A Variable Control Structure Controller for the Wing Rock Phenomenon

摘要

The This paper presents the design of a variable structure controller for the model of the wing rock phenomenon of a delta wing aircraft. It is considered to be a continue study of the last two researches for the same phenomena "Feedback linearization [15] and back stepping controller [14] ". A control technique is proposed to stabilize the aircraft phenomena. The solution presented in this paper give a guarantee of asymptotic convergence to zero of all variables of the system. MATLAB simulation used to show how the proposed control is working well for such phenomena of a delta wing aircraft. The model of the phenomena in this paper will consider the same model presented in the last two researches mentioned above.