考虑多间隙的帆板式展开机构动力学分析
Dynamic Performance of a Solar Array Deployable Mechanism with Multiple Clearances

在轨运行的大型航天器都含有太阳翼等帆板式展开机构，这种机构发射时处于折叠状态，在轨时处于展开结构状态。帆板之间的铰链间隙对于航天器系统的在轨动力学行为会产生很大影响。利用Adams多体动力学分析软件构造了由卫星本体、帆板式展开机构、间隙铰链和柔性帆板组成的多间隙帆板式展开动力学模型，数值分析了在多间隙作用下展开过程的系统动力学特性，比较了不同间隙数目对系统动力学特性的影响。通过分析展开过程中铰链轴与孔体的接触碰撞力，发现间隙的增多会使轴孔碰撞更加强烈，次数更加频繁。通过分析帆板展开过程中的角加速度变化情况，得到了间隙铰碰撞对展开机构运行稳定性的影响。
All large spacecrafts have deployable structures like solar arrays, which are folded during launch and deployed in orbit. The clearances between the deployable joints greatly impact the system′s dynamics. A multi-body model consisting of a satellite, solar panels, clearance revolute joints and flexible panels is established with ADAMS software. The deployment progress of multiple clearances is numerically simulated, and the comparison between models with different numbers of clearance joints is analyzed by calculating the impact force and relative trail of the shaft mass centroid in the joint. The results show that increasing the clearance number brings in more complexity, and that the joint near the spacecraft base has a stronger influence.