硬X射线调制望远镜卫星热设计及验证  

HXMT Satellite Thermal Control Design and Verification

作　　者：周宇鹏[1] 赵欣[1] 周晓云 孙腾飞[1] 崔丽萍[1] 严利娟 ZHOU Yupeng;ZHAO Xin;ZHOU Xiaoyun;SUN Tengfei;CUI Liping;YAN Lijuan(Beijing Key Laboratory of Space Thermal Control Technology,Beijing Institute of Spacecraft System Engineering,Beijing 100094,China;Beijing Spacecrafts,Beijing 100094,China)

机构地区：[1]北京空间飞行器总体设计部,空间热控技术北京市重点实验室,北京100094 [2]北京卫星制造厂有限公司,北京100094

出　　处：《航天器工程》2018年第5期95-101,共7页Spacecraft Engineering

基　　金：国家重大航天工程。

摘　　要：针对硬X射线调制望远镜(HXMT)卫星轨道外热流环境恶劣、变化极其复杂、多载荷一体结构安装布局的热设计难点,结合天文探测卫星的轨道与姿态特点给出了其外热流分析结果和典型极端工况的选取依据,全面总结了整个型号热控研制过程中以乙烷深冷热管技术为代表的被动低温热设计特点及经验,介绍了望远镜载荷复杂凹表面传热系统的试验模拟验证方法及经验,对整星及望远镜载荷热性能的在轨飞行验证进行了总结和评价。In order to overcome the HXMT(hard X-ray modulation telescope)satellite thermal control design difficulties which include the extreme outside heat flux and the integrative configuration with multi-telescope loads,the characteristics of external heat flux and the selection rules of typical extreme conditions for the specific attitude of astronomical satellite observation mode have been analyzed in this paper.The characteristics and experiences in the whole project process of passive cryogenic temperature thermal control design base of ethane heat pipe technique have been presented.The testing verification technique and experiences of the heat transfer system of the telescope complicated concave surface have been presented.The in-orbit thermal control performances for platform and load have been summarized.

关 键 词：硬X射线调制望远镜卫星 外热流分析 热设计 乙烷深冷热管 飞行验证 

分 类 号：V416[航空宇航科学与技术—航空宇航推进理论与工程]