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  • SPACECRAFT PROPULSION AND POWER  (81)
  • 1990-1994  (81)
  • 1980-1984
  • 1945-1949
  • 1991  (81)
  • 1
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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
  • 2
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    Significant reduction in arc frequency biased solar cells: Observations, diagnostics, and mitigation technique(s) (1991)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A variety of experiments were performed which identify key factors contributing to the arcing of negatively biased high voltage solar cells. These efforts have led to reduction of greater than a factor of 100 in the arc frequency of a single cell following proper remediation procedures. Experiments naturally lead to and focussed on the adhesive/encapsulant that is used to bond the protective cover slip to the solar cell. An image-intensified charge coupled device (CCD) camera system recorded UV emission from arc events which occurred exclusively along the interfacial edge between the cover slip and the solar cell. Microscopic inspection of this interfacial region showed a bead of encapsulant along this entire edge. Elimination of this encapsulant bead reduced the arc frequency by two orders of magnitude. Water contamination was also identified as a key contributor which enhances arcing of the encapsulant bead along the solar cell edge. Spectrally resolved measurements of the observable UV light shows a feature assignable to OH(A-X) electronic emission, which is common for water contaminated discharges. Experiments in which the solar cell temperature was raised to 85 C showed a reduced arcing frequency, suggesting desorption of H2O. Exposing the solar cell to water vapor was shown to increase the arcing frequency. Clean dry gases such as O2, N2, and Ar show no enhancement of the arcing rate. Elimination of the exposed encapsulant eliminates any measurable sensitivity to H2O vapor.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Space Photovoltaic Research and Technology Conference; 10 p
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    SEI power source alternatives for rovers and other multi-kWe distributed surface applications (1991)
    In:  CASI
    Details
    Publication Date: 2013-08-29
    Description: Results of the study performed to support the Space Exploration Initiative (SEI) which investigated power system alternatives for the rover vehicles and servicers that would be used for construction and operation of a lunar base is described. Using the mission requirements and power profiles that were subsequently generated for each of these rovers and servicers, candidate power sources incorporating various power generation and energy storage technologies were identified. The technologies were those believed most appropriate to the SEI missions, and included solar, electrochemical, and isotope systems. The candidates were characterized with respect to system mass, deployed area and volume. For each of the missions a preliminary selection was made. Results of this study depict the available power sources in light of the mission requirements as they are currently defined.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: ESA, European Space Power Conference. Volume 1: Power Systems, Power Electronics, Batteries and Fuel Cells; p 365-374
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Investigations of ice formation in the Space Shuttle Main Engine 0209 main injector coolant cavity (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Severe main combustion chamber wall and main injector baffle element deterioration occurred during tests of Space Shuttle Main Engine 0209. One of the possible causes considered is ice formation and blockage of coolant to these components, resulting from the mixing of leaking hot turbine exhaust gas (hydrogen rich steam) and hydrogen coolant in the injector coolant cavity. The plausibility of ice blockage is investigated through simple mixing calculations for hot gas and hydrogen, investigation of condensation and water droplet formation, calculation of the freezing times for droplets, and the prediction of ice layer thicknesses. It is concluded that condensation and droplet formation can occur, and small water droplets that form can freeze very quickly when in contact with the cold coolant cavity surfaces. Copnservative analysis predicts, however, that the maximum thickness of the ice layers formed is too small to result in significant blockage of the coolant flow.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 91-2551
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Multikilowatt power electronics development for spacecraft (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Attention is given to several multikilowatt power electronic components developed by TRW for the Space Station Power Management and Distribution test bed at NASA Lewis Research Center. These components include a 12.5-kW DC-DC converter, a 6.25-kW battery charge/discharge regulator, an 82-channel sequential shunt unit, a 10-A remote power controllers, and three different types of 1-kW load converters. TRW is also monitoring the development of 120-V fuses for space applications. The authors discuss these developments and provide steady-state and dynamic performance parameters.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IECEC ''91: Intersociety Energy Conversion Engineering Conference; Aug 04, 1991 - Aug 09, 1991; Boston, MA; United States
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    NASA TECHNICAL REPORTS
  • 6
