Abstract

The purpose of this paper is to present an overview of an Airbus' approach regarding fatigue spectra for large commercial aircraft. An accurate load representation is essential to the modern aircraft fatigue optimization process. The effort to develop spectra must be consistent with the efforts made to optimize materials and geometries. The main characteristics of large commercial aircraft spectra, both for prediction and testing, are presented. Recent advances are specifically highlighted.

Issue Section:
Research Papers
Keywords:
aircraft, load spectrum, structural analysis, fatigue, damage tolerance

References

1.
Miner
, “
Cumulative Damage in Fatigue
,”
ASTM Transnational Journal of Applied Mechanics
, Vol.
67
,
1945
.
2.
Elber
, “
Fatigue Crack Proopagation: Some Effects of Crack Closure on the Mechanisms of Fatigue Crack Propagation and Cyclic Tension Bending
,” Ph.D. Thesis,
University of South Wales
, Australia,
1968
.
This content is only available via PDF.
All rights reserved. This material may not be reproduced or copied, in whole or in part, in any printed, mechanical, electronic, film, or other distribution and storage media, without the written consent of ASTM International.
You do not currently have access to this content.