Title :
Design and analysis of autopilot based on adaptive control
Author :
Chen Xun ; Liu Yongshan
Author_Institution :
Sch. of Aerosp. Eng., Beijing Inst. of Technol., Beijing, China
Abstract :
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.
Keywords :
Lyapunov methods; control system synthesis; missile control; model reference adaptive control systems; stability; Lyapunov stability theory; adaptive autopilot; aerodynamic coefficient; fin control surface bias; guided missile; model reference adaptive control theory; two-loop acceleration autopilot; Acceleration; Adaptation models; Adaptive control; Aerodynamics; Missiles; Transfer functions; Vehicle dynamics; Lyapunov stability theory; adaptive control; missile; model reference; two-loop autopilot;
Conference_Titel :
Mechatronic Sciences, Electric Engineering and Computer (MEC), Proceedings 2013 International Conference on
Conference_Location :
Shengyang
Print_ISBN :
978-1-4799-2564-3
DOI :
10.1109/MEC.2013.6885529
