嫦娥五号轨道器复合材料承力球冠结构设计及性能评估技术

Design and Performance Evaluation of Composite Ball Shell on Chang’e-5 Orbiter

针对嫦娥五号轨道器结构轻量化设计需求,提出了一种用于贮箱安装的一体成型复合材料承力球冠方案。基于有限元软件参数化建模功能,对承力球冠结构的设计参数进行了优化,获得了承力球冠结构的最佳矢跨比和铺层厚度;基于层合板理论,对承力球冠结构进行力学仿真分析,并开展静力试验验证,试验与仿真分析承载能力偏差为14%,具有良好的一致性;与同类结构产品进行对比,采用了参数优化和一体化成型技术的复合材料承力球冠可显著提升推进平台的整体效率。该研究结果可作为航天器推进平台设计参考。

In view of the lightweight design requirement of Chang’e-5 Orbiter,an integration molding composite ball shell for tank installation is presented.The design parameters of the ball shell are optimized with the parametric modeling function of the ANSYS software,and the optimal rise-span ratio and layer thickness are achieved.The mechanical behavior and load bearing capability of the composite ball shell are studied through the finite element method and tests based on the laminate plate theory.The results show that the results obtained by the tests and simulations agree with each other well,the error is only 14%.Compare with similar structural products,the composite ball shell obtained by parameter optimizing and integration molding can improve the structural efficiency of the propulsion platform significantly.The results can be used as a reference for the design of spacecraft propulsion platforms.