Model Following Reconfigurable Flight Control System Design Using Direct Adaptive Scheme

Abstract

Reconfigurable flight control system provides better survivability through the automatic reconfiguration of the control system, even though faults occur during flight. The indirect adaptive control methods have been successfully applied to the reconfigurable flight control system design. To deal with insufficient input excitation problem which is common in adaptive control system, the identification algorithm of the indirect adaptive control system usually imposes constraints on the past input-output data. However, this kind of constraints may deteriorate the reconfiguration performance. Thus, in order to achieve better performance, a new model following reconfigurable controller with direct adaptive rule is proposed. In the proposed controller, the timescale separation principle is applied to control the inner-loop states as well as the outer-loop states simultaneously. To evaluate the reconfiguration performance of the proposed control method, numerical simulation is performed using six degree-of-freedom nonlinear dynamics.