Volume 29 Issue 5
May  2003
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Sun Bing, Fang Jie, Zhang Huazhao, et al. Study on Residual Propellant Vaporized in Tank  of Some Launch Vehicle Third Stage[J]. Journal of Beijing University of Aeronautics and Astronautics, 2003, 29(5): 463-466. (in Chinese)
Citation: Sun Bing, Fang Jie, Zhang Huazhao, et al. Study on Residual Propellant Vaporized in Tank  of Some Launch Vehicle Third Stage[J]. Journal of Beijing University of Aeronautics and Astronautics, 2003, 29(5): 463-466. (in Chinese)

Study on Residual Propellant Vaporized in Tank  of Some Launch Vehicle Third Stage

  • Received Date: 23 Jan 2003
  • Publish Date: 31 May 2003
  • A zero-dimensional model was proposed to study on residual propellant vaporized in tank of some launch vehicle third stage. The assumptions used in the model and equations were given. By simulating the vaporization of cryogeni c propellant under given solar radiation angel, the variation of gas temperature, pressure and mass in tank, as well as ingoing heat flow and exhaust thrust, were calculated. A brief analysis of the rocket velocity change due to exhaust th rust shows the influence is inconsiderable, and the numerical results might be u seful to study the passivation technology of the launch vehicle further.

     

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