Fault tolerant control for damaged aircraft based on sliding mode control scheme

Abstract

In this paper, the problem of structural damage with partial loss vertical tail in aircraft dynamical system is investigated. A linearized aircraft model is introduced firstly, then a damage-tolerant controller based on an adaptive sliding mode control is proposed. Finally, simulations with an aircraft model are conducted to demonstrate the effectiveness and advantages of the proposed design techniques, which can be properly tuned according to structural fault of aircraft.