航天器展开机构间接式主动热控设计方法  

Indirect Active Thermal Control Design Method for Spacecraft Deployment Mechanism

作　　者：张晓峰[1,2] 赵璇[1] 诸成 冯建朝[1] 刘红 吴立[1] ZHANG Xiaofeng;ZHAO Xuan;ZHU Cheng;FENG Jianchao;LIU Hong;WU Li(Shanghai Engineering Center for Microsatellite,Shanghai 201210,China;Harbin Institute of Technology,Harbin 150001,China)

机构地区：[1]上海微小卫星工程中心,上海201210 [2]哈尔滨工业大学,哈尔滨150001

出　　处：《航天器工程》2019年第1期77-83,共7页Spacecraft Engineering

摘　　要：针对目前航天器展开机构直接热控实施的功能局限性和可靠性风险的问题,提出了一种采用间接控制点控制目标点温度的设计方法,并以某卫星展开机构的热控设计为例,对关键机构部位的热控设计进行了阐述。仿真分析、地面热试验与在轨数据结果均表明:该间接热控设计方法能够满足机构产品的控温需求,展开机构的顺利展开验证了此方法的正确性和合理性,可为以后机构产品的热控设计提供借鉴。According the functional limitation and reliability risk of thermal control design for deployable spacecraft mechanism product,a design method of indirect thermal control(ITCM)is presented.Base on the technical requirements of the thermal control and the design scheme of the key position of the deployment mechanism,the indirect thermal control design is described.The results of simulation analysis,ground thermal test and on-orbit flight all show that the ITCM can meet the thermal-control requirements of the mechanism products,sucessfully work of the deployment mechanism verify its correctness and rationality,which can provide a design idea for the thermal control design of the mechanism products in the future.

关 键 词：航天器 展开机构 间接热控方法 热分析 

分 类 号：V444.3[航空宇航科学与技术—飞行器设计]