학술논문

Output Feedback Fault Tolerant Control for Linear Parameter Varying Plants Considering Imperfect Fault Information
Document Type
Periodical
Source
IEEE Access Access, IEEE. 12:12257-12270 2024
Subject
Aerospace
Bioengineering
Communication, Networking and Broadcast Technologies
Components, Circuits, Devices and Systems
Computing and Processing
Engineered Materials, Dielectrics and Plasmas
Engineering Profession
Fields, Waves and Electromagnetics
General Topics for Engineers
Geoscience
Nuclear Engineering
Photonics and Electrooptics
Power, Energy and Industry Applications
Robotics and Control Systems
Signal Processing and Analysis
Transportation
Actuators
Estimation
Resource management
Output feedback
Observers
Fault diagnosis
Aerodynamics
Fault tolerance
Sliding mode control
Aerospace control
Control systems
sliding mode control
robust control
aerospace control
control system synthesis
Language
ISSN
2169-3536
Abstract
This study focuses on the design of an integral sliding mode-based fault-tolerant control allocation (ISM-FTCA) scheme for the class of uncertain linear parameter varying (LPV) systems. The objective is to tackle the fault occurring in the actuator channel by exploiting available redundancy through a control allocation (CA) scheme in an output feedback framework. In this work, the assumption on the estimation of actuator effectiveness level, which was previously considered (in the existing literature) to be perfect coming from fault diagnosis and identification (FDI) scheme, is relaxed due to its bit conservatism nature. The uncertain system dynamics, originating due to faults, failures, and imperfect fault information, are catered to by designing a virtual control law using the LPV output ISM control strategy. An unknown input LPV observer is designed to provide the estimate of unmeasured plant states to the virtual control law. This work thoroughly investigates the closed-loop dynamics of the uncertain LPV system, utilizing the small gain theorem to develop criteria for stability. These conditions provide crucial insights into the performance and robustness of the suggested strategy. Finally, the efficiency of the proposed control scheme is verified in the simulation environment by using a nonlinear 6-degree-of-freedom dynamic model of the octarotor unmanned aerial vehicle (UAV) system. Numerical simulations under different faults and failures conditions and in the presence of imprecise estimation validate the closed-loop performance close to nominal scenarios.