Hostname: page-component-cd9895bd7-hc48f Total loading time: 0 Render date: 2024-12-22T10:22:09.393Z Has data issue: false hasContentIssue false
  • English
  • Français

Monitoring of aircraft landing gear structure

Published online by Cambridge University Press:  03 February 2016

R. K. Schmidt
R. K. Schmidt*
Affiliation:
Messier-Dowty, Vélizy-Villacoublay, France
Get access Rights & Permissions [Opens in a new window]

Abstract

Landing gear structure is developed predominantly using safe life design criteria. Health monitoring and structural prognosis techniques for landing gear cannot focus on crack detection; techniques for determining input loads and calculating damage or methods for directly measuring material damage must be employed. This paper will discuss Messier-Dowty’s research into structural monitoring over the past several years. Principally, direct damage detection systems and load monitoring systems will be discussed.

Type
Research Article
Information
The Aeronautical Journal , Volume 112 , Issue 1131 , May 2008 , pp. 275 - 278
Copyright
Copyright © Royal Aeronautical Society 2008 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Zhi, . New kind of structural fatigue life predication smart sensor, 2004, Harbin, China.Google Scholar
2. Harting, D.R., The S/N fatigue life gage: a direct means of measuring cumulative fatigue damage, Experimental Mechanics, 1996, 6, (2).Google Scholar
3. ISG Preventive Technology. Understanding of the stress field and stress distribution of the landing gear, and comparison to the FEA readings, 2006, Messier-Dowty internal report, MD04112006.Google Scholar
4. Jentek Sensors. 4-unknown method for analysis of Messier-Dowty cadmium plated 300M steel landing gear, 2005, Messier-Dowty internal report, final letter.Google Scholar
5. Buttle, D.J., Dalzell, W. and Thayer, P.J., Nondestructive rapid residual stress measurements in rail heads with MAPS, 2001, BI NDT conference, Coventry, 18-20 September 2001.Google Scholar
6. Messier-Dowty Patent. Monitoring a parameter with low power consumption for aircraft landing gear, 2001, Data Logger, PCT/GB03/01820.Google Scholar
7. Transport Canada. Supplemental type certificate, 2003, Health Monitoring System, STC # SA03-68.Google Scholar
8. Messier-Dowty. Structural deflection and load measuring device, 2005, Patent application, PCT/CA2005/001304.Google Scholar