Abstract
This study proposes a fault estimation and compensation scheme for hypersonic flight vehicle (HFV) attitude system with body flap fault. To achieve the fault compensation capability, an interval type-2 fuzzy estimator is designed to approximate the unknown nonlinear function caused by modeling uncertainties and the fault. The fault-tolerant controller via the terminal sliding mode and dynamic surface techniques is developed to ensure the tracking accuracy of attitude angles for HFV and the desired control torque can be achieved. Then, a novel control allocation scheme with a cuckoo search algorithm and linear programming method is proposed to distribute the desired torque to aerodynamic surfaces and reaction control system jets. The stability of the proposed scheme is analyzed using the Lyapunov stability theory. The validity of the method is verified by a series of comparisons on numerical simulation results.
Highlights
Hypersonic flight vehicles (HFVs) refer to vehicles that travel at a velocity greater than 5 Mach.[1]
Since HFV works in a harsh environment where flight conditions and parameters often change radically, faults may occur in actuators such as elevators and rudders
A fault estimation and fault-tolerant control (FTC) scheme is developed for HFV subject to body flap additive fault and modeling error
Summary
Hypersonic flight vehicles (HFVs) refer to vehicles that travel at a velocity greater than 5 Mach.[1]. It provides more degrees of freedom that could reduce the effects of uncertainty in the fuzzy rules.[19,20,21] Given such advantages, an interval type-2 fuzzy estimation algorithm is designed to represent the unknown adverse effects of modeling error and faults in this article. These aerodynamic surfaces are usually too weak to satisfy control commands.[22] reaction control system (RCS) will be introduced to provide the residual control torque.[23] In the literature,[10] the derived control torque is distributed by pseudoinverse method directly With this allocator, the utilization ratio of aerosurfaces is definitely low because of the fixed calculation. The control objective is to design an FTC law with respect to the control torque generated by aerodynamic surfaces and RCS jets such that the attitude angles can track the given commands asymptotically even if the body flap fault and disturbances exist.
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