Aircraft Engine Fault Tolerant Control Using Interval Error Observation
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Solution Overview
Problem
Existing aircraft engine control systems face challenges in actively managing actuator and sensor faults under noise signal interference, leading to instability and increased maintenance costs, as traditional methods require redesigning controllers for various fault conditions and lack robustness against noise.
Innovation Solution
An interval error observer-based active fault tolerant control method is developed, which reconfigures the system to match the fault-free state without altering controller structure or parameters, using affine parameter-dependent LPV models, error feedback controllers, virtual sensors, and actuators to autonomously eliminate faults and improve reliability.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional passive fault tolerant control is used to pre-design a controller based on pre-judged possible faults, then the system stability is improved, but the device complexity increases and the controller becomes conservative
Solution Approach 1:
The method pre-calculates and stores optimal controller parameters for various fault conditions in a lookup table before operation. During runtime, the system simply queries the table based on detected fault conditions and applies the pre-computed parameters, avoiding complex real-time optimization while maintaining stability
Solution Approach 2:
The system automatically detects fault conditions through sensors and autonomously retrieves appropriate control parameters from the pre-established lookup table without requiring manual intervention or complex decision-making logic, enabling self-adjustment to fault conditions
2Adaptability or versatility
If active fault tolerant control is used to reconfigure the system after fault occurs, then the controller conservatism is reduced, but the system complexity increases
Solution Approach 1:
All possible reconfiguration strategies and optimal control parameters for different fault scenarios are pre-computed and stored in a lookup table during the design phase. When a fault occurs, the system simply retrieves the appropriate pre-computed parameters based on the detected fault condition, avoiding complex real-time calculations
Solution Approach 2:
The system adjusts control parameters by querying a lookup table that contains pre-determined parameter sets for various fault conditions. This allows the system to adapt to faults by changing parameters without implementing complex real-time optimization algorithms
3Productivity
If existing control methods are used to process noise signal interference, then the control system can operate, but the fault tolerance performance deteriorates
Solution Approach 1:
The system pre-processes and characterizes noise signal patterns during the design phase, incorporating noise robustness criteria into the lookup table parameter optimization. This allows the controller to inherently reject noise while maintaining fault tolerance without requiring complex real-time noise filtering
Solution Approach 2:
The system continuously monitors system performance and fault detection residuals, using this feedback to query the appropriate parameters from the lookup table that are optimized for both noise rejection and fault tolerance, achieving dual objectives through parameter selection rather than complex real-time processing
Data Source
AI summary
The present invention provides an interval error observer-based aircraft engine active fault tolerant control method, and belongs to the technical field of aircraft control. The method comprises: tracking the state and the output of a reference model of an aircraft engine through an error feedback controller; compensating a control system of the aircraft engine having a disturbance signal and actuator and sensor faults through a virtual sensor and a virtual actuator; observing an error between a system with fault of the aircraft engine and the reference model through an interval error observer, and feeding back the error to the error feedback controller; and finally, using a difference between the output of the reference model of the system with fault and the output of the virtual actuator as a control signal to realize active fault tolerant control of the aircraft engine.