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  • Other Sources  (693)
  • Spacecraft Propulsion and Power  (555)
  • AERODYNAMICS
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  • 1995-1999  (655)
  • 1940-1944  (25)
  • 1930-1934  (13)
  • 1
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    Hypersonic aerodynamics test facility using the external propulsion accelerator (1995)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: The use of the External propulsion Accelerator (EPA) for launching models of hypersonic aerodynamic configurations into an instrumented ballistic range is discussed. The aerodynamic model is encased inside an axisymmetric projectile designed to be accelerated to high speed in the EPA. Accelerator lengths required to achieve hypersonic speeds are estimated to vary from 10 meters for Mach 7, 40 meters for Mach 10, 150 meters for Mach 15, and 700 meters for Mach 30, assuming a limit of 50,000 g's acceleration. For a model span of 10 cm to 25 cm, the launch tube diameters are 40 cm and 100 cm, respectively. Using this EPA launcher will enable exact simulation of hypersonic flight in ground facilities where both the gas composition and pressure can be controlled in the ballistic range.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 95-6138 , AIAA, Aerospace Planes and Hypersonics Technologies Conference; Apr 03, 1995 - Apr 07, 1995; Chattanooga, TN; United States|; 5 p.
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  • 2
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    Solar Powered Propulsion for Space. (Latest citations from the Aerospace Database) (1998)
    In:  Other Sources
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    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
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  • 3
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    Method and apparatus for pressure pulse arcjet starting (1996)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The invention disclosed is directed to a method and apparatus for an arcjet starter. The invention discloses a method of moving an arc from the subsonic region of the thruster to the supersonic region by introducing a pressurized propellant into the casuty of the anode.
    Keywords: Spacecraft Propulsion and Power
    Format: application/pdf
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  • 4
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    Engineering design aspects of the heat-pipe power system (1997)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: The Heat-pipe Power System (HPS) is a near-term, low-cost space power system designed at Los Alamos that can provide up to 1,000 kWt for many space nuclear applications. The design of the reactor is simple, modular, and adaptable. The basic design allows for the use of a variety of power conversion systems and reactor materials (including the fuel, clad, and heat pipes). This paper describes a project that was undertaken to develop a database supporting many engineering aspects of the HPS design. The specific tasks discussed in this paper are: the development of an HPS materials database, the creation of finite element models that will allow a wide variety of investigations, and the verification of past calculations.
    Keywords: Spacecraft Propulsion and Power
    Type: DE98-003307 , LA-UR-97-4364 , United States
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  • 5
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    Scramjet thrust measurement in a shock tunnel (1995)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: This note reports tests in a shock tunnel in which a fully integrated scamjet configuration produced net thrust. The experiments not only showed that impluse facilities can be used for assessing thrust performance, but also were a demonstration of the application of a new technique to the measurement of thrust on scramjet configurations in shock tunnels. These two developments are of significance because scramjets are expected to operate at speeds well in excess of 2 km/s, and shock tunnels offer a means of generating high Mach number flows at such speeds.
    Keywords: AERODYNAMICS
    Type: Aeronautical Journal (ISSN 0001-9240); 99; 984; p. 161-163
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  • 6
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    Anti-Matter Propulsion for Space. (Latest citations from the Aerospace Database) (1998)
    In:  Other Sources
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    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
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  • 7
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    Space Power Requirements for Future NASA Missions (1996)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: The key technology issues for the power requirements of future NASA space missions are: reduction in mass to enable smaller launch vehicles, faster trip time and lower cost; simpler more autonomous operations to reduce life cycle cost; reduce design, development , and qualification time to enable frequent low-cost missions; increase payload fraction and science return; enable next generation missions; stimulate U.S. industry to promote strong world leadership capability; and incorporate dual-use strategy into technology development.
