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  • 1
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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
  • 2
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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
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    NASA TECHNICAL REPORTS
  • 3
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    Fast track lunar NTR systems assessment for the First Lunar Outpost and its evolvability to Mars (1992)
    In:  CASI
    Details
    Publication Date: 2013-08-29
    Description: The objectives of the 'fast track' lunar Nuclear Thermal Rocket (NTR) analysis are to quantify necessary engine/stage characteristics to perform NASA's 'First Lunar Outpost' scenario and to assess the potential for evolution to Mars mission applications. By developing NTR/stage technologies for use in NASA's 'First Lunar Outpost' scenario, NASA will make a major down payment on the key components needed for the follow-on Mars Space Transportation System. A faster, cheaper approach to overall lunar/Mars exploration is expected.
    Keywords: ENGINEERING (GENERAL)
    Type: NASA. Lyndon B. Johnson Space Center, Third SEI Technical Interchange: Proceedings; p 421-436
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  • 4
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    The rationale/benefits of nuclear thermal rocket propulsion for NASA's lunar space transportation system (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Two nuclear thermal rocket (NTR) technology options are examined - one derived from the graphite-moderated reactor concept developed by NASA and the AEC under the Rover/NERVA (Nuclear Engine for Rocket Vehicle Application) programs, and a second concept, the Particle Bed Reactor. The paper also summarizes NASA's lunar outpost scenario, compares relative performance provided by different lunar space transportation system concepts, and discusses important operational issues (e.g., reusability, engine 'end-of-life' disposal, etc.) associated with using this important propulsion technology.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: AIAA PAPER 91-2052
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  • 5
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    Lunar mission design using Nuclear Thermal Rockets (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The NERVA-class Nuclear Thermal Rocket (NTR), with performance nearly double that of advanced chemical engines, has long been considered an enabling technology for human missions to Mars. NTR engines address the demanding trip time and payload delivery needs of both cargo-only and piloted flights. But NTR can also reduce the Earth launch requirements for manned lunar missions. First use of NTR for the Moon would be less demanding and would provide a test-bed for early operations experience with this powerful technology. Study of application and design options indicates that NTR propulsion can be integrated with the Space Exploration Initiative scenarios to deliver performance gains while managing controlled, long-term disposal of spent reactors to highly stable orbits.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: In: Space nuclear power systems; Proceedings of the 8th Symposium, Albuquerque, NM, Jan. 6-10, 1991. Pt. 1 (A93-13751 03-20); p. 100-105.
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  • 6
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    "Bimodal" Nuclear Thermal Rocket (BNTR) Propulsion for Future Human Mars Exploration Missions (2004)
    In:  CASI
    Details
    Publication Date: 2018-06-06
    Description: The Nuclear Thermal Rocket (NTR) Propulsion program is discussed. The Rover/NERVA program from 1959-1972 is compared with the current program. A key technology description, bimodal vehicle design for Mars Cargo and the crew transfer vehicle with inflatable module and artificial gravity capability, including diagrams are included. The LOX-Augmented NTR concept/operational features and characteristics are discussed.
    Keywords: Spacecraft Propulsion and Power
    Type: 2003 NASA Seal/Secondary Air System Workshop, Volume 1; 305-323; NASA/CP-2004-212963/VOL1
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  • 7
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    NTR vehicle commonality assessment for piloted lunar and Mars missions (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A study is presented that assesses the feasibility of (1) using common nuclear thermal rocket (NTR) vehicle components to perform a wide range of lunar and Mars missions, and (2) potential performance gains achieved via 'dual-mode' NTR operation, where the nuclear reactor is utilized not only for propulsion but also for electrical power generation. Four vehicle configurations are considered, modular designs with multiple single engine modules and single engine designs with multiple propellant tanks. The standard tank sizes arrived at in the Mars mission mass performance calculations are then applied to cargo and piloted lunar craft to evaluate lunar NTR mass performance against that for chemical propulsion.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 91-3575
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  • 8
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    Radiation dose estimates for typical piloted NTR lunar and Mars mission engine operations (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The natural and manmade radiation environments to be encountered during lunar and Mars missions are qualitatively summarized. The computational methods available to characterize the radiation environment produced by an operating nuclear propulsion system are discussed. Mission profiles and vehicle configurations are presented for a typical all-propulsive, fully reusable lunar mission and for a typical all-propulsive Mars mission. Estimates of crew location biological doses are developed for all propulsive maneuvers. Post-shutdown dose rates near the nuclear engine are estimated at selected mission times.
    Keywords: AEROSPACE MEDICINE
    Type: AIAA PAPER 91-3407
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  • 9
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    A Nuclear Cryogenic Propulsion Stage for Near-Term Space Missions (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-27
    Description: Development efforts in the United States have demonstrated the viability and performance potential of NTP systems. For example, Project Rover (1955 - 1973) completed 22 high power rocket reactor tests. Peak performances included operating at an average hydrogen exhaust temperature of 2550 K and a peak fuel power density of 5200 MW/m3 (Pewee test), operating at a thrust of 930 kN (Phoebus-2A test), and operating for 62.7 minutes on a single burn (NRXA6 test).1 Results from Project Rover indicated that an NTP system with a high thrust-toweight ratio and a specific impulse greater than 900 s would be feasible. Binary and ternary carbide fuels may have the potential for providing even higher specific impulses.
    Keywords: Launch Vehicles and Launch Operations; Spacecraft Propulsion and Power
    Type: M13-2984 , AIAA Space 2013; 10-12 Sept. 2013; San Diego, CA; United States
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  • 10
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    Nuclear propulsion - A vital technology for the exploration of Mars and the planets beyond (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The physics and technology issues and performance potential of various direct thrust fission and fusion propulsion concepts are examined. Next to chemical propulsion the solid core fission thermal rocket (SCR) is the only other concept to be experimentally tested at the power (approx 1.5 to 5.0 GW) and thrust levels (approx 0.33 to 1.11 MN) required for manned Mars missions. With a specific impulse of approx 850 s, the SCR can perform various near-earth, cislunar and interplanetary missions with lower mass and cost requirements than its chemical counterpart. The gas core fission thermal rocket, with a specific power and impulse of approx 50 kW/kg and 5000 s offers the potential for quick courier trips to Mars (of about 80 days) or longer duration exploration cargo missions (lasting about 280 days) with starting masses of about 1000 m tons. Convenient transportation to the outer Solar System will require the development of magnetic and inertial fusion rockets (IFRs). Possessing specific powers and impulses of approx 100 kW/kg and 200-300 kilosecs, IFRs will usher in the era of the true Solar System class spaceship. Even Pluto will be accessible with roundtrip times of less than 2 years and starting masses of about 1500 m tons.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AAS PAPER 87-210
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