以某卫星太阳翼为研究对象,利用UG软件建立了卫星的整星模型,并将其导入MSC.ADAMS软件中,在ADAMS/View模块中建立转动副、扭簧、锁定和绳索联动机构的模型。用接触力模拟锁定机构中的接触碰撞现象,用关联副模拟绳索联动机构协调作用,然后使用ADAMS/Solver进行了动力学仿真。通过仿真分析,得到了连接架和各帆板展开角度与时间的关系以及展开过程中卫星姿态的变化。分析结果表明,太阳翼的展开过程平稳,历时15 s;在展开过程中卫星姿态稳定可控,展开过程对整星的姿态影响很小,太阳翼展开机构设计合理。

On the basis of analysis of the deployment motion of satellite solar array, a whole satellite model was established by UG and was imported to MSC.ADAMS. Then, the deployment of solar array was simulated in ADAMS. A jointing structure consisting of revolute joints, torsion springs and closed cable loops was built in ADAMS/View. Moreover, the impacting process was simulated by contact functions, the closed cable loops was simulated by couplers, and the dynamics characteristic was emulated in ADAMS/Solver. After analysis on the simulation, the relations between deployment angles of linker and solar panels with time were obtained, and the movement of satellite′ attitude influenced by deployment motion was calculated. Analysis results indicate that the deployment process of solar array is 15 s. The deployment motion is stabilization and smoothness, and has a little effect on satellite attitude. These results reported here show that designed solar array is reasonable.