Abstract
This paper describes a scheme for fault-tolerant control of an aircraft with a high angle of incidence. The scheme is an example of a generic scheme proposed in (Maciejowski, 1997), adapted to the particular needs of this application. Details of the predictive control technique when employed for reconfiguration are given. The paper also contains a discussion of various scenarios for possible actuator faults. The performance of the proposed fault-tolerant scheme in the presence of severe failures of control surfaces is examined in simulation with an High Incidence Research Model (HIRM)
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