基于自适应遗传算法的弹道性能优化设计

doi:10.3969/j.issn.1009-086x.2020.02.006

现代防御技术 ›› 2020, Vol. 48 ›› Issue (2): 35-39.DOI: 10.3969/j.issn.1009-086x.2020.02.006

基于自适应遗传算法的弹道性能优化设计

王睦深, 谭湘霞

北京电子工程总体研究所,北京 100854

收稿日期:2019-07-19 修回日期:2019-10-23 出版日期:2020-04-20 发布日期:2021-01-20
作者简介:王睦深(1995-),男,内蒙古呼伦贝尔人。硕士生,主要研究方向为飞行器设计。通信地址:100854 北京142信箱30分箱 E-mail:464365635@qq.com

Missile Trajectory Optimization Based on Adaptive Control Genetic Algorithm

WANG Mu-shen, TAN Xiang-xia

Beijing Institute of Electronic System Engineering, Beijing 100854, China

Received:2019-07-19 Revised:2019-10-23 Online:2020-04-20 Published:2021-01-20

摘要/Abstract

摘要： 在以往分阶段优化导弹弹道研究的基础之上,通过对整个弹道的导弹指令程序角和飞行时序进行设计,使得导弹在三级分离时,海拔高度更低,航程更远。首先对导弹进行了动力学建模,随后对优化问题的优化变量、目标函数、约束条件进行了设计,最后采用自适应遗传算法对导弹弹道优化问题进行仿真求解,结果表明,采用该算法的优化设计弹道海拔更低、射程更远、性能更好。

关键词: 空域, 时序, 程序角, 弹道优化, 自适应遗传算法

Abstract: Based on previous missile trajectory optimization which optimized sectionally,design the pitch angle and the flight sequence of the tajectory integrally to make the missile lower and farther at the separation time of the 3rd stage engine.A dynamic model was built firstly.Then the optimization variables,the objective function and the restrictions were designed.The missile trajectory optimization was calculated and simulated with adaptive genetic algorithm.The simulation result shows that missile trajectory designed this way has lower altitude further range and better flight performance.

Key words: airspace, time sequence, program angle, trajectory optimization, adaptive control genetic algorithm

中图分类号:

TJ761.7

王睦深, 谭湘霞. 基于自适应遗传算法的弹道性能优化设计[J]. 现代防御技术, 2020, 48(2): 35-39.

WANG Mu-shen, TAN Xiang-xia. Missile Trajectory Optimization Based on Adaptive Control Genetic Algorithm[J]. Modern Defense Technology, 2020, 48(2): 35-39.

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基于自适应遗传算法的弹道性能优化设计

Missile Trajectory Optimization Based on Adaptive Control Genetic Algorithm

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