一种大角度大负载展收机构设计与优化  

Design and Optimization of a Big Angle and High Load Deployable Mechanism

作　　者：于春宇[1] 许怡贤 李林[1] 林秋红[1] YU Chunyu;XU Yixian;LI Lin;LIN Qiuhong(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：《载人航天》2016年第6期755-757,765,共4页Manned Spaceflight

基　　金：国家重大科技专项工程(2012AA7060802)

摘　　要：针对为实现交会对接系统可重复使用而产生的可展收防热装置设计需求,提出了一种双四连杆串联式防热罩展收机构,建立了ADAMS仿真模型,以大传动角、避免杆间重叠干涉以及展开位置死点自锁为约束条件,对展收机构的铰点位置和连杆长度等参数进行了优化设计,实现了四杆机构在死点位置时防热罩展开180°的几何特性,具有断电保持能力。通过对大惯量负载的驱动力分析,确定了最小驱动力矩(64.6 N·m)。可实现大角度、大负载重复展收。Rendezvous and D ocking (R V D ) is one of the most im portant functions of the new - generation manned spacecraft. In order to realize repeated use of the R V D equipm en t, a deployable therm alprotection mechanism is needed. A new type of deployable therm al protection mechanism w ith tandemdouble-fo u r-lin k s was presented in this paper. The sim ulation model based on A D A M S software was established.B ig transm ission a n g le , no overlapping interference between the rods and self-lockin g at thedead point position were set as the constraint conditions to optim ize the geometric parameters of the lin kbars. The therm al protection hatch could deploy to 180.at the “ dead p o in t” position of the lin k s andw ith the torque keeping fu n c tio n . The m inim um drive torque (64. 6 N *m ) was determ ined by large in e rtiaload analysis. The large angle and large load deploym ent and stowage was realized

关 键 词：大角度 展开机构 优化设计 ADAMS 

分 类 号：V19[航空宇航科学与技术—人机与环境工程]