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    A high-performance photovoltaic concentrator array - The mini-dome Fresnel lens concentrator with 30 percent efficient GaAs/GaSb tandem cells (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A high-efficiency, lightweight space photovoltaic concentrator array is described. Previous work on the minidome Fresnel lens concentrator concept is being integrated with Boeing's 30 percent efficient tandem GaAs/GaSb concentrator cells into a high-performance photovoltaic array. Calculations indicate that, in the near term, such an array can achieve 300 W/sq m at a specific power of 100 W/kg. Emphasis of the program has now shifted to integrating the concentrator lens, tandem cell, and supporting panel structure into a space-qualifiable array. A description is presented of the current status of component and prototype panel testing and the development of a flight panel for the Photovoltaic Array Space Power Plus Diagnostics (PASP PLUS) flight experiment.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IEEE Photovoltaic Specialists Conference; Oct 07, 1991 - Oct 11, 1991; Las Vegas, NV; United States
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    NASA TECHNICAL REPORTS
  • 7
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    Electric thruster models for multimegawatt nuclear electric propulsion mission design (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: Three types of electric thrusters currently under development at JPL have potential to support future missions which utilize multimegawatt nuclear electric propulsion. These electric thrusters are the electron bombardment ion thruster, the magnetoplasmadynamic (MPD) thruster, and the electron-cyclotron-resonance (ECR) thruster. The electron bombardment ion thruster is a relatively mature technology which has been developed for operation at kilowatt power levels but will require new development for application in the multimegawatt regime. The MPD engine represents a technology which may be very well suited to steady-state multimegawatt applications but which has been limited to sub-scale (100's of kW) and pulsed (MW) testing thus far. The ECR plasma engine represents a class of very promising new concepts which are still in the basic research phase of development, but which may possess important fundamental advantages over other electric thruster technologies. Models of these thrusters are described and used to make projections of thrusters specific mass, efficiency, and power handling capacity for operation in the multimegawatt regime.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: In: Space nuclear power systems; Proceedings of the 8th Symposium, Albuquerque, NM, Jan. 6-10, 1991. Pt. 2 (A93-13751 03-20); p. 482-492.
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  • 8
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    Analysis of nozzle lip and backflow expansion of a small hydrazine thruster (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Results are presented for computations made with the direct simulation Monte Carlo method for the expansion of the thick boundary layer of a small nozzle. The objective in the investigation is to assess the boundary-layer characteristics that most affect the flow properties of the expanding gas. In the computations, large degrees of species separation and thermal nonequilibrium are observed as the gas expands around the nozzle lip. These aspects of the flow indicate the necessity of treating the problem through a discrete particle approach. Assessment is made of the sensitivity of the calculated results to the form of the boundary layer initially assumed. It is found that the amount of backflow is related to the flow temperature close to the wall. Therefore, the opportunity presents itself for the reduction of the impingement potential of such thrusters through appropriate design considerations. Experimental procedures for verification of the type of computations undertaken in the current study are discussed. It is proposed that the calculations made in the backflow region offer the best opportunity.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 7; 531-537
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    NASA TECHNICAL REPORTS
  • 9
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    Numerical propulsion system simulation (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: The approach currently being developed at the NASA Lewis Research Center to address the issues of high-fidelity propulsion systems computational simulations is discussed. The approach focuses on interdisciplinary analysis, system simulation, simulation environment, and parallel computing. The Numerical Propulsion System Simulation is a long range program with the ultimate goal of developing the capability to reduce the cost and time of developing advanced technology propulsion systems.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Computing Systems in Engineering (ISSN 0956-0521); 2; 4, 19
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  • 10
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    Examination of the effect of propulsion system performance variables on the life prediction for the SSME Lox Post (1991)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The main objective is to calculate damage evolution at the critical location of selected components of reusable space propulsion systems as the function of their operating environments and to relate the evolution of damage at the critical locations to the performance variables of the propulsion system using advanced constitutive and damage models. The models so developed will be oriented toward use in an advanced diagnostic/prognostic health monitoring system for reusable propulsion systems. The components to be modelled include a Lox Post (injector element), a thrust chamber, and a turbine blade. The study conducted on the Lox Post is reported.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center, Structural Integrity and Durability of Reusable Space Propulsion Systems; p 219-227
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    NASA TECHNICAL REPORTS
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