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  • 1
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    Enhanced EOS photovoltaic power system capability with InP solar cells (1991)
    In:  CASI
    Details
    Publikationsdatum: 2013-08-29
    Beschreibung: The Earth Observing System (EOS), which is part of the International Mission to Planet Earth, is NASA's main contribution to the Global Change Research Program which opens a new era in international cooperation to study the Earth's environment. Five large platforms are to be launched into polar orbit, two by NASA, two by ESA, and one by the Japanese. In such an orbit the radiation resistance of indium phosphide solar cells combined with the potential of utilizing five micron cell structures yields an increase of 10 percent in the payload capability. If further combined with the advanced photovoltaic solar array the payload savings approaches 12 percent.
    Schlagwort(e): SPACECRAFT PROPULSION AND POWER
    Materialart: ESA, European Space Power Conference. Volume 2: Photovoltaic Generators; p 641-645
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 2
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    Liquid metal cooled reactors for space power applications (1985)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-19
    Beschreibung: 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.
    Schlagwort(e): SPACECRAFT PROPULSION AND POWER
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 3
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    Oxygen/hydrocarbon combustion devices technology (1985)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-19
    Beschreibung: 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.
    Schlagwort(e): SPACECRAFT PROPULSION AND POWER
    Materialart: Johns Hopkins Univ. The 1985 JANNAF Propulsion Meeting, Volume 1; p 271-280
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    LH2 on-orbit storage tank support trunnion design and verification (1985)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: 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.
    Schlagwort(e): SPACECRAFT PROPULSION AND POWER
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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  • 5
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    Orbital spacecraft resupply technology (1986)
    In:  Other Sources
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    Publikationsdatum: 2019-06-28
    Beschreibung: 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.
    Schlagwort(e): SPACECRAFT PROPULSION AND POWER
    Materialart: AIAA PAPER 86-1604
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 6
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    Solid rocket technology advancements for space tug and IUS applications (1975)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: In order for the shuttle tug or interim upper stage (IUS) to capture all the missions in the current mission model for the tug and the IUS, an auxiliary or kick stage, using a solid propellant rocket motor, is required. Two solid propellant rocket motor technology concepts are described. One concept, called the 'advanced propulsion module' motor, is an 1800-kg, high-mass-fraction motor, which is single-burn and contains Class 2 propellent. The other concept, called the high energy upper stage restartable solid, is a two-burn (stop-restartable on command) motor which at present contains 1400 kg of Class 7 propellant. The details and status of the motor design and component and motor test results to date are presented, along with the schedule for future work.
    Schlagwort(e): SPACECRAFT PROPULSION AND POWER
    Materialart: NASA-CR-145561 , JPL-TM-33-746
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 7
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    Experimental evaluation of resistojet thruster plume shields (1988)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: 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.
    Schlagwort(e): SPACECRAFT PROPULSION AND POWER
    Materialart: NASA-TM-101363 , E-4356 , NAS 1.15:101363 , IEPC-88-091
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 8
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    The JPL advanced propulsion module motor chamber (1976)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: A Kevlar 49/epoxy chamber has been developed for the advanced propulsion module motor. This chamber was successfully designed, fabricated, and hydroproof-tested at 511.6 N/sq cm. The fabrication, interior dimensional inspection, and proof test are discussed, showing that the chamber will be capable of achieving the design burst pressure of 639.8 N/sq cm. The projected chamber growth at 448.2 N/sq cm is presented based on the strain gage and volumetric growth data collected in that proof test.
    Schlagwort(e): SPACECRAFT PROPULSION AND POWER
    Materialart: AIAA PAPER 76-637 , Propulsion Conference; Jul 26, 1976 - Jul 29, 1976; Palo Alto, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Cryogenic Fluid Management Facility (1984)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The Cryogenic Fluid Management Facility (CFMF) is a reusable test bed which is designed to be carried into space in the Shuttle cargo bay to investigate systems and technologies required to efficiently and effectively manage cryogens in space. The facility hardware is configured to provide low-g verification of fluid and thermal models of cryogenic storage, transfer concepts and processes. Significant design data and criteria for future subcritical cryogenic storage and transfer systems will be obtained. Future applications include space-based and ground-based orbit transfer vehicles (OTV), space station life support, attitude control, power and fuel depot supply, resupply tankers, external tank (ET) propellant scavenging, space-based weapon systems and space-based orbit maneuvering vehicles (OMV). This paper describes the facility and discusses the cryogenic fluid management technology to be investigated. A brief discussion of the integration issues involved in loading and transporting liquid hydrogen within the Shuttle cargo bay is also included.
    Schlagwort(e): SPACECRAFT PROPULSION AND POWER
    Materialart: AIAA PAPER 84-1340
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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  • 10
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    Advances in thin-film solar cells for lightweight space photovoltaic power (1989)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: 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.
    Schlagwort(e): SPACECRAFT PROPULSION AND POWER
    Materialart: IAF PAPER ICOSP89-1-8 , Space Power (ISSN 0951-5089); 8; 1-2
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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