扇形太阳翼重复折展机构运动仿真及其功能试验

Motion Simulation and Function Test on Repeated Fold-unfold Mechanism of Fan-shaped Solar Array

传统折叠式太阳翼体积与重量大,采用一次性展开锁定机构易引起航天器调姿或变轨时的颤振.为此提出了一种新型扇形太阳翼重复折展机构.基于ProE/Adams联合仿真,建立虚拟样机模型,获取不同电机转速下扇形太阳翼转动导板展开运动参数的变化规律,对所研制的扇形太阳翼重复折展机构原理样机进行展开功能试验.对比仿真与试验结果可知,在电机允许转速范围内调节转速,扇形太阳翼重复折展机构均可在规定时间内完全展开锁定,具有重复折展与锁解功能,且仿真与试验数据高度吻合,表明其符合设计要求.

The traditional folding solar array with large size and big mass, using single deployment and locking mechanism, can cause flutter during the spacecraft attitude adjustment or orbital transfer, and hence a fan-shaped solar array with repeated fold-unfold and lock-unlock mechanism scheme was designed. A virtual prototype model is established based on ProE/Adams co-simulation, and the motion parameter changing rule of the pivot panel at different motor rotational speeds is obtained. The deployment function verification test is carried out using the prototype. By comparing the simulation result with the test data, it can be known that the mechanism can be fully deployed and locked in time when the motor speed is changed in prescriptive range, and can be deployed and locked repeatedly. The simulation result is highly consistent with the test data, which shows that the design can meet the requirements.