Output feedback nonlinear discontinuous adaptive longitudinal flight control for maneuvering aircraft

Based on the variable structure model reference adaptive control theory, a new control system for the control of a maneuvering aircraft, using only pitch rate measurement, is designed. For the derivation of the control law, it is assumed that the aerodynamic parameters in the model are unknown. Moreover, it is assumed that disturbance input is present in the system. It is shown that in the closed-loop system, the pitch rate tracks given reference trajectory. Digital simulation results show that the closed-loop system has good transient behavior and robustness to the uncertainties and disturbance input.