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Finite Element Structural Analysis and Topology Optimization of a Vehicle-borne Missile Launching Cradle
- Acta Armamentarii Vol. 44, Issue 2, Pages: 437-451(2023)
- 作者机构：
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
- 作者简介：
- 基金信息：
DOI：10.12382/bgxb.2021.0561
CLC：Received：23 August 2021，
Published Online：10 March 2023，
Published：28 February 2023
- 稿件说明：
移动端阅览
Cao NIU, Guangxin GU, Lei ZHU, et al. Finite Element Structural Analysis and Topology Optimization of a Vehicle-borne Missile Launching Cradle[J]. Acta Armamentarii, 2023, 44(2): 437-451.
Cao NIU, Guangxin GU, Lei ZHU, et al. Finite Element Structural Analysis and Topology Optimization of a Vehicle-borne Missile Launching Cradle[J]. Acta Armamentarii, 2023, 44(2): 437-451. DOI： 10.12382/bgxb.2021.0561.
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。
Abstract
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
Keywords
references
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