Abstract:

In order to research the influence of the flexible and hinges clearance on the dynamic performance of a solar array during deployment, a lunar rover with a repeatable an unfolded two-stage solar array is used as the research subjects. The modified Coulomb model is taken to describe the friction and to express the clearance in terms of collision force. The finite element method is used for the flexible pannels.A dynamic model which makes the multi-clearance flexible coupling is established. In this paper, the Runge-Kutta method with variable step is applied to the numerical simulation of the deployment of the panel. The effects of the multiple clearances and flexibility on the acceleration of the mass center and the impact force of the hinges clearance are analyzed. The results show that under the premise of ensuring the stiffness requirements of the launching mechanism, the appropriate flexibility of the array can compensate acceleration fluctuation caused by the hinges clearance, weaken the sharp degree of the collision at the clearance and reduce the impact force amplitude, thereby improving the dynamic characteristics of the deployable mechanism. The results can be used to guide the dynamic optimization design of the flexible deployable panels with multiple clearances.

Key words: Clearance, Flexibility, Multi body dynamics, Repeatable deployable solar array