助推-滑翔导弹分段总体参数优化方法研究  

Research on Multi-Stage Overall Parameter Optimization Method for Boost-glide Missile

作　　者：罗炜 雷刚 郑晓龙 LUO Wei;LEI Gang;ZHENG Xiaolong(Rock Force University of Engineering,Xi'an 710025,Shaanxi,China)

机构地区：[1]火箭军工程大学,陕西西安710025

出　　处：《弹箭与制导学报》2023年第5期73-79,共7页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：为发挥助推-滑翔式导弹最大作战效能,需在一定的飞行条件约束下,对其总体参数进行优化设计。首先分析直接起滑式滑翔弹道下各类参数对飞行弹道的影响,并将整个优化过程划分为独立的两个阶段;而后采用自适应遗传算法对各阶段进行优化,得到了满足文中约束条件下的最佳导弹总体方案;最后采用蒙特卡洛模拟对该方法进行验证。结果表明,文中设计方法能够在5.5 s内完成总体参数优化,并在±0.7%的精度范围内使得导弹进行直接起滑式飞行。In order to give full play to the maximum combat effectiveness of the booster-glide missile,its overall parameters are optimized under certain flight conditions.Firstly,after analyzing the influence of various parameters on the flight trajectory un-der the direct takeoff and gliding trajectory,the entire optimization process is divided into two relatively independent sub-sta-ges;then the sub-stages are optimized by adaptive genetic algorithm respectively,and the results satisfying each The optimal missile overall design scheme under the class constraints;finally,the method is verified based on the Monka simulation.The results show that the design method can complete the overall parameter optimization within 5.5 seconds,and make the missile fly with the accuracy of±0.7%.

关 键 词：助推-滑翔式导弹 总体参数设计 分段优化方法 自适应遗传算法 

分 类 号：TJ761.3[兵器科学与技术—武器系统与运用工程]