基于最优控制的落角约束攻击设计

针对导弹落角控制和精度控制的矛盾,运用飞行力学原理和最优控制理论,以落地速度倾角作为终端约束,以脱靶量、最小能量为性能指标,给出了一种适用于攻击地面目标的最优导引律。设计了导弹三通道的PID控制器,最后进行了导弹的6DOF仿真研究,仿真验证了设计方法的有效性。

Design of guidance law and controller of missile with terminal angular constraint based on optimal control

In order to solve the contradiction between terminal angular control and precision control, an optimal guidance law is proposed using flight mechanics and optimal control theory with miss distance and minimum energy as performance index. And a PID controller is designed for the three-channel missile system, which satisfies the requirements of precision and angle. The simulation study for a 6-degree of freedom missile system is performed and the simulation results show the effectiveness of the proposed method.