Parameter optimization for torsion spring of deployable solar array system with multiple clearance joints considering rigid–flexible coupling dynamics

作     者：Yuanyuan LI Meng LI Yufei LIU Xinyu GENG Chengbo CUI Yuanyuan LI;Meng LI;Yufei LIU;Xinyu GENG;Chengbo CUI

作者机构：Qian Xuesen Laboratory of Space TechnologyChina Academy of Space TechnologyBeijing 100094China 

出 版 物：《Chinese Journal of Aeronautics》 (中国航空学报（英文版）)

年 卷 期：2022年第35卷第3期

页      面：509-524页

核心收录：

学科分类：08[工学] 0825[工学-航空宇航科学与技术] 

基　　金：supported by the National Natural Science Foundation of China(No.U1637207) Beijing Natural Science Foundation of China(No.1204040) 

主　　题：Clearance joint Deployable solar array Evaluation index Parameter optimization Rigid-flexible coupling dynamics 

摘      要：In this paper,four novel evaluation indices and corresponding hierarchical optimization strategies are proposed for a deployable solar array system considering panel flexibility and joint *** deployable solar array model consists of a rigid main-body,two panels and four key mechanisms,containing torsion spring mechanism,closed cable loop mechanism,latch mechanism and attitude adjustment *** and flexible components are established by Nodal Coordinate Formulation and Absolute Nodal Coordinate Formulation,*** clearance joint model is described by nonlinear contact force model and amendatory Coulomb friction *** latch time,stabilization time,maximum contact force and impulse sum of the contact force of the solar array system are selected as the four novel evaluation indices to represent the complex dynamic responses of a deployable solar array with clearance joints instead of the lock torque widely used in conventional *** eliminate the gross errors caused by the nonlinear and nonsmooth mechanical properties,a hierarchical optimization strategy based on an adaptive simulated annealing algorithm and a nondominated sorting genetic algorithm is adopted for the solar array system with clearance *** indicate that the effects of panel flexibility on the evaluation index responses and design optimization of the solar array system cannot be ***,increasing the weight factor of the stabilization time index of the rigid system may compensate for the differences in optimal results of the rigid–flexible coupling *** may provide some references for optimization design of deployable space mechanisms considering clearance joints.