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  • 1
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    Low-thrust chemical propulsion system propellant expulsion and thermal conditioning study (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Thermal conditioning systems for satisfying engine net positive suction pressure (NPSP) requirements, and propellant expulsion systems for achieving propellant dump during a return-to-launch site (RTLS) abort were studied for LH2/LO2 and LCH4/LO2 upper stage propellant combinations. A state-of-the-art thermal conditioning system employing helium injection beneath the liquid surface shows the lowest weight penalty for LO2 and LCH4. A technology system incorporating a thermal subcooler (heat exchanger) for engine NPSP results in the lowest weight penalty for the LH2 tank. A preliminary design of two state-of-the-art and two new technology systems indicates a weight penalty difference too small to warrant development of a LH2 thermal subcooler. Analysis results showed that the LH2/LO2 propellant expulsion system is optimized for maximum dump line diameters, whereas the LCH4/LO2 system is optimized for minimum dump line diameter (LCH4) and maximum dump line diameter (LO2). The primary uncertainty is the accurate determination of two-phase flow rates through the dump system; experimentation is not recommended because this uncertainty is not considered significant.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-167841 , GDC-NAS-82-002 , NAS 1.26:167841
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Low-thrust chemical propulsion system propellant expulsion and thermal conditioning study. Executive summary (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Preferred techniques for providing abort pressurization and engine feed system net positive suction pressure (NPSP) for low thrust chemical propulsion systems (LTPS) were determined. A representative LTPS vehicle configuration is presented. Analysis tasks include: propellant heating analysis; pressurant requirements for abort propellant dump; and comparative analysis of pressurization techniques and thermal subcoolers.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-165622 , GDC-NAS-82-001 , NAS 1.26:165622
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Centaur Propellant Thermal Conditioning Study (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A wicking investigation revealed that passive thermal conditioning was feasible and provided considerable weight advantage over active systems using throttled vent fluid in a Centaur D-1s launch vehicle. Experimental wicking correlations were obtained using empirical revisions to the analytical flow model. Thermal subcoolers were evaluated parametrically as a function of tank pressure and NPSP. Results showed that the RL10 category I engine was the best candidate for boost pump replacement and the option showing the lowest weight penalty employed passively cooled acquisition devices, thermal subcoolers, dry ducts between burns and pumping of subcooler coolant back into the tank. A mixing correlation was identified for sizing the thermodynamic vent system mixer. Worst case mixing requirements were determined by surveying Centaur D-1T, D-1S, IUS, and space tug vehicles. Vent system sizing was based upon worst case requirements. Thermodynamic vent system/mixer weights were determined for each vehicle.
    Keywords: PROPELLANTS AND FUELS
    Type: NASA-CR-135032 , CASD-NAS-76-026
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Study of multi-megawatt technology needs for photovoltaic space power systems, volume 2 (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Possible missions requiring multimegawatt photovoltaic space power systems in the 1990's time frame and power system technology needs associated with these missions are examined. Four specific task areas were considered: (1) missions requiring power in the 1-10 megawatt average power region; (2) alternative power systems and component technologies; (3) technology goals and sensitivity trades and analyses; and (4) technology recommendations. Specific concepts for photovoltaic power approaches considered were: planar arrays, concentrating arrays, hybrid systems using Rankine engines, thermophotovoltaic approaches; all with various photovoltaic cell component technologies. Various AC/DC power management approaches, and battery, fuel cell, and flywheel energy storage concepts are evaluated. Interactions with the electrical ion engine injection and stationkeeping system are also considered.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-165323-VOL-2 , GDC-AST-81-019-VOL-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Study of multi-megawatt technology needs for photovoltaic space power systems. Volume 1: Executive summary (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Possible missions requiring multimegawatt photovoltaic space power systems in the 1990's time frame and associated power system technology needs are examined. The following concepts for photovoltaic power approaches are considered: planar arrays, concentrating arrays, hybrid systems using Rankine engines, thermophotovoltaic and AC/DC power management approaches, battery, fuel cell, flywheel energy storage, and interactions with the electrical ion engine injection and stationkeeping system. The levels of modularity for efficient, safe, constructable, serviceable, and cost effective system design are analyzed, and the benefits of alternate approaches developed. Both manned low Earth orbit and unmanned geosynchronous Earth orbit applications were examined for technological development. Technology developments applicable to power systems which appear to have benefits independent of the absolute power level are suggested.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-165323-VOL-1 , REPT-111-2401-204
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Hydrogen peroxide motor exhaust heating to components at cryogenic temperatures in the vacuum of space (1969)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Temperature measurement on thin steel shield subjected to hydrogen peroxide motor exhaust heating at cryogenic temperatures in space
    Keywords: THERMODYNAMICS AND COMBUSTION
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Thermal subcoolers for low-thrust chemical orbital transfer vehicles (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A system alternative to pressurization for providing net positive suction pressure (NPSP) to the main engine of a low-thrust cryogenic stage has been conceptually designed and analyzed. Thermal subcoolers (heat exchangers) provide required NPSP levels by using throttled vent fluid to subcool propellant delivered to the engine. The study analyzed and sized subcoolers that provide NPSP levels of 0.5 to 12.0 psi for liquid oxygen, liquid hydrogen, and liquid methane propellants. The study was part of an overall investigation to compare pressurization and other methods of providing NPSP for low-thrust vehicles.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 81-1510 , Joint Propulsion Conference; Jul 27, 1981 - Jul 29, 1981; Colorado Springs, CO; US
    Format: text
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    NASA TECHNICAL REPORTS
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