Accelerated sonic fatigue testing methodology for reliability assessments of aircraft structure based on linear load intensification

DOI

10.2991/mmebc-16.2016.424How to use a DOI?

Keywords

Accelerated testing; Sonic fatigue; Random loading; Accelerating factor

Abstract

In term of sonic fatigue, initiation tests are commonly stopped at 108 cycles assuming that a fatigue limit exists, whereas feedback experience from in service aircraft has shown that structural elements can fail even after 1011 cycles. Thus, it is important to explore the gigacycle fatigue domain and an accelerated fatigue testing method which is presented in this paper. A method of accelerated durability testing for failure modes and life cycle based on the results of theory derivation and testing analysis are accomplished. And an acceptable estimation of acceleration factor calculation method based on the stress-lifetime approach (S-N curve) under narrow-band random acoustic condition is proved. The experimental results show that the application of the reduced time model can be a possible method for accelerated lifetime testing of time-dependent aircraft metal materials.

Copyright

© 2016, the Authors. Published by Atlantis Press.

Open Access

This is an open access article distributed under the CC BY-NC license (http://creativecommons.org/licenses/by-nc/4.0/).

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TY  - CONF
AU  - Chao Qu
AU  - Wenchao Huang
AU  - Dingwen Gao
PY  - 2016/06
DA  - 2016/06
TI  - Accelerated sonic fatigue testing methodology for reliability assessments of aircraft structure based on linear load intensification
BT  - Proceedings of the 2016 6th International Conference on Machinery, Materials, Environment, Biotechnology and Computer
PB  - Atlantis Press
SP  - 2119
EP  - 2125
SN  - 2352-5401
UR  - https://doi.org/10.2991/mmebc-16.2016.424
DO  - 10.2991/mmebc-16.2016.424
ID  - Qu2016/06
ER  -