Abstract
The effects of joint clearance on deployment of solar panel on spacecraft system are investigated using a computational methodology. Considering the clearance in joints, the contact model is performed using a nonlinear continuous contact force model and the friction effect is considered using modified Coulomb friction model. And then, the numeric simulation of the deployment of a single panel with clearance on a spacecraft is presented and discussed. Two case studies are implemented for different clearance sizes. The effects of clearance on attitude motion of spacecraft system as well as the deployment of solar panel are analyzed. The simulation results indicate that the existence of clearance in joint causes high frequency oscillation both of the attitude motion of spacecraft and deployment performance of solar panel. And higher size of clearance induces higher frequency shake and larger amplitudes of oscillation on attitude angular velocity and acceleration of spacecraft and deployment angular velocity and acceleration of solar panel. The simulation results can predict the effects of clearance on attitude motion of spacecraft system and deployment response of solar panel preferably. It improves the engineering application and benefits for control system design of spacecraft system and ground text.
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