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  • Other Sources  (235)
  • Spacecraft Propulsion and Power  (128)
  • AERODYNAMICS
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  • 2000-2004
  • 1995-1999  (235)
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  • 1998  (235)
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  • Other Sources  (235)
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  • 2000-2004
  • 1995-1999  (235)
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  • 1
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    Solar Powered Propulsion for Space. (Latest citations from the Aerospace Database) (1998)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: The bibliography contains citations concerning the design, development, and performance of solar propulsion systems. Solar electric propulsion and solar thermal propulsion are reviewed. Topics include solar power satellites, nuclear electric propulsion, solar-powered orbit transfer vehicles, and solar dynamic and bimodal power systems. References also discuss atmospheric pollution control, telephone services, space commercialization, interplanetary missions, and lunar and Mars exploration. (Contains 50-250 citations and includes a subject term index and title list.)
    Keywords: Spacecraft Propulsion and Power
    Type: PB98-852858
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Anti-Matter Propulsion for Space. (Latest citations from the Aerospace Database) (1998)
    In:  Other Sources
    Details
    Publication Date: 2019-08-27
    Description: The bibliography contains citations concerning techniques for the efficient production, long-term storage and effective utilization of antimatter for space propulsion. Inertial confinement fusion (ICF), magnetic mirror fusion, and liquid-propellant thermal antimatter fusion propulsion are some of the technologies discussed. Radiation shields, cryogenic confinement of plasma and single-stage-to-orbit vehicles are also cited. (Contains 50-250 citations and includes a subject term index and title list.)
    Keywords: Spacecraft Propulsion and Power
    Type: PB98-852056
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Reducing the risk to Mars: The gas core nuclear rocket (1998)
    In:  Other Sources
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    Publication Date: 2019-08-16
    Description: The next giant leap for mankind will be the human exploration of Mars. Almost certainly within the next thirty years, a human crew will brave the isolation, the radiation, and the lack of gravity to walk on and explore the Red planet. However, because the mission distances and duration will be hundreds of times greater than the lunar missions, a human crew will face much greater obstacles and a higher risk than those experienced during the Apollo program. A single solution to many of these obstacles is to dramatically decrease the mission duration by developing a high performance propulsion system. The gas-core nuclear rocket (GCNR) has the potential to be such a system. The authors have completed a comparative study of the potential impact that a GCNR could have on a manned Mars mission. The total IMLEO, transit times, and accumulated radiation dose to the crew will be compared with the NASA Design Reference Missions.
    Keywords: Spacecraft Propulsion and Power
    Type: LA-UR-97-3361 , CONF-980103 , DE98-001449 , Space Technology and Applications International Forum; Jan 25, 1998 - Jan 29, 1998; Albuquerque, NM; United States
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    NASA TECHNICAL REPORTS
  • 4
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    Nuclear modules for space electric propulsion (1998)
    In:  Other Sources
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    Publication Date: 2019-08-15
    Description: Analysis of interplanetary cargo and piloted missions requires calculations of the performances and masses of subsystems to be integrated in a final design. In a preliminary and scoping stage the designer needs to evaluate options iteratively by using fast computer simulations. The Oak Ridge National Laboratory (ORNL) has been involved in the development of models and calculational procedures for the analysis (neutronic and thermal hydraulic) of power sources for nuclear electric propulsion. The nuclear modules will be integrated into the whole simulation of the nuclear electric propulsion system. The vehicles use either a Brayton direct-conversion cycle, using the heated helium from a NERVA-type reactor, or a potassium Rankine cycle, with the working fluid heated on the secondary side of a heat exchanger and lithium on the primary side coming from a fast reactor. Given a set of input conditions, the codes calculate composition. dimensions, volumes, and masses of the core, reflector, control system, pressure vessel, neutron and gamma shields, as well as the thermal hydraulic conditions of the coolant, clad and fuel. Input conditions are power, core life, pressure and temperature of the coolant at the inlet of the core, either the temperature of the coolant at the outlet of the core or the coolant mass flow and the fluences and integrated doses at the cargo area. Using state-of-the-art neutron cross sections and transport codes, a database was created for the neutronic performance of both reactor designs. The free parameters of the models are the moderator/fuel mass ratio for the NERVA reactor and the enrichment and the pitch of the lattice for the fast reactor. Reactivity and energy balance equations are simultaneously solved to find the reactor design. Thermalhydraulic conditions are calculated by solving the one-dimensional versions of the equations of conservation of mass, energy, and momentum with compressible flow.
