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Volume 25 Issue 6
Jun.  1999
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Journal of Beijing University of Aeronautics and Astronautics  > 1999  >  25(6): 688-691.
Zhang Guozhou. Transient Analysis of a Divert Thruster for Micropropulsion Systems[J]. Journal of Beijing University of Aeronautics and Astronautics, 1999, 25(6): 688-691. (in Chinese)
Citation: Zhang Guozhou. Transient Analysis of a Divert Thruster for Micropropulsion Systems[J]. Journal of Beijing University of Aeronautics and Astronautics, 1999, 25(6): 688-691. (in Chinese)
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Transient Analysis of a Divert Thruster for Micropropulsion Systems

  • Beijing University of Aeronautics and Astronautics,School of Astronautics

  • Received Date: 20 May 1999
  • Publish Date: 30 Jun 1999
    Abstract
  • In the past several years, the miniaturization of Liquid Rocket Propulsion Systems advanced tremendously. The advanced micropropulsion systems are characterized by the miniaturization, high pressure and fast response. For these micropropulsion systems, the mathematical models of components are derived and gathered together. For the divert thruster of micropropulsion system, the variation of the combustion chamber pressure during impulse working and the pressure variation during closing the divert valve are investigated and analysed. It provides a basis for research of the dynamic response of the whole micropropulsion system.

     

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    • References(1)
  • 1. Acampora K J, Wichmann H. Component development for micropropulsion systems. AIAA 92-3255,1992 2. Prickett R P,Mayer E, Hermel J. Water hammer in a spacecraft propellant feed system. Journal of Propulsion and Power, 1992,8 (3):592~597 3. 陈新华,沈赤兵．空间拦截器动力系统小推力高压燃烧室特性研究.指挥技术学院学报,1997(4) 4. Lin T Y, Baker D. Analysis and testing of propellant feed system priming process. Journal of Propulsion and Power, 1995,11 (3):505~512
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