Design and analysis of autopilot based on adaptive control

Based on analysis of the structure, design method and characteristics of the two-loop acceleration autopilot, model reference adaptive control theory was selected to improve the two-loop autopilot. At first, aiming at a guided missile, the object controlled and the model referenced of the adaptive control system were given according to design requirements. Secondly adaptive control law was designed through the Lyapunov stability theory. Then comparison of the two kinds of autopilots above was discussed after mathematic simulation. Besides characteristics of the adaptive autopilot was given, including effect of fin control surface bias on output of the autopilot and the relationship between parameters of the adaptive controller with dynamic characteristics of the autopilot. It is proved that the adaptive autopilot can satisfy the tactical requirements and is insensitive to the variation of aerodynamic coefficients. Response of acceleration output is stable when fin control surface bias exists.