一种空间展开锁定机构锁定可靠性设计和计算方法  

Design and Calculation of Locking Reliability of Spatial Deployable Locking Mechanism

作　　者：沈军龙[1] 李洪超[1] Shen Junlong;Li Hongchao(NO.39 Research Insititute of CETC,Xi’an 710065,China)

机构地区：[1]中国电子科技集团公司第39研究所,西安710065

出　　处：《测控与通信》2020年第2期20-22,共3页

摘　　要：受卫星整流罩尺寸限制,大尺寸有效栽荷通常采用可展开结构形式或者借助伸展臂实现整体收展,以满足装星尺寸要求。无论采用哪种方式,都需要使用到展开锁定机构。本文通过设计计算、仿真分析与试验验证,给出了1种空间展开锁定机构的锁定可靠性设计和计算方法。Limited by the size of the satellite fairing,the large size payload usually adopts the form of deployable structure or the extension arm to achieve the overall spread,in order to meet the requirements of the size of the satellite.Either way,it needs to use an unlocking mechanism.By means of design calculation,simulation analysis and experimental verification,this paper presents the locking reliability design and calculation method of a space deployable locking mechanism.

关 键 词：锁定机构 可靠性 响应时间 

分 类 号：TP3[自动化与计算机技术—计算机科学与技术]