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Bifurcation-induced limits of a controller-reconfigured F-16 subject to actuator failures
Conference proceeding

Bifurcation-induced limits of a controller-reconfigured F-16 subject to actuator failures

S Thomas, H.G Kwatny, Bor-Chin Chang and IEEE
Proceedings of 2005 IEEE Conference on Control Applications, 2005. CCA 2005
2005
DOI: https://doi.org/10.1109/CCA.2005.1507119
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Abstract

Actuators Aerodynamics Aerospace control Aircraft Bifurcation Control systems Guidelines Nonlinear control systems Regulators Stability
Complex systems like the F-16 when subject to actuator failures operate in nonlinear regimes and probably in the vicinity of bifurcation points. Therefore, in designing reconfigured controllers a designer must be aware of all bifurcation points, and their characteristics, within the impaired flight envelope. This work is the first step in that direction. The other limitations that were identified are the stability limits and the control saturation points. We considered both the nominal system, and the reconfigured system with the left elevator stuck. The nominal controller is designed according to the guidelines in the literature. The reconfigured controller is designed as a regulator with disturbance rejection capabilities. The bifurcations are associated with attempting to regulate the velocity and orientation of the aircraft. The main issues at the bifurcation points, in both the nominal and reconfigured system, are that the aircraft becomes uncontrollable and the control inputs become dependent

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Web of Science research areas
Automation & Control Systems
Computer Science, Artificial Intelligence
Robotics
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