用于空间聚光结构的折展机构设计与分析  

Design and analysis of a deployable mechanism for space condensation structure

作　　者：李季[1] 邢利娜[1] 

机构地区：[1]中国科学院长春光学精密机械与物理研究所小卫星技术国家地方联合工程研究中心,吉林长春130033

出　　处：《红外与激光工程》2014年第B12期36-42,共7页Infrared and Laser Engineering

基　　金：国家863项目(2012AA121502)

摘　　要：针对空间太阳能电站大口径聚光结构的应用需求与运载条件相矛盾的情况,以离轴式聚光系统为研究基础,设计了一种具有折叠展开功能的次镜支撑机构。机构采用三关节串联结构为主,两组平行四杆机构为辅,可实现水平、竖直的两次展开,并能保证次镜组件在展开过程中始终保持平动状态。通过建立机构折展的运动学方程,对机构的工作空间进行了求解,规划了展开方案;对机构展开的位置、姿态精度进行了研究,分析了展开精度对机构各结构参数的敏感度;最后,在ADAMS软件中建立了折展机构的虚拟样机,对展开过程进行了仿真,验证了机构设计的正确性与合理性。Aimed at solving the contradiction between the need of large diameter condensation structure for Space Power System and the limitation of the current carrying capacity, a deployable mechanism for the secondary mirror support was designed, based on a two-mirror off-axis condensation system. The major configuration of the deployment mechanism was made of a three-link serial mechanism, with two parallel four-bar mechanisms, which can deploy in the horizontal and vertical directions separately, and ensure that the secondary mirror component remains translational movement during the mechanism deployment. Kinematics equation of deployment was deduced, and the work space was solved to plan the scheme of the mechanism deployment. The position precision and attitude accuracy of the deployment was studied, and the sensitivity of structure parameters was given. Finally, the virtual prototype of the mechanism was built with ADAMS software, and the deployment was simulated to verify the correctness and rationality of the design.

关 键 词：空间太阳能电站 聚光结构 次镜支撑 折展机构 

分 类 号：V11[航空宇航科学与技术—人机与环境工程]