skip to main content
OSTI.GOV title logo U.S. Department of Energy
Office of Scientific and Technical Information

Title: RESEARCH ON SPACECRAFT AND POWERPLANT INTEGRATION PROBLEMS. Second Quarterly Report, July 26 to October 26, 1963

Abstract

Major emphasis is on the design of the 1-Mw(e) Rankine cycle powered spacecraft. The heliocentric phases of planetary missions are analyzed and results obtained for Jupiter, Saturn, Uranus, Neptune, and Pluto. Effort is continuing on Mercury heliocentric, out-of-ecliptic, and solar probe trajectories. An interesting result of the heliocentric studies is the reduction of data to a characteristic distance relating mission time, specific impulse, and spacecraft mass ratio. A LEADER program is prepared for use in optimizing spacecraft parameters for selected NAVIGATOR missions. The design study of spacecraft configuration centered about the choice between a deployable and a non-deployable radiator for the 1-Mw(e) turboelectric system. The launch requirements are satisfied by the conical radiator configuration. The radiator weight, primary plus auxiliary cooling, is estimated at 9,800 pounds, which is 9.8 lb/kw(e) and 3.4 lb/ft/sup 2/ of radiating surface, including headers, feeders, structure, and other support items. Preliminary shielding studies indicate that the shield is not a major spacecraft item. Scattering from the radiator to the payload is significant and scatter shielding must be provided. The shield can probably be passively cooled. The electrical system is quite complex because of the many services performed. A first pass circuit diagram is studied. Themore » guidance and control portion of the electrical system consists of using some of the electric thrusters for attitude control. The power generation system is estimated at about 8,000 pounds for a 1-Mw(e) system, exclusive of reactor, shield, and radiators. Thus, the complete powerplant specific weight is around 28 lb/kw input to the electric thrusters or other payload items. The study is centered on the 2600-lb turbogenerator assembly. Electric power and dimensional requirements of various electric thrusters are estimated. The principal state-ofthe-art limitation is electrode erosion, which limits efficiency, size, and weight. Payload weight data are amplified. (auth)« less

Authors:
Publication Date:
Research Org.:
General Electric Co. Missile and Space Div., Valley Forge Space Technology Center, King of Prussia, Penna.
OSTI Identifier:
4121413
Report Number(s):
63SD886
NSA Number:
NSA-18-006510
DOE Contract Number:  
NAS 3-2533
Resource Type:
Technical Report
Resource Relation:
Other Information: Orig. Receipt Date: 31-DEC-64
Country of Publication:
United States
Language:
English
Subject:
REACTOR TECHNOLOGY; CIRCUITS; CONFIGURATION; CONTROL; COOLANT LOOPS; COOLING; CURRENTS; DIAGRAMS; EFFICIENCY; ELECTRICITY; ELECTRODES; ELECTRONIC EQUIPMENT; EROSION; FAILURES; GAS COOLANT; GENERATORS; HEAT EXCHANGERS; JUPITER; MASS; MATERIALS TESTING; MECHANICAL STRUCTURES; MERCURY; NEPTUNE; NEUTRONS; ORBITS; PLANETS; PLANNING; PLUTO; POWER PLANTS; PROPULSION; RADIATION PROTECTION; RANKINE CYCLE; REACTOR CORE; REACTOR SAFETY; RESEARCH REACTORS; ROCKETS; SCATTERING; SHIELDING; SHIELDING MATERIALS; SPACE FLIGHT; SPACE VEHICLES; STANDARDS; SUN; SURFACES; THERMODYNAMICS; TRANSPORT; TURBINES; VELOCITY; VOLUME; WEIGHT

Citation Formats

Larson, J W. RESEARCH ON SPACECRAFT AND POWERPLANT INTEGRATION PROBLEMS. Second Quarterly Report, July 26 to October 26, 1963. United States: N. p., 1964. Web.
Larson, J W. RESEARCH ON SPACECRAFT AND POWERPLANT INTEGRATION PROBLEMS. Second Quarterly Report, July 26 to October 26, 1963. United States.
Larson, J W. Sat . "RESEARCH ON SPACECRAFT AND POWERPLANT INTEGRATION PROBLEMS. Second Quarterly Report, July 26 to October 26, 1963". United States.
@article{osti_4121413,
title = {RESEARCH ON SPACECRAFT AND POWERPLANT INTEGRATION PROBLEMS. Second Quarterly Report, July 26 to October 26, 1963},
author = {Larson, J W},
abstractNote = {Major emphasis is on the design of the 1-Mw(e) Rankine cycle powered spacecraft. The heliocentric phases of planetary missions are analyzed and results obtained for Jupiter, Saturn, Uranus, Neptune, and Pluto. Effort is continuing on Mercury heliocentric, out-of-ecliptic, and solar probe trajectories. An interesting result of the heliocentric studies is the reduction of data to a characteristic distance relating mission time, specific impulse, and spacecraft mass ratio. A LEADER program is prepared for use in optimizing spacecraft parameters for selected NAVIGATOR missions. The design study of spacecraft configuration centered about the choice between a deployable and a non-deployable radiator for the 1-Mw(e) turboelectric system. The launch requirements are satisfied by the conical radiator configuration. The radiator weight, primary plus auxiliary cooling, is estimated at 9,800 pounds, which is 9.8 lb/kw(e) and 3.4 lb/ft/sup 2/ of radiating surface, including headers, feeders, structure, and other support items. Preliminary shielding studies indicate that the shield is not a major spacecraft item. Scattering from the radiator to the payload is significant and scatter shielding must be provided. The shield can probably be passively cooled. The electrical system is quite complex because of the many services performed. A first pass circuit diagram is studied. The guidance and control portion of the electrical system consists of using some of the electric thrusters for attitude control. The power generation system is estimated at about 8,000 pounds for a 1-Mw(e) system, exclusive of reactor, shield, and radiators. Thus, the complete powerplant specific weight is around 28 lb/kw input to the electric thrusters or other payload items. The study is centered on the 2600-lb turbogenerator assembly. Electric power and dimensional requirements of various electric thrusters are estimated. The principal state-ofthe-art limitation is electrode erosion, which limits efficiency, size, and weight. Payload weight data are amplified. (auth)},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {1964},
month = {10}
}

Technical Report:
Other availability
Please see Document Availability for additional information on obtaining the full-text document. Library patrons may search WorldCat to identify libraries that may hold this item. Keep in mind that many technical reports are not cataloged in WorldCat.

Save / Share: