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Research and modeling of force fighting equalisation for aircraft rudder’s triple active actuation system

Published online by Cambridge University Press:  17 May 2022

D.W. Li ,
M.X. Lin Open the ORCID record for M.X. Lin [Opens in a new window]  and
L. Tian
D.W. Li
Affiliation:
National Demonstration Center for Experimental Mechanical Engineering Education (Shandong University), Key Laboratory of High-efficiency and Clean Mechanical Manufacture of Ministry of Education, School of Mechanical Engineering, Shandong University, Jinan, China Aviation Industry Corporation of China, AVIC XI’AN Aircraft Industry (Group) Company LTD. Xi’an, China
M.X. Lin*
Affiliation:
National Demonstration Center for Experimental Mechanical Engineering Education (Shandong University), Key Laboratory of High-efficiency and Clean Mechanical Manufacture of Ministry of Education, School of Mechanical Engineering, Shandong University, Jinan, China
L. Tian
Affiliation:
QINGAN Co., LTD. Xi’an, China
*
*Corresponding author. Email: mxlin@sdu.edu.cn
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Abstract

This paper presents a new approach to force fighting equalisation in a redundant active-active-active rudder actuation system that is used for the primary flight control system of a turboprop regional aircraft. The related coupled problem of force fighting scenario, and the hydraulic architecture of electronic-hydrostatic actuator (EHA) are analysed, the mathematical model of the EHA system is built. The virtual test bench is designed to evaluate the performance of the force fighting equalisation strategy. The proposed methodology is tested on an iron bird test rig. The physical experiment shows that the fighting force is minimised under all flight conditions, meets the low cost requirement and can be a very reliable system. The proposed methodology can be applied to other types of aircraft’ flight actuation systems.

Keywords

Force fightingRedundant actuation systemFlight actuation systemControl lawElectronic-hydrostatic actuator (EHA)
Type
Research Article
Information
The Aeronautical Journal , Volume 126 , Issue 1304 , October 2022 , pp. 1801 - 1814
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Copyright
© The Author(s), 2022. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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References

