变压装顺序下空间站太阳电池翼多约束装夹内力预测与分析

Prediction and Analysis of the Assembly Preload With Multiple Constrains for Space Solar Arrays in Different Tightening Sequences

多约束下预紧力控制对空间站太阳电池翼折叠压装后长期存放以及发射、在轨展开具有十分重要的意义,柔性电池翼多层复合结构装夹时受多约束压紧变形与装夹顺序的耦合影响,约束机构预紧力难以预测,压装工艺缺乏理论指导。针对柔性电池翼多层结构多约束紧固装夹问题,建立考虑紧固结构交互刚度相互作用的多约束耦合预紧力预测模型,研究不同拧紧顺序下电池翼多约束预紧力的演化规律,分析多约束紧固载荷下各连接位置预紧力相互影响机制。结果表明,加载顺序会影响预紧力变化历程与最终预紧效果,预紧力变化方向和约束所处连接件弯曲挠度的具体区域有关。利用预紧力预测刚度矩阵,能对残余预紧力进行有效预测,设计满足预紧力需求的加载参数,指导实际装夹流程,为空间站太阳电池翼收纳箱夹装工艺提供参考。

The preload control oftheassembly with multiple constrains is important to the long-term storage,launch and in-orbit unfolding ofthe space flexible solar arrays.However,the preloads are affected by the deformation of the solar array storage box and the tightening sequences of the fasteners,causing difficulties to the qualified rate of the final preloads.Therefore,considering the deformation compatibility conditions and the coupling effects,an analytical model based on the elastic interaction stiffness is established to predict the preloads and design the clamping process.Moreover,the preload variation patterns and the interaction mechanism in different tightening sequences are investigated.The results indicate that the residual preloads depend on the pre-tightening sequences and the direction of the preloads is related to the region of the deflection surface where the constrains are located.Finally,the initial preloads varying from different loading sequences may be calculated by using the analytical model to design the preloading process.