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  • ENERGY PRODUCTION AND CONVERSION  (558)
  • SPACECRAFT PROPULSION AND POWER  (438)
  • 1990-1994  (355)
  • 1980-1984  (641)
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Keywords
Years
Year
  • 1
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    Megawatt solar power systems for lunar surface operations (1990)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The work presented here shows that a solar power system can provide power on the order of one megawatt to a lunar base with a fairly high specific power. The main drawback to using solar power is still the high mass, and therefore, cost of supplying energy storage through the solar night. The use of cryogenic reactant storage in a fuel cell system, however, greatly reduces the total system mass over conventional energy storage schemes.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: USRA, Proceedings of the 6th Annual Summer Conference: NASA(USRA University Advanced Design Program; p 229-239
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Stennis Space Center's approach to liquid rocket engine health monitoring using exhaust plume diagnostics (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Details are presented of the approach used in a comprehensive program to utilize exhaust plume diagnostics for rocket engine health-and-condition monitoring and assessing SSME component wear and degradation. This approach incorporates both spectral and video monitoring of the exhaust plume. Video monitoring provides qualitative data for certain types of component wear while spectral monitoring allows both quantitative and qualitative information. Consideration is given to spectral identification of SSME materials and baseline plume emissions.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: SAE PAPER 911192
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Low cost silicon-on-ceramic photovoltaic solar cells (1980)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: A technique has been developed for coating low-cost mullite-based refractory substrates with thin layers of solar cell quality silicon. The technique involves first carbonizing one surface of the ceramic and then contacting it with molten silicon. The silicon wets the carbonized surface and, under the proper thermal conditions, solidifies as a large-grained sheet. Solar cells produced from this composite silicon-on-ceramic material have exhibited total area conversion efficiencies of ten percent.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Status of diffused junction p+n InP solar cells for space applications (1994)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Recently, we have succeeded in fabricating diffused junction p(sup +)n(Cd,S) InP solar cells with measured AMO, 25 C open circuit voltage (V(sub OC)) of 887.6 mV, which, to the best of our knowledge, is higher than previously reported V(sub OC) values for any InP homojunction solar cells. The experiment-based projected achievable efficiency of these cells using LEC grown substrates is 21.3 percent. The maximum AMO, 25 C internal losses due to date on bare cells is, however, only 13.2 percent. This is because of large external and internal losses due to non-optimized front grid design, antireflection (AR) coating and emitter thickness. This paper summarizes recent advances in the technology of fabrication of p(sup +)n InP diffused structures and solar cells, resulted from a study undertaken in an effort to increase the cell efficiency. The topics discussed in this paper include advances in: (1) the formation on thin p(sup +) InP:Cd emitter layers, (2) electroplated front contacts, (3) surface passivation and (4) the design of a new native oxide/Al2O3/MgF2 tree layer AR coating using a chemically-grown P-rich passivating oxide as a first layer. Based on the high radiation resistance and the excellent post-irradiation annealing and recovery demonstrated in the early tests done to date, as well as the projected high efficiency and low-cost high-volume fabricability, these cells show a very good potential for space photovoltaic applications.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: Proceedings of the 13th Space Photovoltaic Research and Technology Conference (SPRAT 13); p 63-79
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    NASA TECHNICAL REPORTS
  • 5
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    Radiation hardness of Ga0.5In0.5 P/GaAs tandem solar cells (1991)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The radiation hardness of a two-junction monolithic Ga sub 0.5 In sub 0.5 P/GaAs cell with tunnel junction interconnect was investigated. Related single junction cells were also studied to identify the origins of the radiation losses. The optimal design of the cell is discussed. The air mass efficiency of an optimized tandem cell after irradiation with 10(exp 15) cm (-2) 1 MeV electrons is estimated to be 20 percent using currently available technology.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA. Lewis Research Center, Space Photovoltaic Research and Technology Conference; 7 p
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  • 6
