LQG最优制导规律在地空导弹中的应用

研究了基于线性二次型高斯（LQG）的中远程空空导弹最优制导规律，给出了有效导航比可变的LQG最优制导规律的简化形式，对有效导航比和比例系数进行了适当简化．为了实现LQG最优制导规律，提出了由LQG最优制导规律与卡尔曼滤波器相结合的最优制导／滤波系统．以中远程地空导弹为背景，对地空导弹的导引头回路、舵机回路、阻尼回路、加速度回路和滚动回路进行了理论分析．利用简易的控制系统设计方法标准系数法设计了加速度稳定回路和滚动稳定回路．

Application of LQG Optimal Guidance Law to Ground-to-air Missile

Based on Linear Quadratic Gaussian （LQG） theory, a LQG optimal guidance law with timevariable effective navigation ratio is studied. Simplified guidance relationship is also given for easy implementation of LQG optimal guidance law. And the effective navigation ratio and the proportional coefficients are simplified. An optimal guidance system is formed with the combination of LQG guidance law and Kalman filter. The theoretical analysis of seeker loop, actuator loop, damp loop, acceleration stable loop and roll stable loop of ground-to-air missile are carried out. Being simplified design method of control system, standard coefficient method is utilized to design the acceleration stable loop and the roll stable loop.