微小卫星解锁分离装置主结构设计分析及优化

摘要

This paper presents the initial design scheme of a clamp band system between the minisatellite and the launch vehicle.The finite element model (FEM) of this product is built.By performing an axial compression test, the validity of the finite element model is verified.After that, replacing the satellite with a concentrated mass point at the center of the mass, the rationality of the main structure design is validated through the modal analysis and the static analysis.It is shown that the structure has a large margin of safety and a potential for optimization.The sensitivity analysis and the design optimization are carried out by using the total mass of the satellite as the objective function, the component's thicknesses of the main structure as the design variables, the natural frequencies in the lateral, the longitudinal and the torsional directions keeping unchanged and the strength of the main structure meeting the design requirements as constraints.The optimization reduces the total mass of the product by 11 %.%文章介绍了某小卫星包带式星箭解锁分离装置初样产品的设计方案,建立了该装置的有限元模型,并通过轴向压缩静力试验验证了该模型的有效性.卫星用质心处的集中质量点代替,对解锁分离装置进行了模态与静力分析,验证了其主结构设计的合理性,同时还具有较高的安全裕度和可优化空间.以卫星总质量为目标函数,解锁分离装置主结构各构件的壁厚为设计变量,并以初样产品的横向、轴向和扭转的基频以及其主结构强度满足设计要求为约束条件,进行了灵敏度分析和优化设计,优化后的解锁分离装置总质量减少了1.5 kg.