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  • 1
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    Application of Taguchi methods to propulsion system optimization for SSTO vehicles (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 29; 4; p. 453-459.
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Propulsion requirements for reusable single-stage-to-orbit rocket vehicles (1994)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: The conceptual design of a single-stage-to-orbit (SSTO) vehicle using a wide variety of evolutionary technologies has recently been completed as a part of NASA's Advanced Manned Launch System (AMLS) study. The employment of new propulsion system technologies is critical to the design of a reasonably sized, operationally efficient SSTO vehicle. This paper presents the propulsion system requirements identified for this near-term AMLS SSTO vehicle. Sensitivities of the vehicle to changes in specific impulse and sea-level thrust-to-weight ratio are examined. The results of a variety of vehicle/propulsion system trades performed on the near-term AMLS SSTO vehicle are also presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 31; 3; p. 414-420
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    NASA TECHNICAL REPORTS
  • 3
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    Nuclear thermal rockets - Key to moon-Mars exploration (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: The Space Exploration Initiative (SEI) calls for lunar and Martian exploration missions for which solid-core nuclear thermal rockets (NTRs), in virtue of their single-stage, fully-reusable nature, are ideally suited. NTRs promise double the specific impulse of chemical propulsion. A lunar mission employing a reusable NTR is currently being conducted by NASA. The NTR would be assembled in LEO in such a way that it remained 'radioactively cold' during earth-to-orbit deployment by a heavy-lift chemical booster, and therefore presented no radioactive hazard. Also under consideration is a particle-bed reactor in which the hydrogen propulsive fluid directly cools coated-particle fuel spheres.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Aerospace America (ISSN 0740-722X); 30; 7, Ju; 34-37
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    NASA TECHNICAL REPORTS
  • 4
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    Utilizing air-turborocket and rocket propulsion for a single-stage-to-orbit vehicle (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 28; 560-566
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    NASA TECHNICAL REPORTS
  • 5
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    State-of-the art of dc components for secondary power distribution of Space Station Freedom (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: 120-V dc secondary power distribution has been selected for Space Station Freedom. State-of-the art components and subsystems are examined in terms of performance, size, and topology. One of the objectives of this work is to inform Space Station users what is available in power supplies and power control devices. The other objective is to stimulate interest in the component industry so that more focused product development can be started. Based on results of this study, it is estimated that, with some redesign, modifications, and space qualification, may of these components may be applied to Space Station needs.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IEEE Transactions on Power Electronics (ISSN 0885-8993); 6; 548-561
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    NASA TECHNICAL REPORTS
  • 6
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    Nuclear thermal rocket workshop reference system Rover/NERVA (1991)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The Rover/NERVA engine system is to be used as a reference, against which each of the other concepts presented in the workshop will be compared. The following topics are reviewed: the operational characteristics of the nuclear thermal rocket (NTR); the accomplishments of the Rover/NERVA programs; and performance characteristics of the NERVA-type systems for both Mars and lunar mission applications. Also, the issues of ground testing, NTR safety, NASA's nuclear propulsion project plans, and NTR development cost estimates are briefly discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Nuclear Thermal Propulsion: A Joint NASA(DOE)DOD Workshop; p 53-92
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Propulsion system needs (1991)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The needs of the designer of a solid core nuclear rocket engine are discussed. Some of the topics covered include: (1) a flight thrust module/feed system module assembly; (2) a nuclear thermal rocket (NTR), expander cycle, dual T/P; (3) turbopump operating conditions; (4) typical system parameters; (5) growth capability composite fuel elements; (6) a NTR radiation cooled nozzle extension; (7) a NFS-3B Feed System; and (8) a NTR Integrated Pneumatic-Fluidics Control System.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center, Nuclear Thermal Propulsion: A Joint NASA(DOE)DOD Workshop; p 399-411
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  • 8
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    NERVA upgrade: Non-nuclear components (1991)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The design of engine based upon the original accomplishmentns of the ROVER/NERVA program (but with the use of advanced technologies) is discussed. Some hypothetical requirements for a typical manned Mars mission are outlined. The following subject areas are covered: typical mission NTR propulsion requirements; performance of NTR operating with high pressure hydrogen; NTR expander cycles; ROVER/NERVA core reactor; Mars propulsion 100 K NTR thrust chamber thermal design parameters; 100 K NTR nozzle assembly; NTR integrated pneumatic-fluidics control system; and 100 K flight thrust module/feed system module assembly.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center, Nuclear Thermal Propulsion: A Joint NASA(DOE)DOD Workshop; p 93-104
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    NASA TECHNICAL REPORTS
  • 9
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    Innovative nuclear thermal propulsion technology evaluation - Results of the NASA/DOE task team study (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: In response to findings from two NASA/DOE nuclear propulsion workshops, six task teams were created to continue evaluation of various propulsion concepts, from which evolved an innovative concepts subpanel to evaluate thermal propulsion concepts which did not utilize solid fuel. This subpanel endeavored to evaluate each concept on a level technology basis, and to identify critical issues, technologies, and early proof-of-concept experiments. Results of the concept studies including the liquid core fission, the gas core fission, the fission foil reactors, explosively driven systems, fusion, and antimatter are presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IAF PAPER 91-235
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    NASA TECHNICAL REPORTS
  • 10
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    Experimental study of low Reynolds number nozzles (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: High-performance electrothermal thrusters operate in a low nozzle-throat Reynolds number regime. Under these conditions, the flow boundary layer occupies a large volume inside the nozzle, contributing to large viscous losses. Four nozzles (conical, bell, trumpet, and modified trumpet) and a sharp-edged orifice were evaluated over a Reynolds number range of 500 to 9000 with unheated nitrogen and hydrogen. The nozzles showed significant decreases in specific impulse efficiency with decreasing Reynolds number. At Reynolds numbers less than 1000, all four nozzles were probably filled with a large boundary layer. The discharge coefficient decreased with Reynolds number in the same manner as the specific impulse efficiency. The bell and modified trumpet nozzles had discharge coefficients 4 to 8 percent higher than those of the cone or trumpet nozzles. The Two-Dimensional Kinetics (TDK) nozzle analysis computer program was used to predict nozzle performance. The results were then compared to the experimental results in order to determine the accuracy of the program within this flow regime.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-89858 , E-3526 , NAS 1.15:89858 , AIAA PAPER 87-0992
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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