中国空间科学技术

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返回式卫星烧蚀防热结构的工程计算

邢连群   

  1. 北京空间飞行器总体设计部
  • 发布日期:1991-04-25

AN ENGINEERING COMPUTATION OF ABLATIVE THERMAL PROTECTION STRUCTURE OF RETURNABLE SATELLITE

Xing Lianqun (Beijing Institute of Spacecraft Systems Engineering)   

  • Published:1991-04-25

摘要： 叙述了一种返回式卫星的烧蚀防热结构形式,对FL复合材料、硅橡胶的烧蚀机理及计算方法进行了论述,并与飞行试验结果进行了比较,给出了结论性的意见。

关键词: 可回收卫星, 防热结构, 烧蚀材料, 计算

Abstract: The paper describes one of the ablative thermal protection struc- tures of a returnable satellite,and discusses the ablation mechanism and the computation method of the FL composite material and siliconerubber, and compares the results with those of test.Finally the paper gives a conclu- sire idea.