基于遗传算法的弹道优化算法

Trajectory Optimization Method Based on Genetic Algorithm for Air-to-Air Missiles

以空空导弹的末端速度作为性能指标,其弹道倾角视为控制变量,在规定的飞行时间及射程下,优化导弹弹道使得其末端速度最大化;通过采用多项式样条插值的方法估计弹道倾角的变化规律,利用遗传算法进行优化计算弹道倾角采样点数据,最后得到满足条件的优化弹道并进行仿真;仿真结果表明:按此优化方法得到的弹道与比例导引方案弹道相比,大大提高了导弹的末端速度,研究结果对空空导弹的标准弹道设计有一定学术和工程参考价值。

An advanced trajectory optimization method based on genetic algorithm is proposed in this paper.The proposed trajectory optimization method regards the terminal velocity as the performance index and the flight path angle as the control variable,and maximizes the terminal velocity in the given flight time and range.The paper estimates the regulation of the flight path angle by multinomial spine interpolation and genetic algorithm.Then,the optimal trajectory is achieved.The simulation results show that the terminal velocity of optimal trajectory achieved from the method above is better than that from proportional method.The results have certain reference value in the design of standard trajectory for air-to-air missiles.