A High Gain Integral Dynamic Compensation Method for Nonlinear Missile Control

Abstract

AbstractA high gain integral dynamic compensation method for a missile pitch motion autopilot design is proposed. The external disturbances and model mismatch are lumped into an unknown input term, and then a high gain integral observer is constructed for the estimation of this term. Through the singular perturbation theory, it is concluded that with the control direction known and the integral gain high enough, the observer output can converge to the unknown input fast enough. The Lyapunov analysis also shows the bounded stability of the closed loop system. Numerical simulation results demonstrate this simple method improves the nominal tracking performance and robustness of dynamic inversion controller against unmodeled dynamics and external disturbances.