摘要
介绍我国返回式卫星热控设计方案。根据我国返回式卫星的特点,描述了热惯性法在热设计中的应用。地面热试验数据与飞行遥测温度数据比较表明,两者一致性良好,热控系统工作正常,星体与星内仪器温度均较好地处于所要求的范围内。
This paper presents the thermal control subsystem of chinese returnable satellite. According to the characteristics of the satellite, a method of thermal inertia used in thermal design is described.The temperatures obtained from orbit telemetry data are in agreement with that from ground testing.Thermal control subsystem operated well the temperatures of the structure and the equipments met the design requirement.
出处
《中国空间科学技术》
EI
CSCD
北大核心
1990年第6期49-56,共8页
Chinese Space Science and Technology
关键词
卫星
返回式
热动力试验
热分析
Recoverable satellite
Temperature control
Thermodynamic test
Thermal analysis
Design
