A study on optimal rotor speed control method for helicopter power system considering the influence of infrared suppressors
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Zhaoguang Wang
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Jiatong Du
Abstract
In order to realize the most economical operation of helicopter power system, the optimal rotor speed control method is proposed and designed. Firstly, the simplified performance calculation model of helicopter required power and turboshaft engine are established, which constitute the performance calculation model of helicopter power system together. Then, according to the above model, through applying blade loading constraint and selecting the minimum engine fuel flow as the optimization objective, an integrated optimization method of optimal rotor speed based on golden section method is proposed, which reveals the variation law of optimal rotor speed under different operation conditions. Finally, the numerical simulation and hardware-in-loop (HIL) simulation are conducted separately to validate the optimal rotor speed control method. The results indicate that compared with constant rotor speed operation, optimal rotor speed control method can decrease engine fuel flow by more than 21 %, which proves the significant effectiveness and satisfactory feasibility. The optimal rotor speed control method ensures that the helicopter power system operates at the optimal rotor speed, and is beneficial to reach the most economical cruise target.
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Research ethics: Not applicable.
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Author contributions: The author(s) have (has) accepted responsibility for the entire content of this manuscript and approved its submission.
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Competing interests: The author(s) state(s) no conflict of interest.
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Research funding: None declared.
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Data availability: The raw data can be obtained on request from the corresponding author.
References
1. Goulos, L, Pachidis, V, D’Lppolito, R, Stevens, J, Smith, C. An integrated approach for the multidisciplinary design of optimum rotorcraft operations. J Eng Gas Turbines Power 2012;134:091701.1–091701.10.10.1115/1.4006982Search in Google Scholar
2. Amri, H, Feil, R, Hajek, M. Possibilities and difficulties for rotorcraft using variable transmission drive trains. CEAS Aeronaut J 2016;7:333–44. https://doi.org/10.1007/s13272-016-0191-6.Search in Google Scholar
3. Garre, W, Amri, H, Pflumm, T, Paschinger, P, Weigand, M. Helicopter configurations and drive train concepts for optimal variable rotor-speed utilization. Munich: Deutsche Gesellschaft für Luft-und Raumfahrt-Lilienthal-Oberth eV; 2017.Search in Google Scholar
4. Stevens, MA, Handschuh, RF, Lewicki, DG. Variable/multispeed rotorcraft drive system concepts. TM-2009-215456; March 2009.Search in Google Scholar
5. Floras, MW, Johnson, W. Performance analysis of the slowed-rotor compound helicopter configuration. J Am Helicopter Soc 2009;54:12–23.10.4050/JAHS.54.022002Search in Google Scholar
6. Welch, GE. Assessment of aerodynamic challenges of a variable-speed power turbine for large civil tilt-rotor application. NASA Report, NASA/TM-2010-216758; 2010.Search in Google Scholar
7. Han, D, Barakos, GN. Variable-speed tail rotors for helicopters with variable-speed main rotors. Aeronaut J 2017;121:433–48. https://doi.org/10.1017/aer.2017.4.Search in Google Scholar
8. Karem, AE. Optimum speed rotor. U.S. Patent 6007298; 1999-12-28.Search in Google Scholar
9. Karem, AE Optimum speed tilt rotor. U.S. Patent 6641365; 2003-11-4.Search in Google Scholar
10. Litt, JS, Edwards, JM, DeCastro, JA. A sequential shifting algorithm for variable rotor speed control. NASA/TM-2007-214842; 2007.Search in Google Scholar
11. Welch, GE, McVetta, AB, Stevens, MA, Howard, SA, Giel, PW, Ameri, AA, et al.. Variable-speed power-turbine research at Glenn Research Center. NASA/TM- 2012-217605; 2012.Search in Google Scholar
12. Steiner, JH. An investigation of performance benefits and trim requirements of a variable speed helicopter rotor. PA: The Pennsylvania State University Master’s thesis; 2008.Search in Google Scholar
13. DiOttavio, J, Friedmann, D. Operational benefits of an optimal widely variable speed rotor. In: Phoenix: in proceedings of AHS 66th annual forum; 2010, vol 1. 1865–71 pp. ISBN: 978-1-61782-926-0.Search in Google Scholar
14. Garavello, A, Benini, E. Preliminary study on a wide-speed-range helicopter rotor/turboshaft system. J Aircraft 2012;49:1032–8. https://doi.org/10.2514/1.c031526.Search in Google Scholar
15. Miste, GA, Pellegrini, A, Benini, E. Variable speed power turbine preliminary design optimization for rotorcraft applications. Barcelona: 11th World Congress on Computational Mechanics; 2014.Search in Google Scholar
16. Ramanujam, R, Abhishek, A. Performance optimization of variable-speed and variable-geometry rotor concept. J Aircraft 2016;54:476–89. https://doi.org/10.2514/1.c033869.Search in Google Scholar
