jet e...

  2. LO, NLO, LO* and jet algorithms

    E-Print Network [OSTI]

    J. Huston

    2010-01-14

    The impact of NLO corrections, and in particular, the role of jet algorithms, is examined for a variety of processes at the Tevatron and LHC.

  3. Jet substructures of boosted polarized top quarks

    E-Print Network [OSTI]

    Yoshio Kitadono; Hsiang-nan Li

    2014-09-05

    We study jet substructures of a boosted polarized top quark, which undergoes the semileptonic decay $t\\to b\\ell\

  4. Observable jets from the BFKL chain

    E-Print Network [OSTI]

    J. Kwiecinski; C. A. M. Lewis; A. D. Martin

    1996-06-19

    We derive a modified form of the BFKL equation which enables the structure of the gluon emissions to be studied in small $x$ deep inelastic scattering. The equation incorporates the resummation of the virtual and unresolved real gluon emissions. We solve the equation to calculate the number of small $x$ deep-inelastic events containing 0,1,2 ...resolved gluon jets, that is jets with transverse momenta $q_{T} > \\mu$. We study the jet decomposition for different choices of the jet resolution parameter $\\mu$.

  5. Increasing jet entrainment, mixing and spreading

    DOE Patents [OSTI]

    Farrington, Robert B. (Wheatridge, CO)

    1994-01-01

    A free jet of air is disturbed at a frequency that substantially matches natural turbulences in the free jet to increase the entrainment, mixing, and spreading of air by the free jet, for example in a room or other enclosure. The disturbances are created by pulsing the flow of air that creates the free jet at the desired frequency. Such pulsing of the flow of air can be accomplished by sequentially occluding and opening a duct that confines and directs the flow of air, such as by rotating a disk on an axis transverse to the flow of air in the duct.

  6. PHYSICAL PARAMETERS OF STANDARD AND BLOWOUT JETS

    SciTech Connect (OSTI)

    Pucci, Stefano; Romoli, Marco; Poletto, Giannina; Sterling, Alphonse C.

    2013-10-10

    The X-ray Telescope on board the Hinode mission revealed the occurrence, in polar coronal holes, of much more numerous jets than previously indicated by the Yohkoh/Soft X-ray Telescope. These plasma ejections can be of two types, depending on whether they fit the standard reconnection scenario for coronal jets or if they include a blowout-like eruption. In this work, we analyze two jets, one standard and one blowout, that have been observed by the Hinode and STEREO experiments. We aim to infer differences in the physical parameters that correspond to the different morphologies of the events. To this end, we adopt spectroscopic techniques and determine the profiles of the plasma temperature, density, and outflow speed versus time and position along the jets. The blowout jet has a higher outflow speed, a marginally higher temperature, and is rooted in a stronger magnetic field region than the standard event. Our data provide evidence for recursively occurring reconnection episodes within both the standard and the blowout jet, pointing either to bursty reconnection or to reconnection occurring at different locations over the jet lifetimes. We make a crude estimate of the energy budget of the two jets and show how energy is partitioned among different forms. Also, we show that the magnetic energy that feeds the blowout jet is a factor of 10 higher than the magnetic energy that fuels the standard event.

  7. Experimental Investigation of Jet Mixing of a Co-Flow Jet Airfoil

    E-Print Network [OSTI]

    Zha, Gecheng

    role in mixing the CFJ with mainflow to transport high kinetic energy from the jet to mainflow so-barrier discharge plasma actuators [9, 10]. However, at present, both ZNMF synthetic jets and plasma actuators net mass flux m Jet mass flow rate u,v,w Velocity components in x-, y-, and z-direction V Velocity

  8. Drying characteristics of slot jet reattachment nozzle and comparison with a slot jet nozzle 

    E-Print Network [OSTI]

    Alam, Syed Aftab

    1998-01-01

    Slot Jet Reattachment (SJR) nozzle is an extension of hics.the Radial Jet Reattachment (RJR) concept used to provide high heat and mass transfer while allowing for the control of flow exerted force on the reattachment surface. The SJR is a slot jet...

  9. Detailed characterization of jets in heavy ion collisions using jet fragmentation functions

    E-Print Network [OSTI]

    Ma, Frank Teng

    2013-01-01

    In this thesis the jet fragmentation function of inclusive jets with transverse momentum PT > 100 GeV/c in PbPb collisions is measured for reconstructed charged particles with PT > 1 GeV/c within the jet cone. A data sample ...

