Study Of Morphing Aircraft Based On Robust Adaptive Control

As a new concept of modern aircraft，morphing aircraft due to its excellent flight performance,has recently received much attention at home and abroad. According to the different needs of flyingmission, morphing aircraft can largely deformate the wing to adjust the flight velocity and flightattitude, which has caused the model structure and parameters uncertainties of the aircraft.This paper based on the characteristic of the morphing aircraft, researchs the control question ofthe system with the model structure and parameters uncertainties. The main content of the presentscientific dissertation can be outlined as follows:1. A novel adaptive integral sliding mode controller is proposed for the system with uncertaintiesand applied to a Morphing Aircraft. The integral sliding surface design is constructed by adding anintegral term into the sliding surface. The additional integral term in the sliding surface provides onemore degree of freedom and also reduces the tracking error. It is shown that the stability of theclosed-loop system can be guaranteed with the proposed adaptive sliding mode control strategy. Thefeasibility of designed control scheme is demonstrated by a Morphing Aircraft model application.2. The morphing aircraft have inherently uncertain and varying dynamics due to the alteration oftheir configuration, so the desired control performance can not be satisfied with a fixed feedbackcontroller. This paper proposes a novel adaptive integral sliding mode tracking controller for amorphing aircraft. An updating rule is designed to estimate the parametric uncertainty by the adaptivelaw. The perturbation can be projected into the matched and unmatched spaces. The additionalintegral term in the sliding surface reduces the steady state error and also provides one more degree offreedom which minimizes the H-infinity norm of unmatched perturbation. It is shown that the stabilityof the closed-loop system can be guaranteed with the proposed adaptive sliding mode control strategy.The feasibility of designed control scheme is demonstrated by a morphing aircraft model application.3. An adaptive output feedback control scheme is proposed for a class of MIMO nonlinearsystem in which the output signal can track the reference signal. The novel design approach uses aradial basis function (RBF) neural network with the online-updated centre and the width of Gaussianfunction to compensate the unknown non-linear dynamics. A robust control law is also designed toreduce the approximation error, which can improve the capacity of resisting disturbance of the system.