Adaptive Sliding Mode Roll Control of a Canard-Controlled Missile
作者单位：Mohammad Ali Jinnah UniversityIslamabadPakistan
会议名称：《2010 Chinese Control and Decision Conference》
会议日期：2010年
学科分类：08[工学] 081105[工学-导航、制导与控制] 0804[工学-仪器科学与技术] 0811[工学-控制科学与工程]
关 键 词：Missile sliding mode control adaptive control autopilot aerodynamics canards.
摘 要：This work is meant to design a roll controller for a short range missile with a free-spinning tail using the sliding mode control *** canards located near the nose of the missile provide aerodynamic ***/yaw stability is achieved through four rotating fins located at the tail of the *** of the missile dictates the whole trajectory in the atmosphere where dynamic pressure varies between 0 and 7 *** the missile can be fired at different launch angles,which implies that the profile of dynamic pressure is not *** strategy strongly depends on dynamic pressure in the case of canard-controlled *** the case of varying dynamic pressure,design of a robust roll controller that can keep roll angle near zero is a challenging *** this paper,a roll controller is designed for a canard-controlled short range missile using sliding mode control *** is done in some control parameters to cater the variation in dynamic pressure and different launch *** robustness of the roll controller is tested in the presence of aerodynamic and other *** is established that the proposed roll controller is capable of rejecting aerodynamic and other disturbances and keep the roll angle close to zero.