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  • 1
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    Propulsion simulator for magnetically-suspended wind tunnel models (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The objective of phase two of a current investigation sponsored by NASA Langley Research Center is to demonstrate the measurement of aerodynamic forces/moments, including the effects of exhaust gases, in magnetic suspension and balance system (MSBS) wind tunnels. Two propulsion simulator models are being developed: a small-scale and a large-scale unit, both employing compressed, liquified carbon dioxide as propellant. The small-scale unit was designed, fabricated, and statically-tested at Physical Sciences Inc. (PSI). The large-scale simulator is currently in the preliminary design stage. The small-scale simulator design/development is presented, and the data from its static firing on a thrust stand are discussed. The analysis of this data provides important information for the design of the large-scale unit. A description of the preliminary design of the device is also presented.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Aerospace Applications of Magnetic Suspension Technology, Part 1; p 249-280
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Laser-driven hypersonic air-breathing propulsion simulator (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A feasibility study is presented of simulating airbreathing propulsion on small scale hypersonic models using laser energy. The laser heat addition scheme allows simultaneous inlet and exhaust flows during wind tunnel testing of models with scramjet models. The proposed propulsion simulation concept has extended the Kantrowitz (1974) idea to propulsive wind tunnel models of hypersonic aircraft. Critical issues in aeropropulsive testing of models based on a ramjet power plant are addressed which include transfer of the correct amount of energy to the flowing gas, efficient absorption of laser energy into the gas, and test performance under tunnel reservoir conditions and at reasonable Reynolds numbers.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AIAA PAPER 92-3922
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Green Liquid Monopropellant Thruster (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-06
    Description: Physical Sciences, Inc. (PSI), and Orbital Technologies Corporation (ORBITEC) are developing a unique chemical propulsion system for next-generation NASA science spacecraft and missions. The system is compact, lightweight, and can operate with high reliability over extended periods of time and under a wide range of thermal environments. The system uses a new storable, low-toxicity liquid monopropellant as its working fluid. In Phase I, the team demonstrated experimentally the critical ignition and combustion processes for the propellant and used the data to develop thruster design concepts. In Phase II, the team developed and demonstrated in the laboratory a proof-of-concept prototype thruster. A Phase III project is envisioned to develop a full-scale protoflight propulsion system applicable to a class of NASA missions.
    Keywords: Propellants and Fuels; Spacecraft Propulsion and Power; Engineering (General)
    Type: An Overview of SBIR Phase 2 In-Space Propulsion and Cryogenic Fluids Management; 13; NASA/TM-2015-218829
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Propulsion simulation for magnetically suspended wind tunnel models (1990)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The feasibility of simulating propulsion-induced aerodynamic effects on scaled aircraft models in wind tunnels employing Magnetic Suspension and Balance Systems. The investigation concerned itself with techniques of generating exhaust jets of appropriate characteristics. The objectives were to: (1) define thrust and mass flow requirements of jets; (2) evaluate techniques for generating propulsive gas within volume limitations imposed by magnetically-suspended models; (3) conduct simple diagnostic experiments for techniques involving new concepts; and (4) recommend experiments for demonstration of propulsion simulation techniques. Various techniques of generating exhaust jets of appropriate characteristics were evaluated on scaled aircraft models in wind tunnels with MSBS. Four concepts of remotely-operated propulsion simulators were examined. Three conceptual designs involving innovative adaptation of convenient technologies (compressed gas cylinders, liquid, and solid propellants) were developed. The fourth innovative concept, namely, the laser-assisted thruster, which can potentially simulate both inlet and exhaust flows, was found to require very high power levels for small thrust levels.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: NASA-CR-182093 , NAS 1.26:182093 , PSI-2055/TR-859
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Fast Ignition and Sustained Combustion of Ionic Liquids (2016)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: A catalyst free method of igniting an ionic liquid is provided. The method can include mixing a liquid hypergol with a HAN (Hydroxylammonium nitrate)-based ionic liquid to ignite the HAN-based ionic liquid in the absence of a catalyst. The HAN-based ionic liquid and the liquid hypergol can be injected into a combustion chamber. The HAN-based ionic liquid and the liquid hypergol can impinge upon a stagnation plate positioned at top portion of the combustion chamber.
    Keywords: Inorganic, Organic and Physical Chemistry
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Variable Absorptance and Emittance Devices for Thermal Control (2008)
    American Chemical Society
    Details
    Publication Date: 2008-01-01
    Print ISSN: 1932-7447
    Electronic ISSN: 1932-7455
    Topics: Chemistry and Pharmacology
    Published by American Chemical Society
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