文中针对以固冲发动机为动力装置的导弹弹道特性与推力特性高度耦合的特点,建立了相应的方案弹道优化模型,并采用基于遗传算法与序列二次规划算法的组合优化方法,以最大射程为目标进行内外弹道一体化优化设计。弹道仿真结果表明:所得到的优化后的飞行弹道方案,在满足飞行条件约束和发动机设计约束的情况下,射程提高了约21.7%。从而验证了所用优化方法的有效性以及一体化优化设计的必要性。

In view of strong coupling of thrust and trajectory characteristic of solid ramjet powered missile, a corresponding project trajectory optimization model was established, and an integrated method of genetic algorithm and sequence quadratic program was used for integrated trajectory missile optimum design which focuses on maximum range.The trajectory simulation result demonstrates that the range is improved by 21.7% while all flight condition and engine design constraints are met.The result also validates effectiveness of optimization method used by this article and necessity of integrated optimum design.