基于遗传算法和有限元计算联合仿真的尾翼轻量化设计  

Lightweight design of tail fin based on co-simulation of genetic algorithm and finite element calculation

作　　者：杨辉 易仁发 YANG Hui;YI Renfa(State-owned Changhong Machinery Factory,Guilin 541003,China;Jiangxi Hongdu Aviation Industry Group Company Ltd.,Nanchang 330001,China)

机构地区：[1]国营长虹机械厂,广西桂林541003 [2]江西洪都航空工业集团有限责任公司,南昌330001

出　　处：《兵器装备工程学报》2024年第11期222-229,共8页Journal of Ordnance Equipment Engineering

摘　　要：针对尾翼轻量化设计,提出了一种联合仿真优化设计方法,以改进遗传算法为寻优算法,用有限元计算完成受力分析,编写程序使寻优过程和有限元计算过程联合对结构进行优化。将结构参数离散为设计参数并编码,将有限元计算结果作为约束条件,零件体积为优化目标,通过外点法将约束和目标转换为适应度函数,经过迭代获得最优结构参数。仿真结果表明:用该方法优化对某型火箭弹尾翼进行优化,在满足原工况下的受力要求的同时,减轻了约30%的结构质量,该优化方法具有一定的可行性;在联合仿真寻优的过程中,多种群遗传算法相对于普通遗传算法有更好的搜索效果。This paper presents a co-simulation optimization design method,which uses the improved genetic algorithm as the optimization algorithm,uses the finite element calculation to complete the stress analysis,and writes the program to achieve the structural optimization through the combination of the optimization process and the finite element calculation process.The structure parameters are discretized into design parameters and coded,the finite element calculation results are taken as constraint conditions,the part volume is the optimization target,and the constraint and target are converted into fitness function through external point method,and the optimal structure parameters are obtained through iteration.At the same time,the coding method of genetic algorithm is improved to make it more suitable for solving practical engineering problems.This method is used to optimize the tail fin of a rocket projectile,which not only meets the stress requirements under the original working condition,but also reduces the structure weight by about 30%,which proves that the optimization method has a certain feasibility.In the process of joint simulation optimization,the multi-population genetic algorithm has better searching effect than the general genetic algorithm.

关 键 词：轻量化设计 有限元计算 遗传算法 拓扑优化 火箭弹尾翼 

分 类 号：TJ760.3[兵器科学与技术—武器系统与运用工程]