Missile Autopilot Design Using Backstepping Approach

Abstract

The autopilot design process is detailed from a backstepping control perspective. The control parameters were determined based on step and sine input commands. Then both characteristics and effect of two control parameters were examined. A linear three-loop topology was also presented for comparison. The results show that the backstepping recursive approach provides a systematically constructive procedure for acceleration autopilot. The based nonlinear autopilot exhibits excellent tracking and robustness.