航天器工程2019，Vol.28Issue(1)：77-83,7.DOI:10.3969/j.issn.1673-8748.2019.01.011
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
张晓峰 1赵璇 2诸成 1冯建朝 1刘红 1吴立1
作者信息
- 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
- 折叠
摘要
Abstract
According the functional limitation and reliability risk of thermal control design for de-ployable 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 de-ployment 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Key words
spacecraft/deployment mechanism/ITCM/thermal analysis分类
航空航天引用本文复制引用
张晓峰,赵璇,诸成,冯建朝,刘红,吴立..航天器展开机构间接式主动热控设计方法[J].航天器工程,2019,28(1):77-83,7.
