基于多种群差分进化算法的火箭弹自力弹射多目标约束优化设计  

Multi-objective constraint optimization design of rocket projectile self-ejection based on multi-population differential evolution algorithm

作　　者：宋健 李超 佘湖清 蔡蒨 SONG Jian;LI Chao;SHE Huqing;CAI Qian(Yichang Testing Technique Research Institue,China State Shipbuilding Corporation Limited,Yichang Hubei 443000,China)

机构地区：[1]中国船舶集团有限公司宜昌测试技术研究所,湖北宜昌443000

出　　处：《航空动力学报》2023年第6期1516-1524,共9页Journal of Aerospace Power

基　　金：“十三五”预研课题(3020106070501)。

摘　　要：针对火箭弹自力弹射设计中降低低压室压强峰值与提高弹体出筒速度之间的矛盾,开展自力弹射的优化设计工作。建立自力弹射发动机-低压室耦合内弹道求解模型,并开展两种工况共4发实弹的验证试验;提出融合多种差分策略的多种群差分进化算法,并采用“剔除-补足”操作处理优化过程中的约束条件;考虑自力弹射的实际设计约束,以低压室压强峰值和弹体出筒速度为目标建立两目标约束优化模型,并采用多种群差分进化算法进行优化计算。结果表明:计算得到的Pareto前沿近似呈斜率不同的两段线性区间,随低压室压强峰值增大,相同压强增幅带来的出筒速度增量减小;在Pareto前沿上均匀选取12个优化方案并采用逼近理想解排序法进行排序,排序后得到的最终优化方案的低压室压强峰值降低16.11%,弹体出筒速度增加54.55%,自力弹射性能得到提升。In view of the contradiction between reducing the pressure peak in low pressure chamber and increasing the exit velocity of self-ejection,the optimization design of self-ejection was carried out.A motor-low pressure coupled internal ballistic solution model of self-ejection was developed,physical experiments of two working conditions with four rockets were carried out.The multi-population differential evolution algorithm using differential strategy was proposed,“eliminate-complement operation”was adopted to deal with the constraints in the optimization process.A two-objective self-ejection constraint optimization model was established with the peak of pressure in low pressure chamber and the exit velocity considering the actual constraints of self-ejection,and this optimization model was calculated by the multi-population differential evolution algorithm.Results showed that,the Pareto front was of two segments with different slopes approximately.With the increase of pressure peak of low pressure chamber,the same increment of pressure led to a smaller increment of exit velocity.Twelve schemes were evenly selected in Pareto front and ranked by using technique for order preference by similarity to an ideal solution;the peak of pressure in low pressure chamber of the final optimized scheme of self-ejection decreased by 16.11%,the exit velocity of the final optimized scheme increased by 54.55%,and the performance of rocket projectile self-ejection had been improved.

关 键 词：火箭弹 自力弹射 内弹道模型 多目标约束优化 差分进化 逼近理想解排序法(TOPSIS) 

分 类 号：V238[航空宇航科学与技术—航空宇航推进理论与工程] TJ02[兵器科学与技术—兵器发射理论与技术]