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。
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 3 rd 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.
作者
王睦深
谭湘霞
WANG Mu-shen;TAN Xiang-xia(Beijing Institute of Electronic System Engineering,Beijing 100854,China)
出处
《现代防御技术》
2020年第2期35-39,共5页
Modern Defence Technology
关键词
空域
时序
程序角
弹道优化
自适应遗传算法
airspace
time sequence
program angle
trajectory optimization
adaptive control genetic algorithm
