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Control of a Helicopter Main Gearbox Active Suspension System

[+] Author Affiliations
Jonathan Rodriguez

Airbus Helicopters, Marignane, FranceLAMCOS - INSA Lyon, Lyon, France

Luc Gaudiller, Simon Chesne

LAMCOS - INSA Lyon, Lyon, France

Paul Cranga

Airbus Helicopters, Marignane, France

Paper No. DETC2014-34278, pp. V008T11A085; 10 pages
doi:10.1115/DETC2014-34278
From:
  • ASME 2014 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference
  • Volume 8: 26th Conference on Mechanical Vibration and Noise
  • Buffalo, New York, USA, August 17–20, 2014
  • Conference Sponsors: Design Engineering Division, Computers and Information in Engineering Division
  • ISBN: 978-0-7918-4641-4
  • Copyright © 2014 by ASME

abstract

This paper considers the control of a helicopter gearbox electromagnetic suspension for a complete multibody model of the structure. As the new generation of helicopters includes variable engine RPM during flight, it becomes relevant to add active control in their suspension systems. Most of active system performances derive directly from the controller construction, its optimization to the system controlled and the disturbances expected. An investigation on a FXLMS control algorithm has been made to optimize it in terms of narrow band disturbance rejection. In this paper an active suspension based on DAVI principle is evaluated. Firstly, a multibody model is set up to estimate realistic acceleration levels inside the cabin. Then multiple controllers are tested, minimizing vibrations on different parts of the helicopter structure. The simulations tend to prove that it is possible to implement an effective active suspension with a low power actuator and obtain a significant vibration reduction level for a frequency bandwidth centered at the natural frequency of the original DAVI.

Copyright © 2014 by ASME

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