This article documents the design of a novel two-loop acceleration autopilot based on 1 L 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 are obtained from the multi-objective optimization problem. The effectiveness of the proposed autopilot is verified through numerical simulations under various conditions. Key words: 1 L adaptive output feedback control, Autopilot, low-pass filter
IntroductionDue to the wide parameter variation and stringent performance requirements, missile autopilot design is a challenging task. The traditional method of guaranteeing stability in the presence of aerodynamic parameter variation or uncertainty is the gain scheduling control strategy. Modern air-to-
IntroductionDue to the wide parameter variation and stringent performance requirements, missile autopilot design is a challenging task. The traditional method of guaranteeing stability in the presence of aerodynamic parameter variation or uncertainty is the gain scheduling control strategy. Modern air-to- 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 are obtained from the multi-objective optimization problem. The effectiveness of the proposed autopilot is verified through numerical simulations under various conditions. adaptive output feedback control, Autopilot, low-pass filter