Dynamics Study On Impact For The Large Scale Solar Array During Deployment And Sun Tracking Process

With the aerospace industry development, the satellites economic indicators,especially the life of the increasingly high demanded, China’s aerospace have the analysisand predict t of the spacecraft’s life put on the agenda. As the energy attachmentreliability of the spacecraft, their work and life is directly related to the economy of theentire spacecraft. During deploying, locking and sun-tracking process, the dynamicsquestions of solar array were studied, especially for easily damaged connection hinge’swindsurfing load analysis, to provide the necessary mechanical basis for life design andprediction.First of all, this paper introduced the mainly forms of solar panels, analyzed andsummarized the current hot issues of the solar array, outlined the development as well asthe main method of the dynamic core problem of the solar panels, collision. Then, fromthe theory, summarized the phenomenon of friction and the friction model, calculated theHertz contact force derived from nonlinear spring-damper model, and the collisionpenetration depth, analyzed the main factors of solar dynamic questions from themathematical calculations point of view.Secondly, the mathematical description of the solar panels during deployment andlocking was done with Euler-four element method, and its dynamic model wasestablished with nonlinear spring-damper model and modified Coulomb friction model.Based on virtual prototyping technology, an analyzing model of the solar array wasestablished, focus on the main factors-driving torque and the dynamic equivalentstiffness, simulations of solar array was executed, analyzing the influence of the factorson the critical hinges impact load.Furthermore, the mathematical description of the pointing issues and the spacerotating hinge was done, and the dynamic model was established with nonlinearspring-damper collision model and modified Coulomb friction model, base on the spacehinge geometry relations, the motion identify criterion of the collision state was built up,solving the problem of the multi-state collisions. A virtual prototype of with hingeclearance solar array was established, focus on the clearance size and tracing speed, thesimulation are executed, analyzing the influence of the two factors to the impact and loadon the key hinges.At last, considering the flexibility of the solar array, base on the comprehensivemodal method, a more accurate model was built up, and simulations are executed for the solar array during deployment locking and sun-tracking process, analyzing the influenceof the flexibility on the impact and load on the key hinges and the posture of the satellite.