框架型柔性太阳电池阵展开机构动力学分析

Dynamic Analysis of Deployable Strut-mechanism for Flexible Solar Array

利用Kane法多体动力学基本理论,建立适用于空间框架型多模块柔性太阳电池阵的展开机构多体系统动力学模型,进行了框架型电池阵展开机构的展开方式和展开过程的仿真分析,并与ADAMS软件计算结果进行了对比,获得了机构组成部件在展开过程中的几何位置、速度、加速度等动力学特性,分析了框架展开机构各个铰接点受力的作用规律。结果表明:Kane法模型计算得到的单模块框架展开机构根铰转动规律与ADAMS分析结果基本相同,说明了Kane法建模的有效性和正确性;对于4模块框架展开机构,距离框架根部固定点越远的铰接点,其线速度和线加速度曲线在框架展开末期变化幅值越大;中间铰接点在展开初始状态所受的垂直于展开平面的作用力最大,在展开过程中逐渐减小;合理控制框架展开机构各运动部件的驱动力矩是保证框架按照确定规律展开的必要条件。研究结果可为空间框架型柔性太阳电池阵展开机构设计提供参考。

With Kane dynamic theory,the multi-body dynamic models of deployable strut-mechanism have been established.The deployable style and deployable process of the struts have been studied,and compared with the calculation results by ADAMS software.The dynamic performance of struts’deployment has been analyzed such as geometric position,velocity,and acceleration,and the inherent regularity of the forces of each hinge have been gained for deployable strut-mechanism.The results show that the rotation regularity of root-hinge calculated by the Kane method is basically the same as that of the ADAMS analysis for the single-module strut-mechanism,which illustrates the validity and correctness of the Kane method.For the four-module strut-mechanism,the farther away from the fixed root-hinge,the greater the amplitudes of the velocity and the acceleration change at the end of strut deployment.The force perpendicular to the deployment plane for the intermediate hinge is maximal in the initial state of deployment,and gradually decreases during the deployable process.The reasonable control of the driving torque of each hinge is the necessary condition for ensuring that the strut-mechanism is deployed according to the definite rule.The research results provide guidance for the detailed design of strut-mechanism for spacial flexible solar array.