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李希伦
发布日期:
Li XiLun (Beijing Institute of Spacecraft Systems Engineering)
Published:
摘要： 我国的一种返回式卫星发射时未设整流罩,星体直接受到气动加热。利用热惯性法进行主动段热控设计,理论计算值、试验值均未超过飞行测量数据,说明设计和计算是合理的。
关键词: 气动加热, 卫星温度, 热分析
Abstract: This paper discusses the problem of aerodynamics heat of non-fairinged satellite.The method of heat-inertia in launching phase,is usedin thermal control design.The theoretical data,test data and flight data are identical with eachother.It shows that the design is very successful.
李希伦. 返回式卫星主动段热控设计[J]. .
Li XiLun (Beijing Institute of Spacecraft Systems Engineering). THERMAL CONTROL DESIGN OF RETURNABLE SATELLITE IN LAUNCHING PHASE[J]. .
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http://zgkj.cast.cn/CN/Y1991/V11/I04/67