  10. Numerical investigation of a transient free jet resembling a laser-produced vapor jet

    E-Print Network [OSTI]

    Budair, Mohammed Omar

    Numerical investigation of a transient free jet resembling a laser-produced vapor jet G.M. Arshed, S.Z. Shuja, B.S. Yilbas *, M.O. Budair Department of Mechanical Engineering, King Fahd University in revised form 29 July 2003 Abstract In the present study, the transiently developing free jet emanating

  11. 21Dr. Gregory A. Dorais, NASA Ames Research Center Dr. David Kortenkamp, NASA Johnson Space Center Design of AA systemsDesign of AA systems

    E-Print Network [OSTI]

    Kortenkamp, David

    21Dr. Gregory A. Dorais, NASA Ames Research Center Dr. David Kortenkamp, NASA Johnson Space Center in autonomy #12;22Dr. Gregory A. Dorais, NASA Ames Research Center Dr. David Kortenkamp, NASA Johnson Space, NASA Ames Research Center Dr. David Kortenkamp, NASA Johnson Space Center Generic control system

  12. www.nasa.gov Strategic Plan

    E-Print Network [OSTI]

    Waliser, Duane E.

    , and engineers. (Credit: NASA/C. Huston) Our heavy-lift rover Tri-ATHLETE, or All-Terrain Hex-Legged Extra activity as construction and maintenance continue on the International Space Station. Aerospace engineer­Urbana Champaign partnered with Glenn to test the model with micro-array flow control to try to alleviate

  13. Project Management in NASA Mars Climate Orbiter

    E-Print Network [OSTI]

    Rhoads, James

    by the Mars Climate Orbiter Mishap Investigation Board F. Recurring Themes From Failure Investigations and Control Center Navigation and Control Center Goddard Space Flight Center Goddard Space Flight Center Merwarth NASA/GSFC-retired Expert in ground operations & flight software development Moshe F. Rubinstein

  14. NASA Fact Sheet Spacecraft Power for Cassini

    E-Print Network [OSTI]

    , compact spacecraft power systems that are extraordinarily reli- able. RTGs are not nuclear reactors with accidents at nuclear power plants. It is completely inaccurate to associate an RTG accident with ChernobylNASA Fact Sheet July 1999 Spacecraft Power for Cassini Cassini's electrical power source -- Radio

  15. Diffusiophoretic Self-Propulsion for Partially Catalytic Spherical Colloids

    E-Print Network [OSTI]

    Joost de Graaf; Georg Rempfer; Christian Holm

    2015-02-11

    Colloidal spheres with a partial platinum surface coating perform auto-phoretic motion when suspended in hydrogen peroxide solution. We present a theoretical analysis of the self-propulsion velocity of these particles using a continuum multi-component, self-diffusiophoretic model. With this model as a basis, we show how the slip-layer approximation can be derived and in which limits it holds. First, we consider the differences between the full multi-component model and the slip-layer approximation. Then the slip model is used to demonstrate and explore the sensitive nature of the particle's velocity on the details of the molecule-surface interaction. We find a strong asymmetry in the dependence of the colloid's velocity as a function of the level of catalytic coating, when there is a different interaction between the solute and solvent molecules and the inert and catalytic part of the colloid, respectively. The direction of motion can even be reversed by varying the level of the catalytic coating. Finally, we investigate the robustness of these results with respect to variations in the reaction rate near the edge between the catalytic and inert parts of the particle. Our results are of significant interest to the interpretation of experimental results on the motion of self-propelled particles.

  16. Assessment of a hot hydrogen nuclear propulsion fuel test facility

    SciTech Connect (OSTI)

    Watanabe, H.H.; Howe, S.D.; Wantuck, P.J.

    1991-01-01

    Subsequent to the announcement of the Space Exploration Initiative (SEI), several studies and review groups have identified nuclear thermal propulsion as a high priority technology for development. To achieve the goals of SEI to place man on Mars, a nuclear rocket will operate at near 2700K and in a hydrogen environment at near 60 atmospheres. Under these conditions, the operational lifetime of the rocket will be limited by the corrosion rate at the hydrogen/fuel interface. Consequently, the Los Alamos National Laboratory has been evaluating requirements and design issues for a test facility. The facility will be able to directly heat fuel samples by electrical resistance, microwave deposition, or radio frequency induction heating to temperatures near 3000K. Hydrogen gas at variable pressure and temperatures will flow through the samples. The thermal gradients, power density, and operating times envisioned for nuclear rockets will be duplicated as close as reasonable. The post-sample flow stream will then be scrubbed and cooled before reprocessing. The baseline design and timetable for the facility will be discussed. 7 refs.

