Study on inversion control for integrated helicopter/engine system with variable rotor speed based on state variable model
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Yong Wang
and
Haoying Chen
Abstract
In order to realize the fast response control for turboshaft engine with variable rotor speed, a dynamic inversion (DI) control method based on state variable model of turboshaft engine is proposed. Meanwhile, in order to expand the application of dynamic inversion controller, the linear parameter varying (LPV) model of turboshaft engine is applied, which constitutes the LPV/DI controller together. The simulation results shows that compared with the conventional PID controller, the LPV/DI controller can effectively reduce the overshoot/droop of the power turbine speed to less than 1% under different flight conditions. The control effect is remarkable and the robust performance is superior.
Funding source: National Science and Technology Major Project
Award Identifier / Grant number: 2017-V-0004-0054
Funding source: Research on the Basic Problem of Intelligent Aero-engine
Award Identifier / Grant number: 2017-JCJQ-ZD-047-21
Funding source: National Natural Science Foundation of China
Award Identifier / Grant number: 51906102
Funding source: China Postdoctoral Science Foundation Funded Project
Award Identifier / Grant number: 2019M661835
Funding source: Aeronautics Power Foundation
Award Identifier / Grant number: 6141B09050385
Funding source: Postgraduate Research & Practice Innovation Program of Jiangsu Province
Award Identifier / Grant number: KYCX20_0218
Funding source: Six Talents Peak Project of Jiangsu Province
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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: The work has been co-supported by National Science and Technology Major Project under Grant 2017-V-0004-0054, Research on the Basic Problem of Intelligent Aero-engine under Grant 2017-JCJQ-ZD-047-21, National Natural Science Foundation of China under Grant 51906102, China Postdoctoral Science Foundation Funded Project under Grant 2019M661835, Aeronautics Power Foundation under Grant 6141B09050385, Postgraduate Research & Practice Innovation Program of Jiangsu Province under Grant KYCX20_0218 and Six Talents Peak Project of Jiangsu Province.
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Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
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© 2020 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- 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
Articles in the same Issue
- 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
