车载导弹发射架结构有限元分析与拓扑优化设计

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.