基于正则摄动理论的无动力飞行器末段制导方法

以无动力飞行器末制导问题为研究对象，用正则摄动理论对其纵向弹道方程进行处理。在零阶方程中考虑重力和气动力的主导部分，在一阶方程中考虑重力和气动力的剩余部分，进而获得了弹道方程的解析解，仿真证明了该解析解具有较高的计算精度和计算效率。基于弹道解析解所获得的脱靶量，提出了正则摄动制导方法，仿真证明了该方法具有最优性。

Final Guidance Law of Glide Vehicle Based on Regular Perturbation Method

The regular perturbation method is applied to solving the trajectory equation of glide vehicle in the final guidance stage. Most of the gravity and aerodynamic forces are considered in the zero order equation, and the residual gravity and aerodynamic forces are considered in the first order equation. The analytical solution of the trajectory equation is obtained by analytical integration. The simulation results show that the analytical solution has high accuracy and computational efficiency. Based on miss distance generated by analytical solution, guidance based on regular perturbation method is proposed. The simulation results prove that this guidance law has optimality in control.