某卫星真空热试验中一些新要求的解决措施  

SOME SPECIAL MEASURES TAKEN IN THERMAL BALANCE TEST OF A SATELLITE

作　　者：杨晓宁[1] 龚洁[1] 

机构地区：[1]北京卫星环境工程研究所,北京100094

出　　处：《航天器环境工程》2005年第2期100-104,共5页Spacecraft Environment Engineering

摘　　要：某卫星在进行真空热试验时,对热流提出了三个方面的新要求：(1)对某些热流要求较低的加热区的加热笼进行修改,提高其低热流实现能力；(2)减小支架漏热；(3)实时计算设计热流和实际热流的周期积分偏差。由于修改时的约束条件较多,新的要求的满足非常困难。经过努力,最终解决了这些问题,通过对某些加热笼采取加热带双面涂黑漆的方法,实现了低热流；经过计算和针对性的设计,支架漏热不超过0．1188W；同时实现了设计热流与实际热流周期积分偏差的实时计算。In the thermal balance test and thermal vacuum test of the certain satellite,three new requirements were put forward,i.e.(1) modifying some heating arrays,the heat flux requirements of which are relatively low,so as to improve their abilities of providing lower heat flux;(2) decreasing the heat leakage through the satellite supporting flange;(3)calculating integral deference between target heat flux and practical heat flux in real time.At last,all the problems have been solved.Low heat flux is provided by painting black lacquer on the both surfaces of heating belt of some heating arrays.The heat leakage of the satellite supporting flange is limited within 0.1188W through theoretical analysis and specific design.At the same time,the integral error between target heat flux and practical heat flux is calculated in real time.

关 键 词：控温 红外加热笼 设计热流 热流积分 

分 类 号：V416.5[航空宇航科学与技术—航空宇航推进理论与工程]