17. Guoqiang, C. Study for real-time optimization control and hardware platform based on integrated helicopter/turboshaft engine system. Nanjing: Nanjing University of Aeronautics and Astronautics; 2012.Search in Google Scholar
18. Yan, Q, Du, Z, Zhou, X, Huang, K. The effect of variable rotor speed flight control on the output response of turboshaft engines. Propuls Technol 2021;42:9.Search in Google Scholar
19. Lang, K, Xia, P, Smith, EC, Shang, L. Normalized adaptive hybrid control algorithms for helicopter vibration with variable rotor speed. J Am Helicopter Soc 2022;67:1–12.10.4050/JAHS.67.022008Search in Google Scholar
20. Chandrasekaran, R, Hodges, DH. Performance advantages and resonance analysis of a variable speed rotor using geometrically exact beam formulations. In: VFS international 77th annual forum & technology display; 2021.10.4050/F-0077-2021-16768Search in Google Scholar
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Articles in the same Issue
- Frontmatter
- Proper Orthogonal Decomposition analysis of mode switching in supersonic jets impinging on flat and corrugated plates
- Impact of cavity and ramp configuration on the combustion performance of a strut-based scramjet combustor
- In-service load calculation surrogate models for high-pressure turbine blade life digital twin
- Numerical analysis on the effect of passive control geometry in supersonic jet mixing enhancement
- Study on one-dimensional performance prediction of multi-stage axial turbine based on the blade height
- Dynamic characteristics of open-ends squeeze film dampers with air ingestion
- Fluid flow in a microdiffuser at small Reynolds numbers
- A study on optimal rotor speed control method for helicopter power system considering the influence of infrared suppressors
- Effects of turbulence and flamelet combustion modelling on the CFD simulation of a dual inlet ramjet combustor
- Design and combustion characteristics analysis of a static shaft turbofan engine
- Aerothermal effects of squealer openings on a cavity tip in a turbine cascade
- Endwall heat transfer in wedge channel with teardrop pin fins, circular fins and oblong pin fins
- Virtual deflection with synthetic jet actuators at high angles of attack
- Design of mode transition control system for tandem TBCC engine based on direct performance parameters closed-loop control
- Effect of tab shape, length, and placement on the over-expanded free jet at Mach 2.0
- Influence of the ending position of controllable speed casing on a transonic compressor rotor tip leakage flow
- Integrated modeling and coupling characteristics analysis of helicopter/engine/infrared suppressor
- Effect of velocity ratio and Mach number on thin lip coaxial jet
- C conjugate heat transfer simulation of swirl internal cooling on blade leading edge
- Influence of inlet structure on combustion flow structure in magnesium powder fueled water ramjet engine
- Research on high-bandwidth linear active disturbance rejection control method for variable speed turboshaft engine
- Numerical investigation of force over the horizontal jet tab of various sector angle fixed to the convergent-divergent nozzle exit
Articles in the same Issue
- Frontmatter
- Proper Orthogonal Decomposition analysis of mode switching in supersonic jets impinging on flat and corrugated plates
- Impact of cavity and ramp configuration on the combustion performance of a strut-based scramjet combustor
- In-service load calculation surrogate models for high-pressure turbine blade life digital twin
- Numerical analysis on the effect of passive control geometry in supersonic jet mixing enhancement
- Study on one-dimensional performance prediction of multi-stage axial turbine based on the blade height
- Dynamic characteristics of open-ends squeeze film dampers with air ingestion
- Fluid flow in a microdiffuser at small Reynolds numbers
- A study on optimal rotor speed control method for helicopter power system considering the influence of infrared suppressors
- Effects of turbulence and flamelet combustion modelling on the CFD simulation of a dual inlet ramjet combustor
- Design and combustion characteristics analysis of a static shaft turbofan engine
- Aerothermal effects of squealer openings on a cavity tip in a turbine cascade
- Endwall heat transfer in wedge channel with teardrop pin fins, circular fins and oblong pin fins
- Virtual deflection with synthetic jet actuators at high angles of attack
- Design of mode transition control system for tandem TBCC engine based on direct performance parameters closed-loop control
- Effect of tab shape, length, and placement on the over-expanded free jet at Mach 2.0
- Influence of the ending position of controllable speed casing on a transonic compressor rotor tip leakage flow
- Integrated modeling and coupling characteristics analysis of helicopter/engine/infrared suppressor
- Effect of velocity ratio and Mach number on thin lip coaxial jet
- C conjugate heat transfer simulation of swirl internal cooling on blade leading edge
- Influence of inlet structure on combustion flow structure in magnesium powder fueled water ramjet engine
- Research on high-bandwidth linear active disturbance rejection control method for variable speed turboshaft engine
- Numerical investigation of force over the horizontal jet tab of various sector angle fixed to the convergent-divergent nozzle exit
