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  • 1
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    MPD work at MIT (1991)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: MPD work at MIT is presented in the form of the view-graphs. The following subject areas are covered: the MIT program, its goals, achievements, and roadblocks; quasi one-dimensional modeling; two-dimensional modeling - transport effects and Hall effect; microscopic instabilities in MPD flows and modified two stream instability; electrothermal stability theory; separation of onset and anode depletion; exit plane spectroscopic measurements; phenomena of onset as performance limiter; explanations of onset; geometry effects on onset; onset at full ionization and its consequences; relationship to anode depletion; summary on self-field MPD; applied field MPD - the logical growth path; the case for AF; the challenges of AF MPD; and recommendations.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center, Magnetoplasmadynamic Thruster Workshop; 17 p
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Annular nozzle engine technology (1992)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The topics covered include: (1) driver rocket subsystem; (2) annular nozzle engine technology; (3) expansion-deflection nozzle; (4) aerospike-nozzled engine background; (5) aerospike testing; (6) linear aerospike; and (7) the combined cycle engine.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center, Rocket-Based Combined-Cycle (RBCC) Propulsion Technology Workshop. Tutorial Session; 8 p
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Design of a direct nuclear propulsion system for a resupply mission to Phobos (1989)
    In:  CASI
    Details
    Publication Date: 2017-03-17
    Description: For a long-term mission in space, a propulsion system with a high specific impulse and low mass must be designed. The system must also be safe in terms of human lives and must be cost efficient to a degree. The main focus is to design a direct nuclear propulsion system for a resupply mission to Phobos from an orbiting Earth space station and return. The design considered is an annular, packed particle bed nuclear reactor with hydrogen used as the reflector, moderator, coolant, and propellant. The use of hydrogen in all these areas helps reduce the total mass, since the amount of hydrogen required is only that needed for propulsion. The mass of hydrogen required for propulsion is reduced by using a direct nuclear propulsion system with a high specific impulse relative to a hydrogen oxygen system. Certain calculations were not looked at in great detail. This included the aerospace details of the mission. Most of the numbers for this section were found in tables and taken to be correct without extensive calculations. The main objective of the project was to study the thermohydraulic and neutronic aspects of the reactor.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: USRA, NASA(USRA University Advanced Design Program Fifth Annual Summer Conference; p 195-200
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Concepts for space maintenance of OTV engines (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Concepts for space maintainability of the Orbital Transfer Vehicle (OTV) engines are examined. An engine design is developed which is driven by space maintenance requirements and by a failure modes and effects analysis (FMEA). Modularity within the engine is shown to offer cost benefits and improved space maintenance capabilities. Space-operable disconnects are conceptualized for both engine change-out and for module replacement. A preliminary space maintenance plan is developed around a controls and condition monitoring system using advanced sensors, controls, and condition monitoring concepts.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ., The 1986 JANNAF Propulsion Meeting, Volume 1; p 99-110
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Orbit Transfer Rocket Engine Technology Program: Advanced engine study, task D.1/D.3 (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Concepts for space maintainability of OTV engines were examined. An engine design was developed which was driven by space maintenance requirements and by a failure mode and effects (FME) analysis. Modularity within the engine was shown to offer cost benefits and improved space maintenance capabilities. Space operable disconnects were conceptualized for both engine change-out and for module replacement. Through FME mitigation the modules were conceptualized to contain the least reliable and most often replaced engine components. A preliminary space maintenance plan was developed around a controls and condition monitoring system using advanced sensors, controls, and condition monitoring concepts. A complete engine layout was prepared satisfying current vehicle requirements and utilizing projected component advanced technologies. A technology plan for developing the required technology was assembled.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-175084 , NAS 1.26:175084 , RI/RD86-116
