Experimental Determination of Aircraft Structural Material Life Envelope

Hai Wei Zhang; Yu Ting He; Li Ming Wu; Qing Shao; Jin Qiang Du

doi:10.4028/www.scientific.net/AMR.299-300.1198

Paper Titles

Monitoring System Design of Fuse Automatic Assembly Machine Based on WinCC
p.1182

Vehicle Engineering Application Study on TSF Var Compensation Method for Electric Locomotive of Electrified Railway
p.1186

Study on the Speed Control of Diesel Engine Based on Neural Sliding Mode Control
p.1190

Design of Measurement and Control System for the Rail Fastening Spring Clip Type A and B
p.1194

Experimental Determination of Aircraft Structural Material Life Envelope
p.1198

Study on Expression of SIF for Tapered Lug Subjected to Oblique Pin-Load
p.1203

Study on Locally Resonant Phononic Crystals Based on Automotive Noise Control
p.1208

Simulation Analysis and Research of Tire Wear
p.1212

Research and Application of Genetic Algorithm in Material Handling Route for Assembly Line of Airbag
p.1217

HomeAdvanced Materials ResearchAdvanced Materials Research Vols. 299-300Experimental Determination of Aircraft Structural...

Experimental Determination of Aircraft Structural Material Life Envelope

Abstract:

A new approach to reflect the relation of aircraft structural calendar life and fatigue life is established by pre-corrosion and fatigue test with 2A12 alloy specimens. The corrosion factor curve is fitted from the test, and then aircraft structural corrosion and fatigue interactive process during actual in-service environment is simulated. Furthermore, combining with Miner linear cumulative damage theory and the method of ‘calendar life tending to minimum’, life envelope is found. The result shows that flight strength is the key factor for aircraft structural life, and the envelope can be used to realize single aircraft structural life surveillance.

You might also be interested in these eBooks

View Preview

Info:

Periodical:

Advanced Materials Research (Volumes 299-300)

Pages:

1198-1202

DOI:

https://doi.org/10.4028/www.scientific.net/AMR.299-300.1198

Citation:

Cite this paper

Online since:

July 2011

Authors:

Hai Wei Zhang, Yu Ting He, Li Ming Wu, Qing Shao, Jin Qiang Du

Keywords:

2A12 Alloy, Aircraft Structural Material Life Envelope, Calendar Life, Fatigue Life

Export:

RIS, BibTeX

Price:

Permissions CCC:

Request Permissions

Permissions PLS:

Request Permissions

Сopyright:

Citation:

References

[1] JSSG-2009 Joint Service Specification Guide-Aircraft Structure. Department of Defense (2009).

Google Scholar

[2] MIL-STD-1530C, aircraft structure integrity program, US Air Force (2005).

Google Scholar

[3] Brooks CL, Prost-Domasky S, Honeycutt K: Corrosion is a structure and economic problem: transforming metrics to a life prediction method (Nato Research and Technology Organization Meeting Proceedings 18, Greece 1998).

Google Scholar

[4] Goswami TK, Hoeppner DW: Pitting corrosion fatigue of structural materials (Structural integrity in aging aircraft, New York 1995).

Google Scholar

[5] Ali Merati: International Journal of Fatigue Vol. 27 (2005), p.33.

Google Scholar

[6] Amilcar Quispitupa, Basir Shafiq, O Marcelo Suarez et al: Journal of Aircraft Vol. 43 (2006), p.787.

Google Scholar

[7] Chen Yueliang, in: Naval aircraft structure corrosion control and strength evaluation (National Defense Industry Press, China 2009).

Google Scholar

[8] Liu Wenting, Li Yuhai, in: Aircraft Structure Calendar Life Evolution Technology (Aeronautic Industry Press, China 2004).

Google Scholar

[9] He Yuting : Journal of Air Force Engineering University Vol. 6 (2005), p.4.

Google Scholar

[10] He Yuting, Fan Chaohua.: Journal of Air Force Engineering University Vol. 6 (2006), p.1.

Google Scholar

[11] He Yuting.: Engineering Science Vol. 6 (2006), p.23.

Google Scholar