Effects of Clearance on Deployment of Solar Panels on Spacecraft System

Abstract

This paper establishes a dynamics model for deploying solar panels with clearances by using a practical method and provides a useful way to identify the effects of clearances on spacecraft systems. Considering the clearance of joints, a contact dynamic model is established using the nonlinear spring-damp model and the friction effect is considered by using the Coulomb friction model. Based on the model, numeric simulation of the deployment of a single panel with clearance on a spacecraft is presented. The effects of the clearance on attitude motion of the spacecraft as well as the deployment of a solar panel with joint clearance are analyzed. The simulation results predict the effects of clearance on the attitude motion of a spacecraft system and the deployment dynamics of solar panel preferably. It is useful for engineering design of a spacecraft control system and ground text. This work provides a valuable method for improving the dynamics of spacecraft systems.