Missile two-loop acceleration autopilot design based on L₁ adaptive output feedback control

This article designs a novel two-loop acceleration autopilot based on L₁ adaptive output feedback control for tail-controlled missiles. The inner loop is an adaptive angle-of-attack tracking loop and the outer loop is the traditional PI controller for error compensation. A systematic low-pass filter design procedure is provided for minimum phase system and is applied to the inner loop design while the parameters of the outer loop is obtained from multi-objective optimization problem. The effectiveness of the proposed autopilot is verified through numerical simulations under various conditions.