H_∞ guidance law accounting for dynamics of missile autopilot

In order to intercept the maneuvering targets and overcome the adverse effect of the missile autopilot's dynamics on the guidance performance, this paper aims to propose a H_∞ robust guidance law with the dynamics of the autopilot considered. The third-order linear time-varying state equation for the integrated guidance and second-order dynamics of autopilot is expressed as a polytopic LPV system. A novel H_∞ robust guidance law, in the form of linear state-feedback with parameter-dependent gain, is designed using LMI method. The coefficients in the parameter-dependent gain are obtained by solving a convex optimization problem with LMI constraints. Simulation results indicate that, even if the target's acceleration is not known, the H_∞ guidance law can still achieve strong robustness and obtain high guidance precision.