北京航空航天大学学报 ›› 2003, Vol. 29 ›› Issue (5): 463-466.

• 论文 • 上一篇    下一篇

某火箭三子级剩余推进剂汽化研究

孙冰1, 方杰1, 张化照2, 张福忠2   

  1. 1. 北京航空航天大学 宇航学院;
    2. 北京宇航系统工程研究所
  • 收稿日期:2003-01-23 发布日期:2003-05-25
  • 作者简介:孙 冰 (1960-),女,黑龙江罗北人,副教授,100083,北京.

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

Sun Bing1, Fang Jie1, Zhang Huazhao2, Zhang Fuzhong2   

  1. 1. School of Astronautics, Beijing University of Aeronautics and As tronautics;
    2. Beijing Institute of Astronautical Systems Engineering
  • Received:2003-01-23 Published:2003-05-25

摘要: 针对某火箭三子级剩余推进剂的汽化过程,建立了一个零维的数学物理模型.在给定太阳辐 射角的工况下,对贮箱中低温液体推进剂汽化时,贮箱内气体温度和压力变化、贮箱内质量 变化、进入贮箱的外界热流的变化及贮箱排放推力的变化等进行了数值计算,并对贮箱保险 活门排放推力对火箭在轨速度的极限影响作了简单分析.计算结果可进一步用于该火箭三子 级钝化技术的研究.

Abstract: 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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