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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: [email protected]
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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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