With the increasing diversity of spacecraft, the solar wing deployable mechanisms are gradually developing to be more lightweight. In this paper, a scissor-type flexible solar wing deployable mechanism is proposed. In particular, the geometric nonlinear large deformation problem after deployment locking is primarily investigated, and the structural properties such as static load deformation, spatial modes, and impulse response are discussed sequentially. Firstly, the geometrically nonlinear incremental formulation of the spatial structure is established based on the Updated Lagrangian method, and the nonlinear system of equations is solved using the arc-length incremental iteration method. Secondly, a virtual beam element is introduced to represent the stiffness characteristics of the connected joints. Finally, a three-layer nested iteration algorithm, including time step and load step, is constructed for the dynamic response problem. The comparison of experimental and numerical results proves the reliability of the theoretical method. The method proposed in this paper provides guidance in equivalent modeling and numerical solutions, which is of great significance for the analysis and optimization of large-scale deployable aerospace structures.

中文翻译：

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具有几何非线性的剪刀式柔性太阳能翼的动力学建模与实验研究


随着航天器的日益多样化，太阳能翼可展开机构正逐渐向更轻量化的方向发展。本文提出了一种剪刀式柔性太阳能翼可展开机构。特别是，主要研究了部署锁定后的几何非线性大变形问题，并依次讨论了静载荷变形、空间模式和脉冲响应等结构性质。首先，基于更新的拉格朗日方法建立了空间结构的几何非线性增量公式，并采用弧长增量迭代法求解非线性方程组。其次，引入虚拟梁单元来表示连接节点的刚度特性。最后，针对动态响应问题构建了包括时间步长和负载步长在内的三层嵌套迭代算法。实验结果与数值结果的对比证明了理论方法的可靠性。本文提出的方法为等效建模和数值解提供了指导，对大规模可展开航空航天结构的分析和优化具有重要意义。