Study on inversion control for integrated helicopter/engine system with variable rotor speed based on state variable model
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Yong Wang
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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.
References
1. DeSmidt, HA, Smith, EC, Bill, RC, Wang, K-W. Comprehensive modeling and analysis of rotorcraft variable speed propulsion system with coupled engine/transmission/rotor dynamics. Washington, D.C.: NASA/CR-2013-216502.Suche in Google Scholar
2. Gerard, EW. Overview of variable-speed power-turbine research. Washington, D.C.: NASA/TM-2012-217605.Suche in Google Scholar
3. Wang, Y, Zheng, Q, Zhang, H, Xu, Z. Research on integrated control method of tiltrotor with variable rotor speed based on two-speed gearbox. Int J Turbo JetEngines 2021:38:173–83. https://doi.org/10.1515/tjj-2018-0004.Suche in Google Scholar
4. Endwell, OD. NASA overview: fundamental aeronautics program research activities on noise impacts. noise impacts roadmap annual meeting. Washington: Springer Press; 2011.Suche in Google Scholar
5. Johnson, W, Yamauchi, GK, Watts, ME. NASA heavy lift rotorcraft systems investigation. Nanjing: SAE Technical Paper; 2005.10.4271/2005-01-3149Suche in Google Scholar
6. Wang, Y, Zheng, Q, Zhang, H, Gao, Y. A study on nonlinear model predictive control for helicopter/engine with variable rotor speed based on linear kalman filter. Int J Turbo Jet Engines 2022;39:357–66. https://doi.org/10.1515/tjj-2019-0016.Suche in Google Scholar
7. Widrow, B, Walach, E. Translated by LIU Shutang, HAN Chongzhao. Adaptive inverse montrol. Xian: Xian Jiaotong University Press; 2000:1–27.Suche in Google Scholar
8. Shafai, B, Pi, CT, Nork, S, Linder, SP. Proportional integral adaptive observer for parameter and disturbance estimations. In: Proceedings of the IEEE conference on decision and control, vol. 4; 2002.10.1109/CDC.2002.1185119Suche in Google Scholar
9. Cao, L, Zhang, S, Li, X, Liu, Y. Nonlinear flight controller design using H∞ optimization and hierarchy-structured dynamic inversion. Acta Aeronautica Et Astronautica Sinica 2011;32:1678–85. https://doi.org/10.1016/S1005-0302(11)60031-5.Suche in Google Scholar
10. Avanzini, G, Thomson, D, Torasso, A. Model predictive control architecture for rotorcraft inverse simulation. J Guid Control Dynam 2012;36:207–17. https://doi.org/10.2514/1.56563.Suche in Google Scholar
11. Sieberling, S. Design of a robust generic flight control system using incremental nonlinear dynamic inversion. Unpublished M. Sc. Thesis, Faculty of Aerospace Engineering, In Delft: Delft University of Technology; 2009.Suche in Google Scholar
12. Wedershoven, J. Analysis of nonlinear dynamic inversion based control law designs. Unpublished M. Sc. Thesis, Faculty of Aerospace Engineering, In Delft : Delft University of Technology; 2010.Suche in Google Scholar
13. Edwards, C, Lombaerts, T, Smaili, H. Fault tolerant flight control. Lecture notes in control and information sciences, vol. 399; Berlin, Heidelberg: Springer Press; 210:1–560pp.10.1007/978-3-642-11690-2Suche in Google Scholar
14. Van Oort, ER. Adaptive backstepping control and safety analysis for modern fighter aircraft. Delft: TU Delft, Delft University of Technology; 2011.Suche in Google Scholar
15. Kumar, K. Inverse adaptive neuro-control of a turbo-fan engine. AIAA guidance, navigation, and control conference and exhibit. Portland, OR: American Institute of Aeronautics and Astronautics, Inc; 1999:354–4pp.Suche in Google Scholar
16. Wen-Fei, HU, Huang, JQ. Study of aeroengine adaptive inverse control. J Aerospace Power 2005;2005:293–7. https://doi.org/10.13675/j.cnki.tjjs.2008.02.025.Suche in Google Scholar
17. Yao, Y, Sun, J. Aero-engine direct thrust control based on neural network inverse control. J Propul Technol 2008;29:249–52. https://doi.org/10.13675/j.cnki.tjjs.2008.02.025.Suche in Google Scholar
18. Simplício, P, Pavel, MD, Van Kampen, E, Chu, QP. An acceleration measurements-based approach for helicopter nonlinear flight control using incremental nonlinear dynamic inversion. Control Eng Pract 2013;21:1065–77. https://doi.org/10.1016/j.conengprac.2013.03.009.Suche in Google Scholar
19. Wang, Y, Zheng, Q, Zhang, H, Chen, M. The LQG/LTR control method for turboshaft engine with variable rotor speed based on torsional vibration suppression. J Low Freq Noise Vibrat Active Control 2019. https://doi.org/10.1177/1461348419847010.Suche in Google Scholar
20. Fan, S. Aeroengine control. Xian: Northwestern Polytecnical Press; 2008, vol. 6.Suche in Google Scholar
21. Wu, JF, Guo, YQ. Design and simulation of aero-engine steady-state and transient-state control integration. J Aerospace Power 2013;28:1436–40. https://doi.org/10.13224/j.cnki.jasp.2013.06.016.Suche in Google Scholar
22. Lu, B, Wu, F, Kim, SW. Switching LPV control for high performance tactical aircraft. Providence, RI. AIAA-2010-7903; 2010.Suche in Google Scholar
23. Zhang, J, Li, J. Adaptive backstepping sliding mode control for wheel slip tracking of vehicle with uncertainty observer. Measur Control 2018;51:396–405. https://doi.org/10.1177/0020294018795321.Suche in Google Scholar
24. Jiang, R. Linear-parameter-varying control design for aero-engine. Njoyanjing: Nanjing University of Aeronautics and Astronautics; 2015.Suche in Google Scholar
© 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
