Abstract:This paper focused on designing a robust controller for high angle-of-attack missiles. The similarity between the HJI inequality of nonlinear L2 gain control and the HJB partial differential equation of nonlinear optimal control is analyzed. The closed-form solution of the HJI inequality for nonlinear L2 robust controllers is given based on the θ-D method for the HJB partial differential equation. Then an application in the design of missile autopilot is presented. Numerical simulations show that this method could ensure good dynamic response. At the same time, the satisfactory robustness in the face of measurement noise and uncertainties is confirmed by the simulation results.