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  • Other Sources  (12)
  • SPACECRAFT PROPULSION AND POWER  (8)
  • ELECTRONICS AND ELECTRICAL ENGINEERING  (4)
  • Life and Medical Sciences
  • 1985-1989  (12)
  • 1960-1964
  • 1
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    Liquid metal cooled reactors for space power applications (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The technology basis for evaluation of liquid metal cooled space reactors is summarized. Requirements for space nuclear power which are relevant to selection of the reactor subsystem are then reviewed. The attributes of liquid metal cooled reactors are considered in relation to these requirements in the areas of liquid metal properties, neutron spectrum characteristics, and fuel form. Key features of typical reactor designs are illustrated. It is concluded that liquid metal cooled fast spectrum reactors provide a high confidence, flexible option for meeting requirements for SP-100 and beyond.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Oxygen/hydrocarbon combustion devices technology (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: A program was conducted to investigate ignition, combustion and heat transfer characteristics of liquid oxygen and RP-1 fuel applicable to large gas generator cycle booster engines. The program was part of a broad effort intended to generate a combustion devices technology base for both RP-1 and methane fuels and both gas generator and staged combustion engine cycles. Two gas generator injector designs were tested over a chamber pressure range of 1500 to 3100 psia and a gas temperature range of 1500 to 2300 R. Both configurations were evaluated for combustion efficiency, gas temperature profile and combustion stability. Thrust chamber firings were conducted using a platelet type main injector and a water cooled calorimeter combustion chamber. Test conditions ranged from 1700 to 2200 psia chamber pressure and from 2.0 to 2.8 mixture ratio. A program goal to reduce previously measured nozzle heating rates was achieved, but at the expense of combustion efficiency.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ. The 1985 JANNAF Propulsion Meeting, Volume 1; p 271-280
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    LH2 on-orbit storage tank support trunnion design and verification (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A detailed fatigue analysis was conducted to provide verification of the trunnion design in the reusable Cryogenic Fluid Management Facility for Shuttle flights and to assess the performance capability of the trunnion E-glass/S-glass epoxy composite material. Basic material property data at ambient and liquid hydrogen temperatures support the adequacy of the epoxy composite for seven-mission requirement. Testing of trunnions fabricated to the flight design has verified adequate strength and fatigue properties of the design to meet the requirements of seven Shuttle flights.
    Keywords: SPACECRAFT PROPULSION AND POWER
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    NASA TECHNICAL REPORTS
  • 4
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    Design and development of a multibeam 1.4 GHz pushbroom microwave radiometer (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The design and operation of a multiple beam, digital signal processing radiometer are discussed. The discussion includes a brief description of each major subsystem and an overall explanation of the hardware requirements and operation. A series of flight tests was conducted in which sea-truth sites, as well as an existing radiometer were used to verify the Pushbroom Radiometer performance. The results of these tests indicate that the Pushbroom Radiometer did meet the sensitivity design goal of 1.0 kelvin, and exceeded the accuracy requirement of 2.0 kelvin. Additional performance characteristics and test results are also presented.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA-TM-89005 , NAS 1.15:89005
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Orbital spacecraft resupply technology (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The resupplying of orbital spacecraft using the Space Shuttle, Orbital Maneuvering Vehicle, Orbital Transfer Vehicle or a depot supply at a Space Station is studied. The governing factor in fluid resupply designs is the system size with respect to fluid resupply quantities. Spacecraft propellant management for tankage via diaphragm or surface tension configurations is examined. The capabilities, operation, and application of adiabatic ullage compression, ullage exchange, vent/fill/repressurize, and drain/vent/no-vent fill/repressurize, which are proposed transfer methods for spacecraft utilizing tankage configurations, are described. Selection of the appropriate resupply method is dependent on the spacecraft design features. Hydrazine adiabatic compression/detonation, liquid-free vapor venting to prevent freezing, and a method for no-vent liquid filling are analyzed. Various procedures for accurate measurements of propellant mass in low gravity are evaluated; a system of flowmeters with a PVT system was selected as the pressurant solubility and quantity gaging technique. Monopropellant and bipropellant orbital spacecraft consumable resupply system tanks which resupply 3000 lb of hydrazine and 7000 lb of MMH/NTO to spacecraft on orbit are presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 86-1604
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    NASA TECHNICAL REPORTS
  • 6
