一种非线性最优导弹制导律

ONE NONLINEAR OPTIMAL MISSILE GUIDANCE LAW

以质点飞行器的非线性运动方程为基础，研究了导弹拦截目标问题。运用线化变换理论和线性二次型微分对策理论，导出了导弹和目标的最优控制策略，对导弹最优策略进行了综合分析，给出了一种可以实时实现的最优制导律。并以某型中远程地－空导弹的气动数据和数学模型为基础，进行了全弹道拦截数字仿真。

The problem of interception of missile target is studied,which based on nonlinear equations of motion of point mass aircraft.The optimal control strategy of missile and target is given by using the theory of prelinearizing transformations and linear quadratic differential games.One on line realizing optimal guidance law is synthesized.We,taking aerodynamic data and mathematical model of a certain earth to air midcourse long missile,have made digital simulation of whole missile trajectory.Simulation results shows that guidance law which given in this paper is more effective than space PN(Proportional Navigation) guidance law.