An active fault-tolerant control strategy of aircraft engines based on multi-model predictive control
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Xian Du
Abstract
In order to mitigate or even eliminate the adverse effects caused by typical components faults of aircraft engines, an active fault-tolerant strategy based on multi-model predictive control is proposed, which consists of a pre-established multi-model library, a judgement module, and corresponding predictive controllers with smooth transition switching logic. Multiple dynamic nonlinear or linear models are firstly established by means of system identification methods, based on the component-level nonlinear engine model or historical data in faults cases. The judgement module is utilized to online compare the engine measured outputs with that of all models in the pattern library and select the best matched dynamic model on the basis of outputs error quadratic performance index, thus determining the most appropriate predictive controller for the next control sample period. When a certain fault occurs, the fault model in the library could be identified and fault-model based predictive controller is activated. Finally, two kinds of pre-considered high-pressure compressor and high-pressure turbine component-level faults are taken as an example to design the active fault-tolerant controller. Simulation results show that the judgement module owns the ability to sense the fault and gives smooth switching signal to the suitable predictive controller, verifying the effectiveness of the proposed technique.
Funding source: National Natural Science Foundation of China
Award Identifier / Grant number: 61903059
Award Identifier / Grant number: 61903061
Award Identifier / Grant number: 61890924
Funding source: LiaoNing Revitalization Talents Program
Award Identifier / Grant number: XLYC1907070
Funding source: Aviation Science Foundation of China
Award Identifier / Grant number: 2019ZB063001
Funding source: National Science and Technology Major Project
Award Identifier / Grant number: 2017-V-0011-0062
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Author contribution: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.
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Research funding: This work is partly supported by the National Natural Science Foundation of China (Grant No. 61903059, 61903061, 61890924), and partly supported by LiaoNing Revitalization Talents Program (Grant No. XLYC1907070), and partly supported by Aviation Science Foundation of China (Grant No. 2019ZB063001) and National Science and Technology Major Project (Grant No. 2017-V-0011-0062).
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Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
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Copyright reminder: If any material that is included in a paper is under copyright, the authors of the paper are responsible for obtaining copyright permissions, including any information required by the copyright holder, and be able to produce such permissions upon request.
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© 2020 Walter de Gruyter GmbH, Berlin/Boston
Artikel in diesem Heft
- Frontmatter
- Integration of a transonic high-pressure turbine with a rotating detonation combustor and a diffuser
- Prediction of compressor nominal characteristics of a turboprop engine using artificial neural networks for build standard assessment
- Study on inversion control for integrated helicopter/engine system with variable rotor speed based on state variable model
- Effects of casing angle on the performance of parallel hub axial annular diffuser
- Experimental research on the performance of the forward variable area bypass injector for variable cycle engines
- Film cooling characteristics on a grooved surface with different injection orientation angles
- Aero-thermal optimization of the rim seal cavity to enhance rotor platform thermal protection
- Numerical study of the parameters of a gas turbine combustion chamber with steam injection operating on distillate fuel
- An active fault-tolerant control strategy of aircraft engines based on multi-model predictive control
- Conjugate heat transfer analysis of a radially cooled nozzle guide vane in an aero gas turbine engine
- A new method to improve the real-time performance of aero-engine component level model
- Experimental and numerical investigation of expansion corner effects on isolator performance
Artikel in diesem Heft
- Frontmatter
- Integration of a transonic high-pressure turbine with a rotating detonation combustor and a diffuser
- Prediction of compressor nominal characteristics of a turboprop engine using artificial neural networks for build standard assessment
- Study on inversion control for integrated helicopter/engine system with variable rotor speed based on state variable model
- Effects of casing angle on the performance of parallel hub axial annular diffuser
- Experimental research on the performance of the forward variable area bypass injector for variable cycle engines
- Film cooling characteristics on a grooved surface with different injection orientation angles
- Aero-thermal optimization of the rim seal cavity to enhance rotor platform thermal protection
- Numerical study of the parameters of a gas turbine combustion chamber with steam injection operating on distillate fuel
- An active fault-tolerant control strategy of aircraft engines based on multi-model predictive control
- Conjugate heat transfer analysis of a radially cooled nozzle guide vane in an aero gas turbine engine
- A new method to improve the real-time performance of aero-engine component level model
- Experimental and numerical investigation of expansion corner effects on isolator performance
