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  • 1
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    A safety and reliability analysis for space nuclear thermal propulsion systems (1993)
    Elsevier
    Details
    Publication Date: 1993-07-01
    Print ISSN: 0094-5765
    Electronic ISSN: 1879-2030
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Elsevier
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    PAPER CURRENT
  • 2
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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
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Nuclear Engine System Simulation (NESS) version 2.0 (1993)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The topics are presented in viewgraph form and include the following; nuclear thermal propulsion (NTP) engine system analysis program development; nuclear thermal propulsion engine analysis capability requirements; team resources used to support NESS development; expanded liquid engine simulations (ELES) computer model; ELES verification examples; NESS program development evolution; past NTP ELES analysis code modifications and verifications; general NTP engine system features modeled by NESS; representative NTP expander, gas generator, and bleed engine system cycles modeled by NESS; NESS program overview; NESS program flow logic; enabler (NERVA type) nuclear thermal rocket engine; prismatic fuel elements and supports; reactor fuel and support element parameters; reactor parameters as a function of thrust level; internal shield sizing; and reactor thermal model.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center, Nuclear Propulsion Technical Interchange Meeting, Volume 2; p 666-685
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Enabler 1 and 2 engine system design modeling and comparisons (1993)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Viewgraphs on Enabler 1 and 2 engine system design modeling and comparisons are presented. The objective of this research was to define a near-term solid-core nuclear thermal propulsion (NTP) engine system scaling database. A unified set of performance, weight, and size scaling data are identified and documented. Results should be useful to meet initial mission and concept design study requirements.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center, Nuclear Propulsion Technical Interchange Meeting, Volume 1; p 366-389
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Nuclear Engine System Simulation (NESS). Version 2.0: Program user's guide (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This Program User's Guide discusses the Nuclear Thermal Propulsion (NTP) engine system design features and capabilities modeled in the Nuclear Engine System Simulation (NESS): Version 2.0 program (referred to as NESS throughout the remainder of this document), as well as its operation. NESS was upgraded to include many new modeling capabilities not available in the original version delivered to NASA LeRC in Dec. 1991, NESS's new features include the following: (1) an improved input format; (2) an advanced solid-core NERVA-type reactor system model (ENABLER 2); (3) a bleed-cycle engine system option; (4) an axial-turbopump design option; (5) an automated pump-out turbopump assembly sizing option; (6) an off-design gas generator engine cycle design option; (7) updated hydrogen properties; (8) an improved output format; and (9) personal computer operation capability. Sample design cases are presented in the user's guide that demonstrate many of the new features associated with this upgraded version of NESS, as well as design modeling features associated with the original version of NESS.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-191081 , E-7623 , NAS 1.26:191081
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Nuclear Engine System Simulation (NESS). Volume 1: Program user's guide (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A Nuclear Thermal Propulsion (NTP) engine system design analysis tool is required to support current and future Space Exploration Initiative (SEI) propulsion and vehicle design studies. Currently available NTP engine design models are those developed during the NERVA program in the 1960's and early 1970's and are highly unique to that design or are modifications of current liquid propulsion system design models. To date, NTP engine-based liquid design models lack integrated design of key NTP engine design features in the areas of reactor, shielding, multi-propellant capability, and multi-redundant pump feed fuel systems. Additionally, since the SEI effort is in the initial development stage, a robust, verified NTP analysis design tool could be of great use to the community. This effort developed an NTP engine system design analysis program (tool), known as the Nuclear Engine System Simulation (NESS) program, to support ongoing and future engine system and stage design study efforts. In this effort, Science Applications International Corporation's (SAIC) NTP version of the Expanded Liquid Engine Simulation (ELES) program was modified extensively to include Westinghouse Electric Corporation's near-term solid-core reactor design model. The ELES program has extensive capability to conduct preliminary system design analysis of liquid rocket systems and vehicles. The program is modular in nature and is versatile in terms of modeling state-of-the-art component and system options as discussed. The Westinghouse reactor design model, which was integrated in the NESS program, is based on the near-term solid-core ENABLER NTP reactor design concept. This program is now capable of accurately modeling (characterizing) a complete near-term solid-core NTP engine system in great detail, for a number of design options, in an efficient manner. The following discussion summarizes the overall analysis methodology, key assumptions, and capabilities associated with the NESS presents an example problem, and compares the results to related NTP engine system designs. Initial installation instructions and program disks are in Volume 2 of the NESS Program User's Guide.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-191080 , E-7622 , NAS 1.26:191080
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    A review of nuclear thermal propulsion carbide fuel corrosion and key issues (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Corrosion (mass loss) of carbide nuclear fuels due to their exposure to hot hydrogen in nuclear thermal propulsion engine systems greatly impacts the performance, thrust-to-weight and life of such systems. This report provides an overview of key issues and processes associated with the corrosion of carbide materials. Additionally, past pertinent development reactor test observations, as well as related experimental work and analysis modeling efforts are reviewed. At the conclusion, recommendations are presented, which provide the foundation for future corrosion modeling and verification efforts.
