硬X射线调制望远镜卫星及有效载荷环境条件设计与试验验证  

Environment Condition Design and Test Verification of HXMT Satellite and Payload

作　　者：刘欣[1] 张也弛[1] 王晓姝[1] 张龙[1] 元勇[1] LIU Xin;ZHANG Yechi;WANG Xiaoshu;ZHANG Long;YUAN Yong(Beijing Institute of Spacecraft System Engineering,Beijing 100094,China)

机构地区：[1]北京空间飞行器总体设计部,北京100094

出　　处：《航天器工程》2018年第5期40-45,共6页Spacecraft Engineering

基　　金：国家重大航天工程

摘　　要：分析了硬X射线调制望远镜(HXMT)卫星及有效载荷特性,采用基于"下凹"控制策略的环境条件制定方法,有效降低有效载荷界面振动力学环境条件达57%,避免了有效载荷"过设计";提出了有效载荷部件级试验与整星级试验相结合的考核方法,避免了有效载荷"过试验"的风险;针对HXMT卫星研制特点提出了整星级环境试验方案。通过卫星系统级环境试验及在轨飞行验证表明:卫星环境条件设计正确、试验设计合理,达到了考核卫星设计的效果。Environment design and test verification are the difficulties faced in the period of system design and realization of the HXMT(hard X-ray modulation telescope)satellite.Firstly,the characteristics of the satellite and payload are analyzed.The design load condition of payload is reduced by 57%through the method of‘concave’control method,and the risk of over-design is avoided.The risk of over-test of payload is avoided through component and system test.The system design plan is also proposed.The system verification proved that the design was correct and the product met the requirement.

关 键 词：硬X射线调制望远镜卫星 有效载荷特点 环境条件 

分 类 号：V41[航空宇航科学与技术—航空宇航推进理论与工程]