车载导弹发射架结构有限元分析与拓扑优化设计  

Finite Element Structural Analysis and Topology Optimization of a Vehicle-borne Missile Launching Cradle

作　　者：牛草 顾广鑫 朱磊 徐宏斌[1] 李正宇 张卫红[2] 陈永伟 王博 石建雄 李一哲 NIU Cao;GU Guangxin;ZHU Lei;XU Hongbin;LI Zhengyu;ZHANG Weihong;CHEN Yongwei;WANG Bo;SHI Jianxiong;LI Yizhe(Xi'an Modern Control Technology Research Institute,Xi'an 710065,Shaanxi,China;State IJR Center of Aerospace Design and Additive Manufacturing,School of Mechanical Engineering,Northwestern Polytechnical University,Xi'an 710072,Shaanxi,China)

机构地区：[1]西安现代控制技术研究所,陕西西安710065 [2]西北工业大学机电学院航宇材料结构一体化设计与增材制造装备技术国际联合研究中心,陕西西安710072

出　　处：《兵工学报》2023年第2期437-451,共15页Acta Armamentarii

基　　金：中国博士后科学基金资助项目(2020M673520);陕西省科协企业创新争先青年人才托举计划项目(陕科协发[2021]事企字8号)。

摘　　要：发射架是车载发射装置的关键承力构件之一,其结构刚度和固有频率等静动力学特性对导弹发射精度具有重要影响。以某车载导弹发射架为研究对象,通过多种行军过载和载弹工况的有限元建模与分析对比,研究发射架的受载特点,提出导弹装填、卸载和发射作业序列规划的一般指导原则。进而对发射架结构进行多工况条件下的拓扑优化,讨论挤压约束、最小和最大尺寸约束对拓扑优化结果的影响。根据拓扑优化构型对发射架进行重构设计,对优化设计进行有限元校核分析。分析结果表明,与原有设计相比,拓扑优化设计后的发射架结构减重超过10%,且几乎所有考虑工况下的刚强度均得到改善,刚度最大增幅达到21.47%,等效应力最大降幅达到31.97%;前6阶固有频率提升超过12%,对于减小发射扰动具有重要意义。Launching cradle is a key load-bearing component of a vehicle-borne missile launcher. Its static and dynamic structural characteristics, such as structural stiffness and natural frequency, significantly affect the accuracy of missile launching. Using a vehicle-borne missile launching cradle as the research object, the loading characteristics are investigated through finite element modeling and analyses under various load conditions such as overloading during marching and missile-carrying. General guidelines for missile loading, unloading, and launch sequence planning are proposed based on the finite element analysis results. The launching cradle’s topology optimization is then performed with multiple load conditions considered. The influence of manufacturing constraints as well as minimum and maximum member size constraints on the optimized topological configuration is investigated. The launching cradle is reconstructed according to the optimized configurations. Finite element analyses are carried out to verify the optimized design. Compared with the original design, the weight is reduced by 10.69% while both structural rigidity and strength are improved under almost all considered load conditions. The maximum improvement in structural rigidity reaches 21.47%, and the maximum reduction in equivalent stress reaches 31.97%. Meanwhile, the first six natural frequencies increase by more than 12%, which is of great significance for reducing launching disturbances.

关 键 词：车载导弹发射架 有限元分析 拓扑优化 

分 类 号：TJ768.2[兵器科学与技术—武器系统与运用工程]