Nonlinear H-infinity optimal control for agile missiles

Nonlinear H-infinity optimal control is used to design a pitch plane flight control system for a high-angle-of-attack agile missile. The nonlinear H-infinity control law is obtained by approximating the solution to the Hamilton-Jacobi-Isaacs equation, The solution to the partial differential equation is formed using the method of characteristics and is numerically approximated using successive approximations, Nonlinear simulation results using the nonlinear control law are presented, Simulation results testing the algorithms demonstrated excellent performance.