    Keywords: Spacecraft Propulsion and Power
    Type: CONF-980103-1 , DE97-009366 , Space Technology and Applications International Forum; Jan 25, 1998 - Jan 29, 1998; Albuquerque, NM; United States
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    NASA TECHNICAL REPORTS
  • 5
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    Propulsion/ASME Rocket-Based Combined Cycle Activities in the Advanced Space Transportation Program Office (1998)
    In:  Other Sources
    Details
    Publication Date: 2019-08-13
    Description: NASA's Office Of Aeronautics and Space Transportation Technology (OASTT) has establish three major coals. "The Three Pillars for Success". The Advanced Space Transportation Program Office (ASTP) at the NASA's Marshall Space Flight Center in Huntsville,Ala. focuses on future space transportation technologies under the "Access to Space" pillar. The Advanced Reusable Technologies (ART) Project, part of ASTP, focuses on the reusable technologies beyond those being pursued by X-33. The main activity over the past two and a half years has been on advancing the rocket-based combined cycle (RBCC) technologies. In June of last year, activities for reusable launch vehicle (RLV) airframe and propulsion technologies were initiated. These activities focus primarily on those technologies that support the year 2000 decision to determine the path this country will take for Space Shuttle and RLV. In February of this year, additional technology efforts in the reusable technologies were awarded. The RBCC effort that was completed early this year was the initial step leading to flight demonstrations of the technology for space launch vehicle propulsion. Aerojet, Boeing-Rocketdyne and Pratt & Whitney were selected for a two-year period to design, build and ground test their RBCC engine concepts. In addition, ASTROX, Pennsylvania State University (PSU) and University of Alabama in Huntsville also conducted supporting activities. The activity included ground testing of components (e.g., injectors, thrusters, ejectors and inlets) and integrated flowpaths. An area that has caused a large amount of difficulty in the testing efforts is the means of initiating the rocket combustion process. All three of the prime contractors above were using silane (SiH4) for ignition of the thrusters. This follows from the successful use of silane in the NASP program for scramjet ignition. However, difficulties were immediately encountered when silane (an 80/20 mixture of hydrogen/silane) was used for rocket ignition.
    Keywords: Spacecraft Propulsion and Power
    Type: Interagency Propulsion Committee; Dec 07, 1998 - Dec 11, 1998; Tucson, AZ; United States
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    NASA TECHNICAL REPORTS
  • 6
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    RSRM Nozzle Anomalous Throat Erosion Investigation Overview (1998)
    In:  Other Sources
    Details
    Publication Date: 2019-08-13
    Description: In September, 1996, anomalous pocketing erosion was observed in the aft end of the throat ring of the nozzle of one of the reusable solid rocket motors (RSRM 56B) used on NASA's space transportation system (STS) mission 79. The RSRM throat ring is constructed of bias tape-wrapped carbon cloth/ phenolic (CCP) ablative material. A comprehensive investigation revealed necessary and sufficient conditions for occurrence of the pocketing event and provided rationale that the solid rocket motors for the subsequent mission, STS-80, were safe to fly. The nozzles of both of these motors also exhibited anomalous erosion similar to, but less extensive than that observed on STS-79. Subsequent to this flight, the investigation to identify both the specific causes and the corrective actions for elimination of the necessary and sufficient conditions for the pocketing erosion was intensified. A detailed fault tree approach was utilized to examine potential material and process contributors to the anomalous performance. The investigation involved extensive constituent and component material property testing, pedigree assessments, supplier audits, process audits, full scale processing test article fabrication and evaluation, thermal and thermostructural analyses, nondestructive evaluation, and material performance tests conducted using hot fire simulation in laboratory test beds and subscale and full scale solid rocket motor static test firings. This presentation will provide an over-view of the observed anomalous nozzle erosion and the comprehensive, fault-tree based investigation conducted to resolve this issue.
    Keywords: Spacecraft Propulsion and Power
    Type: Rocket Nozzle Technology; Mar 15, 1998 - Mar 20, 1998; Salt Lake City, UT; United States
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    NASA TECHNICAL REPORTS
  • 7
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    Mixing of Supersonic Streams (1998)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The Strutjet approach to Rocket Based Combined Cycle (RBCC) propulsion depends upon fuel-rich flows from the rocket nozzles and turbine exhaust products mixing with the ingested air for successful operation in the ramjet and scramjet modes. It is desirable to delay this mixing process in the air-augmented mode of operation present during low speed flight. A model of the Strutjet device has been built and is undergoing test to investigate the mixing of the streams as a function of distance from the Strutjet exit plane during simulated low speed flight conditions. Cold flow testing of a 1/6 scale Strutjet model is underway and nearing completion. Planar Laser Induced Fluorescence (PLIF) diagnostic methods are being employed to observe the mixing of the turbine exhaust gas with the gases from both the primary rockets and the ingested air simulating low speed, air augmented operation of the RBCC. The ratio of the pressure in the turbine exhaust duct to that in the rocket nozzle wall at the point of their intersection is the independent variable in these experiments. Tests were accomplished at values of 1.0, 1.5 and 2.0 for this parameter. Qualitative results illustrate the development of the mixing zone from the exit plane of the model to a distance of about 10 rocket nozzle exit diameters downstream. These data show the mixing to be confined in the vertical plane for all cases, The lateral expansion is more pronounced at a pressure ratio of 1.0 and suggests that mixing with the ingested flow would be likely beginning at a distance of 7 nozzle exit diameters downstream of the nozzle exit plane.