    Keywords: NUCLEAR AND HIGH-ENERGY PHYSICS
    Type: NASA-CR-197533 , NAS 1.26:197533 , UNM-ISNPS-5-1994
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Updated solid-core nuclear thermal propulsion engine trades (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This study examined the application of state-of-the-art propulsion and reactor technologies to a near-term solid-core NERVA-based nuclear thermal propulsion system. Updated reactor performance and weight scaling laws were initially derived and input into a nuclear rocket engine system cycle design analysis code. Nuclear Thermal Propulsion (NTP) engine system weight, size, and performance are presented here for a large range of chamber pressures, nozzle area ratios, and thrust levels for three reactor fuel types operating at their corresponding temperatures. Operational characteristics and design features of representative NTP engine concepts are also presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 91-3507
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Near-term lunar nuclear thermal rocket engine options (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The Nuclear Thermal Rocket (NTR) is an attractive candidate propulsion system option for manned planetary missions. Its high performance capability for such missions translates into a substantial reduction in low-earth-orbit (LEO) required mass and trip times with increased operational flexibility. This study examined NTR engine options that could support near-term lunar mission operations. Expander and gas generator cycle, solid-core NERVA derivative reactor-based NTR engines were investigated. Weight, size, operational characteristics, and design features for representative NTR engine concepts are presented. The impact of using these NTR engines for a typical lunar mission scenario is also examined.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 91-2056
    Format: text
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  • 10
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    Preliminary Assessment of Using Gelled and Hybrid Propellant Propulsion for VTOL/SSTO Launch Systems (1998)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A novel, reusable, Vertical-Takeoff-and-Vertical-Takeoff-and-Landing, Single-Stage-to-Orbit (VTOL/SSTO) launch system concept, named AUGMENT-SSTO, is presented in this paper to help quantify the advantages of employing gelled and hybrid propellant propulsion system options for such applications. The launch vehicle system concept considered uses a highly coupled, main high performance liquid oxygen/liquid hydrogen (LO2/LH2) propulsion system, that is used only for launch, while a gelled or hybrid propellant propulsion system auxiliary propulsion system is used during final orbit insertion, major orbit maneuvering, and landing propulsive burn phases of flight. Using a gelled or hybrid propellant propulsion system for major orbit maneuver burns and landing has many advantages over conventional VTOL/SSTO concepts that use LO2/LH2 propulsion system(s) burns for all phases of flight. The applicability of three gelled propellant systems, O2/H2/Al, O2/RP-1/Al, and NTO/MMH/Al, and a state-of-the-art (SOA) hybrid propulsion system are examined in this study. Additionally, this paper addresses the applicability of a high performance gelled O2/H2 propulsion system to perform the primary, as well as the auxiliary propulsion system functions of the vehicle.
    Keywords: Propellants and Fuels
    Type: NASA/TM-1998-206306 , NAS 1.15:206306 , AIAA Paper 97-3216 , E-11004 , Joint Propulsion Conference; Jul 07, 1997 - Jul 09, 1997; Seattle, WA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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