Dynamic Surface Control for Hypersonic Aircraft Using Fuzzy Logic System

Abstract

An adaptive fuzzy control strategy is proposed for the hypersonic aircraft. Fuzzy logic system is used to compensate the unknown nonlinearities and modeling errors caused by changes of flight conditions. The DSC method eliminates the "explosion of terms" inherent existing in the conventional back-stepping method. Stability analysis shows that the control law can guarantee the semi-globally uniform boundedness of the solution of the closed-loop system. Numerical simulation use the longitudinal model of a hypersonic aircraft to demonstrate the effectiveness of the proposed strategy.