The Design and Semi-Physical Simulation Test of Fault-Tolerant Controller for Aero Engine
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Yuan Liu
Abstract
A new fault-tolerant control method for aero engine is proposed, which can accurately diagnose the sensor fault by Kalman filter banks and reconstruct the signal by real-time on-board adaptive model combing with a simplified real-time model and an improved Kalman filter. In order to verify the feasibility of the method proposed, a semi-physical simulation experiment has been carried out. Besides the real I/O interfaces, controller hardware and the virtual plant model, semi-physical simulation system also contains real fuel system. Compared with the hardware-in-the-loop (HIL) simulation, semi-physical simulation system has a higher degree of confidence. In order to meet the needs of semi-physical simulation, a rapid prototyping controller with fault-tolerant control ability based on NI CompactRIO platform is designed and verified on the semi-physical simulation test platform. The result shows that the controller can realize the aero engine control safely and reliably with little influence on controller performance in the event of fault on sensor.
Funding statement: This work was supported by National Natural Science Foundation of China (No.51176075, No.61104067).
Nomenclature
fuel consumption, L/min
nozzle area
speed of low-pressure rotor, %
speed of high-pressure rotor, %
inlet temperature of low-pressure turbine, K
the demand of fuel quantity, kg/s
the remained quantity of fuel, kg/s
the current dynamic coefficient of fuel consumption acceleration
speed of high-pressure rotor which is output by simplified real-time model, %
speed of high-pressure rotor which is output by simplified real-time model modified by Kalman filter, %
the difference between actual measurement and static value of simplified real-time model
the difference between actual controlled quantity and static controlled quantity of simplified real-time model
the filter output
the output of the simplified real-time model
standard deviation
- HIL
hardware-in-the-loop
- WSSR
weighted sum-squared residual
- CLM
component-level model
- LVDT
linear variable differential transformer
- NI
National Instrument
- PXI PCI
extensions for Instrumentation
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© 2017 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Expanded R&D by Jet-engine-steering Revolution
- Scientific Paper
- Switching LPV Control with Double-Layer LPV Model for Aero-Engines
- On-Board Real-Time Optimization Control for Turbo-Fan Engine Life Extending
- Investigation of Engine Oil-cooling Problem during Idle Conditions on Pusher Type Turbo Prop Aircraft
- Regulating Effect of Asymmetrical Impeller on the Flow Distributions of Double-sided Centrifugal Compressor
- Numerical Prediction of the Influence of Thrust Reverser on Aeroengine’s Aerodynamic Stability
- Performance Evaluation of an Experimental Turbojet Engine
- The Design and Semi-Physical Simulation Test of Fault-Tolerant Controller for Aero Engine
- The Ignition of Two Phase Detonation by a Branching Detonation Tube
- Tab Geometry Effect on Supersonic Elliptic Jet Control
Articles in the same Issue
- Frontmatter
- Expanded R&D by Jet-engine-steering Revolution
- Scientific Paper
- Switching LPV Control with Double-Layer LPV Model for Aero-Engines
- On-Board Real-Time Optimization Control for Turbo-Fan Engine Life Extending
- Investigation of Engine Oil-cooling Problem during Idle Conditions on Pusher Type Turbo Prop Aircraft
- Regulating Effect of Asymmetrical Impeller on the Flow Distributions of Double-sided Centrifugal Compressor
- Numerical Prediction of the Influence of Thrust Reverser on Aeroengine’s Aerodynamic Stability
- Performance Evaluation of an Experimental Turbojet Engine
- The Design and Semi-Physical Simulation Test of Fault-Tolerant Controller for Aero Engine
- The Ignition of Two Phase Detonation by a Branching Detonation Tube
- Tab Geometry Effect on Supersonic Elliptic Jet Control