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    Progress toward the development of dual junction GaAs/Ge solar cells (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Large area GaAs/Ge cells offer substantial promise for increasing the power output from existing silicon solar array designs and for providing an enabled technology for missions hitherto impossible using silicon. Single junction GaAs/Ge cells offer substantial advantages in both size, weight, and cost compared to GaAs cells but the efficiency is limited to approximately 19.2 to 20 percent AMO. The thermal absorptance of GaAs/Ge cells is also worse than GaAs/GaAs cells (0.88 vs 0.81 typ.) due to the absorption in the Ge substrate. On the other hand dual junction GaAs/Ge cells offer efficiencies up to ultimately 24 percent AMO in sizes up to 8 x 8 cm but there are still technological issues remaining to achieve current matching in the GaAs and Ge cells. This can be achieved through tuned antireflection (AR) coatings, improved quality of the GaAs growth, improved quality Ge wafers and the use of a Back Surface Field (BSF)/Back Surface Reflector (BSR) in the Ge cell. Although the temperature coefficients of efficiency and voltage are higher for dual junction GaAs/Ge cells, it has been shown elsewhere that for typical 28 C cell efficiencies of 22 percent (dual junction) vs 18.5 percent (single junction) there is a positive power tradeoff up to temperatures as high as 120 C. Due to the potential ease of fabrication of GaAs/Ge dual junction cells there is likely to be only a small cost differential compared to single junction cells.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA, Lewis Research Center, Space Photovoltaic Research and Technology, 1989; p 29-41
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Plume impingement study for reaction control system of the Orbital Maneuvering Vehicle (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A study has been performed to assess plume impingement effects from the reaction control system of NASA's OMV. A key aspect of this modeling effort has been the use of the direct Monte Carlo method as an integral part of the nozzle/plume flowfield modeling and to compute the impingement effects for configurations in which vehicle structure or multiple plumes resulted in highly three-dimensional rarefied plume flowfields. The calculation of the flowfield for a pair of interacting thruster plumes has shown that backflow in the region between the thrusters is greatly enhanced by the interaction of the two plumes. Although the present analyses have focussed on impingement force and heating effects, this methodology would also be valuable for contamination assessments since it properly accounts for the species separation effects that are inherent in the nonequilibrium nature of rarefied gas flows.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 90-1708
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    NASA TECHNICAL REPORTS
  • 8
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    Analysis of DSN software anomalies (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A categorized data base of software errors which were discovered during the various stages of development and operational use of the Deep Space Network DSN/Mark 3 System was developed. A study team identified several existing error classification schemes (taxonomies), prepared a detailed annotated bibliography of the error taxonomy literature, and produced a new classification scheme which was tuned to the DSN anomaly reporting system and encapsulated the work of others. Based upon the DSN/RCI error taxonomy, error data on approximately 1000 reported DSN/Mark 3 anomalies were analyzed, interpreted and classified. Next, error data are summarized and histograms were produced highlighting key tendencies.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-164369 , JPL-9950-536 , RCI-TR-005 , LO-726925
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    NASA TECHNICAL REPORTS
  • 9
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    Design and analysis report for the RL10-2B breadboard low thrust engine (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The breadboard low thrust RL10-2B engine is described. A summary of the analysis and design effort to define the multimode thrust concept applicable to the requirements for the upper stage vehicles is provided. Baseline requirements were established for operation of the RL10-2B engine under the following conditions: (1) tank head idle at low propellant tank pressures without vehicle propellant conditioning or settling thrust; (2) pumped idle at a ten percent thrust level for low G deployment and/or vehicle tank pressurization; and (3) full thrust (15,000 lb.). Several variations of the engine configuration were investigated and results of the analyses are included.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-174857 , NAS 1.26:174857 , FR-18046-3
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    NASA TECHNICAL REPORTS
  • 10
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    LOX/hydrocarbon auxiliary propulsion system study (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Liquid oxygen/hydrocarbon propulsion systems applicable to a second generation orbiter OMS/RCS were compared, and major system/component options were evaluated. A large number of propellant combinations and system concepts were evaluated. The ground rules were defined in terms of candidate propellants, system/component design options, and design requirements. System and engine component math models were incorporated into existing computer codes for system evaluations. The detailed system evaluations and comparisons were performed to identify the recommended propellant combination and system approach.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-171655 , NAS 1.26:171655 , MDC-E2576
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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