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Orbit transfer rocket engine technology program. Phase 2: Advanced engine study (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In Phase 2 of the Advanced Engine Study, the Failure Modes and Effects Analysis (FMEA) maintenance-driven engine design, preliminary maintenance plan, and concept for space operable disconnects generated in Phase 1 were further developed. Based on the results of the vehicle contractors Orbit Transfer Vehicle (OTV) Concept Definition and System Analysis Phase A studies, minor revisions to the engine design were made. Additional refinements in the engine design were identified through further engine concept studies. These included an updated engine balance incorporating experimental heat transfer data from the Enhanced Heat Load Thrust Chamber Study and a Rao optimum nozzle contour. The preliminary maintenance plan of Phase 1 was further developed through additional studies. These included a compilation of critical component lives and life limiters and a review of the Space Shuttle Main Engine (SSME) operations and maintenance manual in order to begin outlining the overall maintenance procedures for the Orbit Transfer Vehicle Engine and identifying technology requirements for streamlining space-based operations. Phase 2 efforts also provided further definition to the advanced fluid coupling devices including the selection and preliminary design of a preferred concept and a preliminary test plan for its further development.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-179602 , NAS 1.26:179602 , RI/RD-87-126
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Advanced LOX/H2 engine technologies for future OTVs (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: It is pointed out that NASA and DOD missions of the near future include, by current estimates, approximately 50 highly energetic missions to geosynchronous orbit. Advanced concepts make use of the Space Shuttle to transport the assembled orbital transfer vehicle (OTV) to low earth orbit (LEO) or to bring components and propellants from which to assemble the OTV in LEO. An advanced expander cycle engine based upon the RS-44 engine design has been planned for ultimate use with advanced space-based OTVs. Its design features complement the characteristics of manned space-based aeroassist vehicles which will provide the most cost-effective means for payload transfer between LEO and GEO orbits. A test-bed program is planned for early demonstration of the advanced expander cycle engine operation.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 83-1312
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Linear rocket engines for advanced space transportation systems (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: The linear rocket engine is shown to be a viable candidate propulsion system for post-Space Shuttle single-stage-to-orbit systems. The linear engine system has been developed and fired demonstrating high performance and long life with firing durations exceeding 500 seconds. The application of the split or dual combustor to the linear engine permits the uses of two different propellant combinations in a single engine system. The split combustor possesses the advantages of the two position extendible bell nozzle in a fixed nozzle configuration. Engine power cycles and applications to typical vehicles are discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 75-1251
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    NASA TECHNICAL REPORTS
  • 9
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    Linear aerospike engine (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A description is presented of a dual-fuel modular split-combustor linear aerospike engine concept. The considered engine represents an approach to an integrated engine for a reusable single-stage-to-orbit (SSTO) vehicle. The engine burns two fuels (hydrogen and a hydrocarbon) with oxygen in separate combustors. Combustion gases expand on a linear aerospike nozzle. An engine preliminary design is discussed. Attention is given to the evaluation process for selecting the optimum number of modules or divisions of the engine, aspects of cooling and power cycle balance, and details of engine operation.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 77-968 , Propulsion Conference; Jul 11, 1977 - Jul 13, 1977; Orlando, FL; US
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    NASA TECHNICAL REPORTS
  • 10
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    Advanced LOX/H sub 2 engine technologies for future OTVs (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The optimization methods and trade studies which were used to define a 1980 state-of-the-art design of orbital transfer vehicles are summarized. The advanced thrust chamber, turbomachinery, and engine power cycle technologies recommended for development and verification during the 1980's are discussed. The state-of-the-art design serves as one of the reference points for evaluation of the advanced technology concepts. A second reference point is provided by the 1960 state-of-the-art RL-10 engine. Advanced heat energy extraction concepts in the combustor and injector are presented that will permit the high chamber pressures expected of the advanced expander cycle engine concept. Advanced turbomachinery concepts are selected that will help utilize efficiently the heat energy extracted in the thrust chamber and aid in uprating chamber pressures to values five times those realized with 1960 to 1980 technologies. The higher chamber pressure benefits are maximized with nozzle concepts that will package within a short retracted length and extend to the very high expansion area ratios required for specific impulse values significantly higher than those now realized by operational systems. Control system component concepts studied will allow utilization of the high turbine drive energy levels in a reliable repeatable manner that will reduce program risk and enhance overall space transportation system mission life cycle cost.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: APL The 1983 JANNAF Propulsion Meeting, Vol. 1; p 29-40
    Format: text
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