    Keywords: Spacecraft Propulsion and Power
    Type: Dec 07, 1998 - Dec 11, 1998; Tucson, AZ; United States
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    NASA TECHNICAL REPORTS
  • 8
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    Rocketdyne Advanced Reusable Technologies Program Update (1998)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: NASA Marshall Space Flight Center Advanced Reusable Technologies/Rocket Based Combined Cycle (RBCC) program has enabled: (1) the creation of unique trajectory simulation facility; (2) development of basic operability and performance data; (3) results to date: (a) rocket thrusters performing as designed (P(sub c), MR, q, etc); (b) AAR performance data measured at M = 0 and 3; (c) rocket mode performance at simulated vacuum conditions; and (d) data reduction in progress; (4) completing testing; M = 0, 3 and trajectory M = 3 to 3.7; and (5) next logical steps: build flight type engine and flight demonstrate RBCC.
    Keywords: Spacecraft Propulsion and Power
    Type: Jul 16, 1998 - Jul 17, 1998; Cleveland, OH; United States
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    NASA TECHNICAL REPORTS
  • 9
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    Impact of Radiation Hardness and Operating Temperatures of Silicon Carbide Electronics on Space Power System Mass (1998)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The effect of silicon carbide (SiC) electronics operating temperatures on Power Management and Distribution (PMAD), or Power Conditioning (PC), subsystem radiator size and mass requirements was evaluated for three power output levels (100 kW(e) , 1 MW(e), and 10 MW(e)) for near term technology ( i.e. 1500 K turbine inlet temperature) Closed Cycle Gas Turbine (CCGT) power systems with a High Temperature Gas Reactor (HTGR) heat source. The study was conducted for assumed PC radiator temperatures ranging from 370 to 845 K and for three scenarios of electrical energy to heat conversion levels which needed to be rejected to space by means of the PC radiator. In addition, during part of the study the radiation hardness of the PC electronics was varied at a fixed separation distance to estimate its effect on the mass of the instrument rated reactor shadow shield. With both the PC radiator and the conical shadow shield representing major components of the overall power system the influence of the above on total power system mass was also determined. As expected, results show that the greatest actual mass savings achieved by the use of SiC electronics occur with high capacity power systems. Moreover, raising the PC radiator temperature above 600 K yields only small additional system mass savings. The effect of increased radiation hardness on total system mass is to reduce system mass by virtue of lowering the shield mass.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/TM-1998-208826 , E-11453 , NAS 1.15:208826 , Space Technology and Applications; Jan 31, 1999 - Feb 04, 1999; Albuquerque, NM; United States
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    NASA TECHNICAL REPORTS
  • 10
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    Subsystem Analysis/Optimization for the X-34 Main Propulsion System (1998)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The Orbital Sciences Corporation X-34 vehicle demonstrates technologies and operations key to future reusable launch vehicles. The general flight performance goal of this unmanned rocket plane is Mach 8 flight at an altitude of 250,000 feet. The Main Propulsion System (MPS) supplies liquid propellants to the main engine, which provides the primary thrust for attaining mission goals. Major MPS design and operational goals are aircraft-like ground operations, quick turnaround between missions, and low initial/operational costs. Analyses related to optimal MPS subsystem design are reviewed in this paper. A pressurization system trade weighs maintenance/reliability concerns against those for safety in a comparison of designs using pressure regulators versus orifices to control pressurant flow. A propellant dump/feed system analysis weighs the issues of maximum allowable vehicle landing weight, trajectory, and MPS complexity to arrive at a final configuration for propellant dump/feed systems.
    Keywords: Spacecraft Propulsion and Power
    Type: AIAA Paper 98-4827 , Multidisciplinary Analysis and Optimization; Sep 02, 1998 - Sep 04, 1998; Saint Louis, MO; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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