含铰间间隙太阳帆板展开动力学仿真

Dynamics simulation of deployment for solar panels with hinge clearance

为了研究铰间间隙在太阳帆板展开过程中的影响,采用非线性等效弹簧阻尼模型建立了间隙处的接触碰撞模型,同时采用Cou lomb摩擦模型考虑铰间间隙处的摩擦作用.并将其嵌入到ADAMS多体系统动力学分析软件中,对一单翼小卫星太阳帆板展开过程进行了数值仿真.研究了间隙撞击力的变化规律,分析了间隙对卫星本体姿态运动及帆板展开过程的影响.仿真结果可以较好地预测铰间间隙对卫星本体姿态运动及太阳帆板展开动力学的影响,对卫星姿态控制系统的设计和地面试验提供了参考和依据.

The effects of hinge clearance on the deployment of solar panels were studied. The contact dynamics model was established using the nonlinear equivalent spring-damp model and the friction effect was considered by using the Coulomb friction model. Then the models were incorporated into ADAMS, and a large number of numeric simulations of deployment of a single panel on a satellite were made. The regularity of contact forces in clearance was studied in detail and the effects of clearance on attitude motion of the satellite and deployment of solar panels were analyzed. The simulation results can predict the effects of clearance on satellite attitude motion and deployment dynamics of solar panels preferably. It can be a reference for engineering design of satellite control system and ground test.