  17. Convectively generated zonal jets by thunderstorms on Jupiter

    E-Print Network [OSTI]

    Zhang, Xi Arthur; Showman, Adam

    2011-01-01

    which assumes the jet streams are the weather pattern con?is adopted to simulate the jet streams, espe- cially theThe wind direction of jet stream is alternating with

  18. Images in Emergency Medicine: Irritant Contact Dermatitis from Jet Fuel

    E-Print Network [OSTI]

    Trigger, Christopher C; Eilbert, Wesley

    2009-01-01

    and penetration of JP-8 jet fuel and its components. ToxicolContact Dermatitis from Jet Fuel Christopher C. Trigger, MDday. He reported spilling jet fuel on his right lower leg at

  19. MHD jet propagation in the case of DG Tau

    E-Print Network [OSTI]

    Vaidya, Bhargav; Rubini, Francesco; de Colle, Fabio

    2010-01-01

    of art telescopes. Usually jets are observed in forbiddenlike SII, OII etc. One of the jet studied in great detailsis the DG Tau jet. (Lavalley-Fouquet et al. (2000), Dougados

  20. Jet Schemes and Truncated Wedge Schemes Cornelia O. Yuen

    E-Print Network [OSTI]

    Smith, Karen E.

    Jet Schemes and Truncated Wedge Schemes by Cornelia O. Yuen A dissertation submitted in partial of jets and arcs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 1.2 A higher dimension analog of arcs and jets . . . . . . . . . . . . . . . . . . . 3 1.3 History

  1. Jet maximization, axis minimization, and stable cone finding

    E-Print Network [OSTI]

    Thaler, Jesse

    Jet finding is a type of optimization problem, where hadrons from a high-energy collision event are grouped into jets based on a clustering criterion. As three interesting examples, one can form a jet cluster that (i) optimizes ...

  2. Effective Field Theory Techniques for Resummation in Jet Physics

    E-Print Network [OSTI]

    Dunn, Nicholas Daniel

    2012-01-01

    QCD corrections to WW+jet production at hadron colliders.al. Substructure of high-p T Jets at the LHC. Phys. Rev. ,decorrelations between QCD jets at all orders. Phys.Lett. ,

  3. Quark Matter 2006: High-pt and jets

    E-Print Network [OSTI]

    van Leeuwen, Marco

    2007-01-01

    Quark Matter 2006: High-p T and jets M van Leeuwen LawrenceT particle production and jets in heavy ion collisions fromp T particle production and jet-like correlations from Quark

  4. JETS OF NUCLEAR MATTER FROM HIGH ENERGY HEAVY ION COLLISIONS

    E-Print Network [OSTI]

    Stocker, H.

    2013-01-01

    be published. Table 1: The jet angle, ejet' relative to theof California. LBL~ll774 Jets of Nuclear Matter from Highreactions. Strongly correlated jets of nuclear matter are

  5. Systemsize dependence of associated yields in hadron-triggered jets

    E-Print Network [OSTI]

    Abelev, Betty

    2010-01-01

    in hadron-triggered jets B.I.Abelev (STARCollaboration)yields in hadron-triggered jets B. I. Abelev 8 , M. M.+Au collisions reveal similar jet-like correlation yields at

  6. Earth Science Educational and Informational Products

    E-Print Network [OSTI]

    Earth Science Educational and Informational Products Electronic Availability Videocassette CD Earth is our home, we still have much to discover about it. At NASA's Jet Propulsion Laboratory, we planet. Visit Earth at: http://www.jpl.nasa.gov/earth JPL offers many products and programs

  7. Multi-robot Simultaneous Localization and Mapping using Particle Filters

    E-Print Network [OSTI]

    Del Moral , Pierre

    Multi-robot Simultaneous Localization and Mapping using Particle Filters Andrew Howard NASA Jet Propulsion Laboratory Pasadena, California 91109, U.S.A. Email: abhoward@robotics.jpl.nasa.gov Abstract-- This paper describes an on-line algorithm for multi- robot simultaneous localization and mapping (SLAM). We

  8. Phoenix Landing Mission to the Martian Polar North

    E-Print Network [OSTI]

    Kounaves, Samuel P.

    Phoenix Landing Mission to the Martian Polar North Press Kit/MAY 2008 #12;#12;Media Contacts Dwayne Phoenix Mars Lander Mission 818-354-5011 Jet Propulsion Laboratory guy.webster@jpl.nasa.gov Pasadena Channel, access to NASA TV's Public Channel on the Web and a schedule of programming for Phoenix Mars

  9. Asymmetric Supernovae from Magneto-Centrifugal Jets

    E-Print Network [OSTI]