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    Recent developments on a 128 x 128 indium antimonide/FET switch hybrid imager for low-background applications (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: By combining high-quality mesa photovoltaic indium antimonide detector material with a silicon x-y FET switch multiplexer, a useful infrared area detector has been developed. This device is intended for low-background applications, where high sensitivity is required. Initial characterization of the detector at 80 K showed a KTC limited read noise of less than 1000 electrons, good dark current, responsivity uniformity, and a maximum readout rate of 10 MHz. The hybrid mating technology has sufficient precision to allow expansion to a 256 x 256 format. The dark current in the detector material is sufficiently low to allow full-frame integration, even with arrays as large as 256 x 256 elements.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: Infrared detectors, sensors, and focal plane arrays; Aug. 21, 22, 1986; San Diego, CA; United States
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    NASA TECHNICAL REPORTS
  • 7
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    Experimental evaluation of resistojet thruster plume shields (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The exhaust of an engineering model resistojet has been investigated using rotary pitot probes and a rotary quartz crystal microbalance. The resistojet operated on CO2 propellant at a mass flow rate of 0.29 g/sec in both heated and unheated flows. Measurements of local flow angles in the near field of a conical plume shield indicated that the shield was not wholly effective in confining the flow to the region upstream of its exit plane. However, the absolute levels of the measured mass flux into the backflow region were very low, on the order of 7 x 10 to the -7 power g/sqcm/sec or less. The use of a circualr disk at the exit plane of the existing conical shield showed some benefit in decreasing the amount of backflow by a factor of two. Lastly, a detached shield placed upstream of the resistojet exit plane demonstrated a small degree of local shielding for the region directly behind it.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-101363 , E-4356 , NAS 1.15:101363 , IEPC-88-091
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Advances in thin-film solar cells for lightweight space photovoltaic power (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: The development of photovoltaic arrays beyond the next generation is discussed with attention given to the potentials of thin-film polycrystalline and amorphous cells. Of particular importance is the efficiency (the fraction of incident solar energy converted to electricity) and specific power (power to weight ratio). It is found that the radiation tolerance of thin-film materials is far greater than that of single crystal materials. CuInSe2 shows no degradation when exposed to 1-MeV electrons.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IAF PAPER ICOSP89-1-8 , Space Power (ISSN 0951-5089); 8; 1-2
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    NASA TECHNICAL REPORTS
  • 9
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    Short wavelength 128 by 128 focal plane arrays for remote sensing applications (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Short-wavelength (1-2.5-micron) 128x128 focal plane arrays have been fabricated and demonstrated with high pixel yields and dark-current-limited performance. The detector material is HgCdTe grown by LPE on a sapphire substrate which yields high-performance uniform detectors. The detector arrays were characterized at temperatures of 80-150 K; the peak quantum efficiency at 2.4 microns is 80 percent. The multiplexer is a Reticon FET switch with output amplifiers. It is noted that the long-term goal of this project is to develop a 150x1000 mosaicked focal plane for use in the HIRIS instrument on the Earth Observing System.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: Focal Plane Arrays: Technology and Applications; Nov 19, 1987 - Nov 20, 1987; Cannes; France
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    NASA TECHNICAL REPORTS
  • 10
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    Advances in thin-film solar cells for lightweight space photovoltaic power (1989)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The present stature and current research directions of photovoltaic arrays as primary power systems for space are reviewed. There have recently been great advances in the technology of thin-film solar cells for terrestrial applications. In a thin-film solar cell the thickness of the active element is only a few microns; transfer of this technology to space arrays could result in ultralow-weight solar arrays with potentially large gains in specific power. Recent advances in thin-film solar cells are reviewed, including polycrystalline copper-indium selenide (CuInSe2) and related I-III-VI2 compounds, polycrystalline cadmium telluride and related II-VI compounds, and amorphous silicon:hydrogen and alloys. The best experimental efficiency on thin-film solar cells to date is 12 percent AMO for CuIn Se2. This efficiency is likely to be increased in the next few years. The radiation tolerance of thin-film materials is far greater than that of single-crystal materials. CuIn Se2 shows no degradation when exposed to 1 MeV electrons. Experimental evidence also suggests that most of all of the radiation damage on thin-films can be removed by a low temperature anneal. The possibility of thin-film multibandgap cascade solar cells is discussed, including the tradeoffs between monolithic and mechanically stacked cells. The best current efficiency for a cascade is 12.5 percent AMO for an amorphous silicon on CuInSe2 multibandgap combination. Higher efficiencies are expected in the future. For several missions, including solar-electric propulsion, a manned Mars mission, and lunar exploration and manufacturing, thin-film photovolatic arrays may be a mission-enabling technology.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-102017 , E-4734 , NAS 1.15:102017 , International Conference on Space Power; Jun 05, 1989 - Jun 07, 1989; Cleveland, OH; United States
    Format: application/pdf
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