超弹性杆折展机构越来越多地用于太空卫星光学薄膜的收拢和展开的支撑问题, 为了避免使用过程因应力集中而产生疲劳裂纹, 延长超弹性杆使用寿命, 对复合材料超弹性杆在不同铺层方式下压扁后的应力进行了研究。首先, 建立单元胞豆荚蜂窝杆有限元模型, 使用显示动力法对其压扁后的状态进行非线性数值分析。然后, 通过复合材料单元胞豆荚蜂窝杆的不同铺层方式下的压扁后最大应力值建立径向基函数代理模型。最后, 利用ISIGHT软件中的遗传算法进行铺层角度的优化。仿真结果表明, 在铺设层数为两层的情况下, 两层应力对应有限元结果与径向基函数(RBF)结果之间的误差都小于9.95％。复合材料单元胞豆荚蜂窝杆采用两层铺层时, 最优的铺层角为第一层、第二层分别为81.962°和82.671°。

Hyper-elastic boom-deployable mechanisms are increasingly used to support and collapse the optical film of space satellites.To avoid fatigue crack caused by stress concentration during operation and to prolong service life, the stress in the hyper-elastic boom after flattening under different layup operations was studied. First, a finite-element model of a single lenticular honeycomb(SLH) boom was established, and a non-linear numerical analysis after flattening was performed using the explicit dynamic method. Thereafter, an approximate model of the radial basis function(RBF) was established using the maximum stress after flattening under different lamination modes of the SLH boom. Finally, the Neighborhood Cultivation Genetic Algorithm in ISIGHT software was used to optimize the layup angle. Simulation results show that the error values of the stresses between the finite-element and RBF results are less than 9.95%.According to the resultsobtained,the SLH boom is laminated with two layers, with the optimal layering method constituting the first and second layers, 81.962° and 82.671°, respectively.