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  • SPACECRAFT PROPULSION AND POWER  (443)
  • 1985-1989  (443)
  • 1
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    Advanced orbit transfer vehicle propulsion system study (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A reuseable orbit transfer vehicle concept was defined and subsequent recommendations for the design criteria of an advanced LO2/LH2 engine were presented. The major characteristics of the vehicle preliminary design include a low lift to drag aerocapture capability, main propulsion system failure criteria of fail operational/fail safe, and either two main engines with an attitude control system for backup or three main engines to meet the failure criteria. A maintenance and servicing approach was also established for the advanced vehicle and engine concepts. Design tradeoff study conclusions were based on the consideration of reliability, performance, life cycle costs, and mission flexibility.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-174843 , NAS 1.26:174843
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Oxygen/hydrogen Space Station propulsion system concept definition for IOC (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The potential for the reduction in propulsion system life cycle costs through the use of on-board water electrolysis to generate oxygen and hydrogen propellants, as well as the potential advantages of improved system safety and contamination impact, led to a study to evaluate candidate oxygen-/hydrogen-based propulsion systems. In this study a representative set of propulsion system requirements were compiled and candidate oxygen/hydrogen-based propulsion systems synthesized. These candidate concepts were screened and a systems evaluation was performed on the remaining eight candidate concepts. Detailed system schematics were prepared. Operational design conditions were determined and system weight, volume, energy requirements, and costs were calculated. Evaluation results indicated that the oxygen/hydrogen propulsion systems can provide simple, low cost, and viable systems for the IOC Space Station. Based on these data, a relative concept evaluation was conducted using as selection criteria reliability, safety, cost, technical risk, contamination, operational utility, growth potential, and integration potential. Top ranked candidate systems were recommended to NASA/MSFC for consideration for the IOC Space Station.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 86-1561
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    The mini-dome lens space concentrator array - Recent component test results and current array development status (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The development of a high-performance, lightweight space photovoltaic concentrator array is described. The array is the first space photovoltaic concentrator system to use a refractive optical concentrator in the form of a dome-shaped, point-focus, Fresnel lens. In addition, it is the first such concentrator system to utilize prismatic cell covers to eliminate gridline obscuration losses. By combining these array features with state-of-the-art gallium arsenide cell technology, array areal power values (in watts per square meter) well in excess of present space power system levels are anticipated. In addition, the array has the potential for extremely high specific power values (in watts per kilogram).
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IECEC-89; Aug 06, 1989 - Aug 11, 1989; Washington, DC; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Simplified design and life prediction of rocket thrust chambers (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 22; 181-187
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Reactor power system deployment and startup (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: This paper addresses issues that should receive further examination in the near-term as concept selection for development of a U.S. space reactor power system is approached. The issues include: the economics, practicality and system reliability associated with transfer of nuclear spacecraft from low earth shuttle orbits to operational orbits, via chemical propulsion versus nuclear electric propulsion; possible astronaut supervised reactor and nuclear electric propulsion startup in low altitude Shuttle orbit; potential deployment methods for nuclear powered spacecraft from Shuttle; the general public safety of low altitude startup and nuclear safe and disposal orbits; the question of preferred reactor power level; and the question of frozen versus molten alkali metal coolant during launch and deployment. These issues must be considered now because they impact the SP-100 concept selection, power level selection, weight and size limits, use of deployable radiators, reliability requirements, and economics, as well as the degree of need for and the urgency of developing space reactor power systems.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Format: text
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  • 6
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    High performance Solid Rocket Motor (SRM) submerged nozzle/combustion cavity flowfield assessment (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Two and three dimensional internal flowfield solutions for critical points in the Space Shuttle solid rocket booster burn time were developed using the Lockheed Huntsville GIM/PAID Navier-Stokes solvers. These perfect gas, viscous solutions for the high performance motor characterize the flow in the aft segment and nozzle of the booster. Two dimensional axisymmetric solutions were developed at t = 20 and t = 85 sec motor burn times. The t = 85 sec solution indicates that the aft segment forward inhibitor stub produces vortices with are shed and convected downwards. A three dimensional 3.5 deg gimbaled nozzle flowfield solution was developed for the aft segment and nozzle at t = 9 sec motor burn time. This perfect gas, viscous analysis, provided a steady state solution for the core region and the flow through the nozzle, but indicated that unsteady flow exists in the region under the nozzle nose and near the flexible boot and nozzle/case joint. The flow in the nozzle/case joint region is characterized by low magnitude pressure waves which travel in the circumferential direction. From the two and three dimensional flowfield calculations presented it can be concluded that there is no evidence from these results that steady state gas dynamics is the primary mechanism resulting in the nozzle pocketing erosion experienced on SRM nozzles 8A or 17B. The steady state flowfield results indicate pocketing erosion is not directly initiated by a steady state gas dynamics phenomenon.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-179307 , NAS 1.26:179307 , LMSC-HEC-TR-F225727
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Laser-energized MHD generator for hypersonic electric air-turborockets (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The analysis and design of an open cycle Faraday MHD generator suitable for use in an electric air-turborocket cycle, the MHD-fanjet, is presented. The working fluid for the generators is unseeded high temperature hydrogen, generated by a standing, laser-supported combustion wave. This study also examines the performance of an advanced combined-cycle engine, powered by beamed energy, proposed for use in future SSTO aerospacecraft. This innovative engine incorporates the MHD-fanjet for the acceleration role within the hypersonic flight regime, from about Mach 11 to above Mach 25. Performance results indicate that specific impulses could fall in the range of 10,000 to 16,000 seconds. This would enable propellant mass fractions as low as 6 percent to 9 percent for such advanced shuttlecraft flying SSTO missions to low earth orbit.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 87-1816
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    One-megawatt solar pumped and electrically driven lasers for space power transmission (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: High power lasers in space could provide power for a variety of future space missions such as spacecraft electric power requirements and laser propulsion. This study investigates four electrically pumped laser systems, krypton fluoride, copper vapor, laser diode array, and the carbon dioxide laser, all scaled to 1-MW laser output. Each system obtained its primary power from a large solar photovoltaic array which, in turn, provides power for the appropriate laser power conditioning subsystem. Each system was block-diagrammed, and the power and efficiency were found for each subsystem. The laser diode array had the highest solar-to-laser efficiency (6 percent) and smallest radiator area making it the most advantageous of the electrically driven lasers studied. This system was then compared with an iodine solar pumped laser system previously studied. The diode array had a better wavelength with regard to transmission optics mass, but it also had a heavier radiator because of its lower temperature radiator requirement. A more advanced solar pumped laser could emerge as the preferred laser system for space applications.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: 1988 IECEC; Jul 31, 1988 - Aug 05, 1988; Denver, CO; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Rocket nozzle lip flow by direct simulation Monte Carlo method (1986)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 23; 363-367
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Heat transfer in space power and propulsion systems (1986)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: NASA's planned Space Station has projected power requirements in the 75-300 kW range; attention is presently given to the range of power system configurations thus far proposed. These are a silicon solar cell system incorporating regenerative fuel cell or battery storage, with a 10-year lifetime, a solar-dynamic power system with phase-change or regenerative fuel cell energy storage, and a combination of these two alternatives. A development status evaluation is also given for the propulsion systems that may be used by next-generation boosters. These include such novel airbreathing systems as turboramjets, air liquefaction cycle rockets, airturboramjet/rockets, and supersonic combustion ramjets.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Mechanical Engineering (ISSN 0025-6501); 108; 40-52
    Format: text
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