Passive fault tolerant control approach for hypersonic vehicle with actuator loss of effectiveness faults

In this paper, a passive fault tolerant controller is designed for a hypersonic vehicle with bounded external disturbances and unknown actuator loss of effectiveness faults. The nonlinear attitude dynamics models of hypersonic vehicle are firstly given, when some actuator occur unknown loss of effectiveness faults, the faulty attitude control systems of hypersonic vehicle are established, which could be divided into the outer attitude angle loop and the inner angle velocity loop based on the timescale separation principle. By using terminal sliding mode technique, a passive fault tolerant control approach is developed, which guarantees that the closed-loop attitude control systems of hypersonic vehicle in actuator loss of effectiveness fault case are stable. Finally, simulation results are presented to demonstrate the feasibility of the proposed fault tolerant control approach.