Maré, J-C. (2017). Aerospace actuators 2 (signal-by-wire and power-by-wire) || notations and acronyms, doi: 10.1002/9781119332442, 235–243.CrossRefGoogle Scholar
Xue, Y. and Yao, Z.Q. A way to mitigate force-fight oscillation based on pressure and position compensation for fly-by-wire flight control systems, Trans. Japan Soc. Aeronaut. Space Sci., 2020, 63, (1), pp 1–7.Google Scholar
Ma, C.Y. Fly-By-Wire Dual-Dual Flight Control Actuation System, 1, 1998.CrossRefGoogle Scholar
Cochoy, O., Hanke, S. and Carl, U.B. Concepts for position and load control for hybrid actuation in primary flight controls, Aerosp. Sci. Technol., 2007, 11, (2–3), pp 194–201.CrossRefGoogle Scholar
Flight Control Surface Actuation Force Fight Mitigation System and Method. U.S. Patent No. 8,583,293 B2, 12 November 2013.Google Scholar
Wang, L. and Mare, J.C. A force equalization controller for active/active redundant actuation system involving servo-hydraulic and electro-mechanical technologies, Proc. Inst. Mech. Eng. G J. Aerosp. Eng., 2014, 228, (G10), pp 1768–1787.CrossRefGoogle Scholar
Rehman, W.U., Wang, S., Wang, X. and Kamran, A. A position synchronization control for HA/EHA system, Fluid Power and Mechatronics (FPM), 2015 International Conference on IEEE, 2015.Google Scholar
Röben, T., Stumpf, E., Weber, G. and Grom, T. An innovative all-active hybrid actuation system, AIAA Modeling & Simulation Technologies Conference 2015.CrossRefGoogle Scholar
Rehman, W.U., Wang, X., Wang, S. and Azhar, I. Motion synchronization of HA/EHA system for a large civil aircraft by using adaptive control, Guidance, Navigation & Control Conference IEEE, 2017.CrossRefGoogle Scholar
Rehman, W.U., Nawaz, H., Wang, S., Wang, X. and Elahi, H. Trajectory based motion synchronization in a dissimilar redundant actuation system for a large civil aircraft, 2017 29th Chinese Control And Decision Conference (CCDC), 2017.Google Scholar
Ijaz, S., Yan, L. and Hamayun, M.T. Fractional order modeling and control of dissimilar redundant actuating system used in large passenger aircraft, Chinese J. Aeronaut., 2018, 31, pp 279–290.CrossRefGoogle Scholar
Li, T., Yang, T., Cao, Y., Xie, R. and Wang, X. Adaptive robust fault-tolerant synchronization control for a dual redundant hydraulic actuation system with common-mode fault, Math. Prob. Eng., 2018, 2018, pp 1–14.Google Scholar
Maré, J-C. “Aerospace Actuators 3 (European Commercial Aircraft and Tiltrotor Aircraft) || European Commercial Aircraft before the Airbus A320.” doi: 10.1002/9781119505433(2018), 1–30.CrossRefGoogle Scholar
Ijaz, S., Hamayun, M.T., Anwaar, H., Yan, L. and Li, M.K. “LPV modeling and tracking control of dissimilar redundant actuation system for civil aircraft, Int. J. Control Autom. Syst., 2019, 17, pp 705–715.CrossRefGoogle Scholar
Kang, R., Jiao, Z., Shuai, W., Shang, Y. and Mare, J.C. The nonlinear accuracy model of electro-hydrostatic actuator, 2008 IEEE Conference on Robotics, Automation and Mechatronics, RAM 2008, 21–24 September 2008, Chengdu, China IEEE, 2008 CrossRefGoogle Scholar
Röben, T. Hybrid actuation in primary flight control systems: a force-fight inhibiting system architecture, Rheinisch-Westfälischen Technischen Hochschule Aachen, [PhD Thesis], 2018.Google Scholar
Kang, R., Jiao, Z., Wang, S. and Chen, L. Design and simulation of electro-hydrostatic actuator with a built-in power regulator, Chinese J. Aeronaut., 2009, 22, (6), pp 700–706.Google Scholar
Kuznetsov, V.E., Khanh, N.D. and Lukichev, A.N. System for synchronizing forces of dissimilar flight control actuators with a common controller, 2020 XXIII International Conference on Soft Computing and Measurements (SCM), 2020.Google Scholar
Li, Z., Shang, Y., Jiao, Z., Lin, Y., Wu, S. and Li, X. Analysis of the dynamic performance of an electro-hydrostatic actuator and improvement methods, Chinese J. Aeronaut., 2018, 31, pp 2312–2320.Google Scholar
Bauer, G. Ölhydraulik. Springer, 2011, Berlin, Germany.Google Scholar
Fesenmayr, J. Calculation of the volumetric and mechanical pump losses based on the A380 pump test results, Internal doc., Liebherr-Aerospace, 2004.Google Scholar
Ren, G., Esfandiari, M., Song, J. and Sepehri, N. “Position control of an electro-hydrostatic actuator with tolerance to internal leakage,” IEEE Trans. Control Syst. Technol., 2016, 24, (6), pp 2224–2232.CrossRefGoogle Scholar
Liang, T., Zhang, Y. and Wang, H. Fly by wire actuation system modeling and force fight equalization research, J. Northwest. Polytech. Univ., 2020, 38, (3), pp 643–648.Google Scholar
AIR4253: Description of Actuation Systems for Aircraft With Fly-By-Wire Flight Control Systems - SAE International, 2021.Google Scholar
Chen, Y., Tian, J., Wang, X., et al. “Electrical Flight Control System Development and Certification for Regional Aircraft,” Shang Hai Jiao Tong University Press, ShangHai, China, 2019, pp 205–208.Google Scholar