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Characteristic Aircraft Landing Gear Thermo-Tribo-Mechanical Model

[+] Author Affiliations
Laurent Heirendt, Hugh H. T. Liu

University of Toronto, Toronto, ON, Canada

Phillip Wang

Messier-Dowty Inc., Ajax, ON, Canada

Paper No. IMECE2012-86621, pp. 1743-1748; 6 pages
doi:10.1115/IMECE2012-86621
From:
  • ASME 2012 International Mechanical Engineering Congress and Exposition
  • Volume 3: Design, Materials and Manufacturing, Parts A, B, and C
  • Houston, Texas, USA, November 9–15, 2012
  • Conference Sponsors: ASME
  • ISBN: 978-0-7918-4519-6
  • Copyright © 2012 by ASME

abstract

A methodology for studying the characteristic thermal response of a landing gear (LG) shock absorber is presented. Rough runways induce high loads on the shock absorber bearings and because of high relative sliding speeds of the shock absorber piston, heat is dissipated which is known to have led to structural damage. In this work, an overall model has been developed that is used to outline the characteristics of the thermal behavior and identify the heat sources and sinks in the landing gear shock absorber. The developed thermo-tribo-mechanical model (TTM model) is subdivided into four parts, all using simplified but representative equations. Emphasis is placed on developing a methodological framework and studying the evolution of the average temperature in the TZI (thermal zone of interest) while taxiing and taking-off.

Copyright © 2012 by ASME
Topics: Gears , Aircraft

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