论文部分内容阅读
针对SINS/GPS航弹无动力飞行和高度测量误差较大的缺点,设计了基于最大升阻比的中制导律,利用最优控制理论设计了一种带落角约束的末制导律,运用遗传算法对末制导律参数进行优化,达到滑翔增程的目的,并使制导航弹以陡峭的弹道攻击目标,消除高度误差对制导精度的影响。仿真结果表明,滑翔段弹道平缓,增程效果显著;俯冲段弹道陡峭,着地时弹道倾角接近-90°。
Aiming at the shortcomings of SINS / GPS bombs, such as non-powered flight and high altitude measurement errors, a mid-guidance law based on the maximum lift-drag ratio is designed. Based on the optimal control theory, a final guidance law with dangling constraint is designed. The algorithm optimizes the parameters of the final guidance law to achieve the purpose of gliding gain and makes the guided missile play a steep trajectory to the target and eliminate the influence of height error on the guidance accuracy. The simulation results show that the gliding trajectory is smooth, and the extended range effect is remarkable. The trajectory of the plunging stage is steep, and the trajectory inclination of the ground is close to -90 °.