微小型空间相机碳纤维整体式主框架轻量化设计

针对某微小型离轴空间相机结构紧凑、质量轻的设计要求，设计了一个高度轻量化的整体式碳纤维主框架。首先，根据空间相机具体功能的设计指标和光学系统，确定主框架的材料和结构形式，设计出碳纤维整体式主框架的基本构型。接着对铺层厚度参数化优化，并考虑碳纤维复合材料的制造约束，确定了主框架碳纤维铺层的厚度、比例。将参数化优化的结果进行离散化，进行碳纤维铺层顺序的优化，确定了最佳的堆叠次序，完成了碳纤维的铺层优化设计，实现了主框架的轻量化设计，解决了复杂碳纤维零件优化的问题。然后对设计完的碳纤维主框架结构代入整机有限元模型中，进行有限元仿真分析，验证主框架的性能指标。最后，将整机装配完成进行动力学试验，并与有限元分析结果进行对比验证。经过优化，碳纤维主框架的质量为4.5 kg,相机一阶频率为81 Hz,动力学试验得到的相机整机的一阶频率为78 Hz,仿真误差为3.7%,符合仿真结果，进一步说明了设计的合理性以及正确性。本文提出的空间相机碳纤维整体式主框架设计方法对微小型离轴三反式空间相机结构设计以及碳纤维零件的轻量化优化设计具有一定的借鉴意义。

A lightweight design of carbon fiber integrated main frame for the micro space camera

To meet design requirements of the small off-axis space camera with compact structure and light weight, a highly lightweight integral carbon fiber main frame is designed. First, according to the design indicators and the optical system of the specific functions of the space camera, the material and structure of the main frame are determined. And the basic configuration of the carbon fiber monolithic main frame is designed. Then, the layup thickness is parameterized and optimized. The manufacturing constraints of carbon fiber composite materials are considered. The thickness and proportion of the main frame carbon fiber layup are determined. The results of parametric optimization are discretized, the stacking sequence of carbon fiber is optimized, the optimal stacking sequence is determined, the optimization design of carbon fiber is achieved, the lightweight design of the main frame is realized, and the optimization problem of complex carbon fiber parts is solved. Next, the designed carbon fiber main frame structure is substituted into the finite element model of the whole machine, and the finite element simulation analysis is implemented to verify the performance index of the main frame. Finally, the whole machine is assembled for dynamic test, and compared with the finite element analysis results. After optimization, the mass of the carbon fiber main frame is 4. 5 kg, the first-order frequency of the camera is 81 Hz, the first-order frequency of the camera obtained through the dynamic test is 78 Hz, and the simulation error is 3. 7% , which is in line with simulation results. Results further explain the rationality and correctness of the design. The design method of carbon fiber integral main frame of space camera proposed in this article has a certain reference significance for the structural design of micro off-axis three trans space camera and the lightweight optimization design of carbon fiber parts.