空射弹道导弹助推段弹道设计与优化

Design and optimization of boost phase trajectory for air-launched ballistic missile

在弹道优化设计研究中,针对空射弹道导弹弹道优化两点边值问题解析求解困难且对参数敏感的问题,基于将过程优化问题转化为参数优化问题的思想,采用了飞行程序角设计的参数优化方法。根据空射弹道导弹亚声速水平发射的特点,首先基于动力特性设计了其助推段飞行程序角模型,确定了恰当的控制变量参数化结构,在满足飞行过程的多种约束条件下,建立了弹道优化模型,引入序列二次规划法对其进行优化计算,从而实现了对确定优化目标的轨迹快速生成。仿真结果表明,弹道优化计算时间缩短,收敛速度明显提高,可在原有设计基础上,提升优化指标16%,验证了该方法的有效性。

To avoid difficulties in solving two-point boundary value and the parameter sensitive issues in horizontally air-launched ballistic missile for trajectory optimization,a parameter optimization method based on flight program angle design is proposed.According to the characteristics of horizontally air-launched missile,the model of flight program angle in boost phase is designed and a proper control variable parameterization structure is established on the basis of dynamic characteristics.Then,considering constrains of the whole flight trajectory,a mathematical model of maximum range optimization is built,and the sequential quadratic programming algorithm is used to solve the optimization issue.Simulation results show the optimization index increases by 16 percents and verifies the validity of the method.