    Keywords: Spacecraft Propulsion and Power
    Type: The 1995 NASA Aerospace Battery Workshop; 3-12; NASA-CP-3325
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  • 8
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    Raman Spectroscopy for Instantaneous Multipoint, Multispecies Gas Concentration and Temperature Measurements in Rocket Engine Propellant Injector Flows (1999)
    In:  Other Sources
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    Publication Date: 2019-08-17
    Description: Propellent injector development at MSFC includes experimental analysis using optical techniques, such as Raman, fluorescence, or Mie scattering. For the application of spontaneous Raman scattering to hydrocarbon-fueled flows a technique needs to be developed to remove the interfering polycyclic aromatic hydrocarbon fluorescence from the relatively weak Raman signals. A current application of such a technique is to the analysis of the mixing and combustion performance of multijet, impinging-jet candidate fuel injectors for the baseline Mars ascent engine, which will bum methane and liquid oxygen produced in-situ on Mars to reduce the propellent mass transported to Mars for future manned Mars missions. The present technique takes advantage of the strongly polarized nature of Raman scattering. It is shown to be discernable from unpolarized fluorescence interference by subtracting one polarized image from another. Both of these polarized images are obtained from a single laser pulse by using a polarization-separating calcite rhomb mounted in the imaging spectrograph. A demonstration in a propane-air flame is presented.
    Keywords: Spacecraft Propulsion and Power
    Type: 1999 NASA/ASEE Summer Faculty Fellowship Program; D-48
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  • 9
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    Planetary and Deep Space Requirements for Photovoltaic Solar Arrays (1995)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: In the past 25 years, the majority of interplanetary spacecraft have been powered by nuclear sources. However, as the emphasis on smaller, low cost missions gains momentum, more deep space missions now being planned have baselined photovoltaic solar arrays due to the low power requirements (usually significantly less than 100 W) needed for engineering and science payloads. This will present challenges to the solar array builders, inasmuch as planetary requirements usually differ from earth orbital requirements. In addition, these requirements often differ greatly, depending on the specific mission; for example, inner planets vs. outer planets, orbiters vs. flybys, spacecraft vs. landers, and so on. Also, the likelihood of electric propulsion missions will influence the requirements placed on solar array developers. This paper will discuss representative requirements for a range of planetary and deep space science missions now in the planning stages. We have divided the requirements into three categories: Inner planets and the sun; outer planets (greater than 3 AU); and Mars, cometary, and asteroid landers and probes. Requirements for Mercury and Ganymede landers will be covered in the Inner and Outer Planets sections with their respective orbiters. We will also discuss special requirements associated with solar electric propulsion (SEP). New technology developments will be needed to meet the demanding environments presented by these future applications as many of the technologies envisioned have not yet been demonstrated. In addition, new technologies that will be needed reside not only in the photovoltaic solar array, but also in other spacecraft systems that are key to operating the spacecraft reliably with the photovoltaics.
    Keywords: Spacecraft Propulsion and Power
    Type: Space Photovoltaic Research and Technology 1995; 2-9; NASA-CP-10180
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  • 10
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    Metallographic Analysis of Brush Bristle and Integrity Testing of Brush Seal in Shroud Ring of T-700 Engine (1995)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Post-test investigation of a T-700 engine brush seal found regions void of bristles ('yanked out'), regions of bent-over bristles near the inlet, some 'snapped' bristles near the fence, and a more uniform 'smeared' bristle interface between the first and last axial rows of bristles. Several bristles were cut from the brush seal, wax mounted, polished, and analyzed. Metallographic analysis of the bristles near the rub tip showed tungsten-rich phases uniformly distributed throughout the bristle with no apparent change within 1 to 2 micron of the interface except for possibly a small amount of titanium, which would represent a transfer from the rotor. Analysis of the bristle wear face showed nonuniform tungsten, which is indicative of material resolidification. The cut end contained oxides and internal fractures; the worn end was covered with oxide scale. Material losses due to wear and elastoplastic deformation within the shear zone and third-body lubrication effects in the contact zone are discussed.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA-TM-106361 , ARL-MR-119 , E-8155 , NAS 1.15:106361 , International Symposium on Transport Phenomena and Dynamics of Rotating Machinery; May 08, 1994 - May 11, 1994; Kaanapali, Maui, HI; United States
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