具有落点和落角约束的圆轨迹制导律

Circular Trajectory Guidance Law with Terminal Constraints of Impact Point and Impact Angle

针对再入飞行器带终端约束的末制导问题,在二维平面内设计了一种新型圆轨迹制导律。首先,利用再入飞行器与目标相对几何关系对圆轨迹制导方法进行运动学分析。再通过对制导任务的分析,定义了两个圆轨迹跟踪误差变量,并基于此提出误差反馈导引方法。然后,得出闭环圆轨迹制导律,并对制导指令分量的具体含义进行了分析。最后,对该制导算法的有效性进行了仿真验证。仿真结果表明:此算法可用于末端大角度转向飞行,有效提高再入飞行器的作战效能;并且制导精度高,其中命中点误差和碰撞角约束误差都很小。

A novel circular trajectory guidance law is proposed for reentry vehicle with terminal constraints in a two- dimensional plane. Firstly, the kinematic property of the circular trajectory guidance is analyzed by using the engagement geometry. Furthermore, a closed-loop modification method is presented based on two newly defined deviation variables of the circular trajectory guidance. Then the closed-loop circular trajectory guidance law is derived, and meanings of components of the guidance law are revealed respectively. Finally, the validity of the guidance law is verified by numerical simulations. Simulation results have demonstrated that the guidance law greatly improves the attacking efficiency of the reentry vehicle in a steep maneuvering engagement scenario, and it attains a perfect intercept with small miss distance and impact angle error.