Aircraft Actuator Fault Diagnosis and Isolation using Robust Incremental Nonlinear Dynamic Inversion

Authors

1 Faculty of Electrical and Robotic, Eng

2 Faculty of Electrical Engineering Shahrood University of Technology

Abstract

One of the major faults accrued in the aircraft is corresponding to its actuators. In order to fault diagnosis and isolation in the aircraft actuator, this paper presents a new robust method based on the incremental nonlinear dynamic inversion, which is robust to the disturbance and uncertainties. The produced residual is robust to the system uncertainties, and the adaptive threshold is designed to evaluate this residual with fuzzy logic, which is altered in the presence of disturbance or variation in the input command to prevent faulty detection. Since this method requires the online knowledge of the upper bound of undesirable factors (disturbance and uncertainty) and the disturbance occurrence on the system, new equations is developed to calculate this bound and an innovative structure is suggested to detect the disturbance event. In order to evaluate the proposed method, it is simulated on the nonlinear dynamics of the Boeing-747 considering the coupling between the longitudinal and lateral dynamics, whereas the disturbance is applied on the three axes at different times and the rudder actuator fault is locked to the aircraft. Simulations verify that despite the uncertainty and disturbance, the following of the input commands is well performed and the timing of the operator's fault and the location of the operator is determined according to the adaptive threshold.

Keywords

References

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Journal of Solid and Fluid Mechanics
Volume 10, Issue 3
October 2020
Pages 103-120

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