卫星主承力板点阵式结构设计与力学分析

Design and Mechanical Analysis on the Lattice Structure for the Primary Load-Bearing Panel of a Satellite

为了达成卫星主承力板在轻量化及刚度性能上的设计要求,并有效降低板载单机的动力学响应,将点阵结构引入卫星承力板的设计当中。首先,介绍了点阵结构的胞元构成,并得出采用点阵结构填充的卫星主承力板,在保持相同外观尺寸的前提下,相较于传统蜂窝夹芯结构板,质量减轻了35%左右,满足了卫星轻量化设计的需求。随后,建立了单个胞元的相对密度、平压刚度、平压强度和剪切刚度的理论数学模型,并通过仿真分析验证了模型的准确性。解释了动力学分析的基本原理和优化方法,并基于模态分析结果,对所设计的主承力结构板进行简谐振动和随机振动响应分析。结果表明:主承力板的结构刚度分布均匀,对激励具有良好的响应,各项动力学性能指标满足要求。

In order to meet the design requirements of the primary load-bearing panel of a satellite in terms of lightweight and stiffness performance and effectively reduce the dynamic responses of the panel,a lattice structure is incorporated into the design of the primary panel.First,the cell composition of the lattice structure is introduced.It is demonstrated that the satellite primary load-bearing panel filled with the lattice structure can reduce the weight of approximately 35%compared with the traditional honeycomb core panel,while maintaining the same external dimensions,thereby satisfying the lightweight design requirements for satellites.Second,theoretical mathematical models for the relative density,in-plane stiffness,in-plane strength,and shear stiffness of a single cell unit are established,and the accuracy of the models are validated through simulation analyses.The fundamental principles of dynamic analyses and the optimization methods are illustrated.Finally,based on the modal analysis results,harmonic and random vibration response analyses are conducted on the designed primary load-bearing structure.The results show that the structural stiffness distribution of the primary load-bearing panel is uniform and exhibits favorable responses to excitations,and all dynamic performance indicators meet the specified requirements.