    J. Craig Wheeler; David L. Meier; James R. Wilson

    2001-12-02

    Strong toroidal magnetic fields generated in stellar collapse can generate magneto-centrifugal jets in analogy to those found in simulations of black hole accretion and explain why all core collapse supernovae are found to be substantially asymmetric and predominantly bi-polar. We describe two phases: the initial LeBlanc-Wilson jet and a subsequent protopulsar or toroidal jet that propagates at about the core escape velocity. The jets will produce bow shocks that tend to expel matter, including iron and silicon, into equatorial tori, accounting for observations of the element distribution in Cas A. A magnetic ``switch'' mechanism may apply in instances of low density and large magnetic field with subsequent increase in the speed and collimation of the toroidal jet, depositing relatively little momentum. The result could be enough infall to form a black hole with a third, highly relativistic jet that could catch up to the protopulsar jet after it has emerged from the star. The interaction of these two jets could generate internal shocks and explain the presence of iron lines in the afterglow. Recent estimates that typical gamma-ray burst energy is about 3x10^50 erg imply either a very low efficiency for conversion of rotation into jets, or a rather rapid turnoff of the jet process even though the black hole still rotates rapidly. Magnetars and ``hypernovae'' might arise in an intermediate parameter regime of energetic jets that yield larger magnetic fields and provide more energy than the routine case, but that are not so tightly collimated that they yield failed supernova. (slightly abridged)

  10. Why Do Disks Form Jets?

    E-Print Network [OSTI]

    D Lynden-Bell

    2002-03-27

    It is argued that jet modelers have given insufficient study to the natural magneto-static configurations of field wound up in the presence of a confining general pressure. Such fields form towers whose height grows with each twist at a velocity comparable to the circular velocity of the accretion disk that turns them. A discussion of the generation of such towers is preceded by a brief history of the idea that quasars, active galaxies, and galactic nuclei contain giant black holes with accretion disks.

  11. NASA's Marshall Space Flight Center Improves Cooling System Performanc...

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

    The program saved the facility more than 800,000 gallons of water in eight months. nasa-msfcwatercs2.pdf More Documents & Publications NASA's Marshall Space Flight Center...

  12. National Aeronautics and Space Administration www.nasa.gov

    E-Print Network [OSTI]

    Christian, Eric

    National Aeronautics and Space Administration www.nasa.gov Volume 2 Issue 15 August 2006 Goddard Prize Pg 7 National Aeronautics and Space Administration www.nasa.gov Volume 2 Issue 15 August 2006 #12

  13. National Aeronautics and Space Administration www.nasa.gov

    E-Print Network [OSTI]

    Christian, Eric

    National Aeronautics and Space Administration www.nasa.gov Volume 2 Issue 17 September 2006 GoddardView National Aeronautics and Space Administration www.nasa.gov Volume 2 Issue 17 September 2006 Earth

  14. National Aeronautics and Space Administration www.nasa.gov

    E-Print Network [OSTI]

    Christian, Eric

    National Aeronautics and Space Administration www.nasa.gov Volume 3 Issue 6 April 2007 GoddardView National Aeronautics and Space Administration www.nasa.gov Volume 3 Issue 6 April 2007 Deep Impact Extended

  15. Electrocodeposition of nanoparticle composite films using an impinging jet electrode

    E-Print Network [OSTI]

    Osborne, Steven J.

    2006-01-01

    Particles by Jet Electroplating,” Materials Transactions,of the Impinging Jet Electroplating System……………………….. 3.1Design………………………………………….. 3.5 Electroplating Cell

  16. Interpretation of ageostrophic winds and implications for jet stream maintenance

    E-Print Network [OSTI]

    Wirosoetisno, Djoko

    Interpretation of ageostrophic winds and implications for jet stream maintenance Article Published Version Blackburn, M. (1985) Interpretation of ageostrophic winds and implications for jet stream

  17. Fragmentation, underlying event and jet shapes at the Tevatron...

    Office of Scientific and Technical Information (OSTI)

    Conference: Fragmentation, underlying event and jet shapes at the Tevatron Citation Details In-Document Search Title: Fragmentation, underlying event and jet shapes at the Tevatron...

  18. Boron nitride ablation studies in arc jet facilities (Conference...

    Office of Scientific and Technical Information (OSTI)

    Boron nitride ablation studies in arc jet facilities Citation Details In-Document Search Title: Boron nitride ablation studies in arc jet facilities You are accessing a document...

  19. MEASUREMENTS OF JET VELOCITY IN UNSTRATIFIED AND STRATIFIED FLUIDS

    E-Print Network [OSTI]

    in Civil Engineering Georgia Institute of Technology February 2000 #12;MEASUREMENTS OF JET VELOCITYMEASUREMENTS OF JET VELOCITY IN UNSTRATIFIED AND STRATIFIED FLUIDS A Thesis Presented

  20. ,/'iV _ .s=J NASA Technical Memorandum 4592

    E-Print Network [OSTI]

    Butler, Ricky W.

    ,/'iV _ .s=J NASA Technical Memorandum 4592 f_ /03 ASSIST User Manual Sally C. Johnson and David P. Boerschlein i i (NASA-TN-4$?2) (NASA. Langley 103 p ASSIST USER MANUAL Research Center) H1162 N95-32250 Unclas 00601'69 August 1995 #12;#12;NASA Technical Memorandum 4592 ASSIST User Manual Sally C. Johnson Langley