基于非线性瞬态响应的空间站柔性太阳翼在轨载荷分析

Nonlinear transient on-orbit load analysis of a flexible solar array

针对展开面积大、机构环节多、带有柔性索/膜结构的空间站太阳翼,建立精细的有限元模型、分析其在轨高强度激励条件下的瞬态变形和应力是强度设计所必须完成的环节。利用"间隙-接触"(Gap)单元的力学特性,将其倒置后作为钢丝绳与收藏箱的连接单元,一举解决了柔性阵面预紧力施加、钢丝绳不连续拉压刚度模拟以及收藏箱弹性变形补偿等多个问题,成功获得了太阳翼重要部件的瞬态剪力、弯矩等载荷结果,为产品设计提供了重要决策依据。结果表明基于线性模型的计算方法应用于此问题时存在显著不足。

The space station solar array is usually a flexible cable/membrane structure with large developing area and plenty of mechanism links. It is necessary to establish a fine finite element model and analyze the transient deformation and stress under high strength on-orbit load conditions. Making use of the advautageous mechanical properties of the Gap element, inverted Gap elements were used as the connecting unit between the flexible substrate and the storage boxer. Several problems such as the pretigthening force on flexible substrate, the simulation of discontinuous tension, the compression stiffness of the cable, and the elastic deformation offset of the storage boxer were solved at one stroke. The transient shear forces and bending moments on some improtant components of the solar array were obtained successfully, which provides important decision basis for product design. The results also show that there are significant shortcomings in the application of linear model to this problem.