Life Degeneration Rule on 2A12 Aluminium Alloy with Corrosion and Fatigue Experiment

Hai Wei Zhang; Yu Ting He; Li Ming Wu; Hua Ding; Qing Shao

doi:10.4028/www.scientific.net/AMM.80-81.27

Paper Titles

Investigation of Fatigue Behaviour and Notch Sensitivity of Ti-6Al-4V
p.7

Microcantilevers Fabrication Process of Silicon-Based (Pb, La)(Zr, Ti)O₃ Antiferroelectric Thick Films for Microactuator Applications
p.13

Grain Refinement of Fe-32%Ni Alloy by Multi-Axial Forging
p.18

Modeling of Phase Transformation Behaviors of Shape Memory Alloy Associated with Temperature Memory Effect
p.22

Life Degeneration Rule on 2A12 Aluminium Alloy with Corrosion and Fatigue Experiment
p.27

Analysis and Optimization on the Gating System of Aluminum Alloy Piston in Casting
p.32

Microscopic Phase-Field Simulation of the Process of Middle Heat Treatment of Ni-Cr-Al Alloy
p.36

Effect of Process Parameters on Microstructures of 7055 Aluminum Alloy in Creep Age Forming
p.40

Modeling on Laser Cladding on In718 Superalloy
p.46

HomeApplied Mechanics and MaterialsApplied Mechanics and Materials Vols. 80-81Life Degeneration Rule on 2A12 Aluminium Alloy...

Life Degeneration Rule on 2A12 Aluminium Alloy with Corrosion and Fatigue Experiment

Abstract:

2A12 specimens are selected in pre-corrosion fatigue test to get the ground corrosion effect coefficient, namely C(t) curve. Then, combining with Miner linear cumulative damage theory, theoretical fatigue life model is established based on the simulated corrosion-fatigue interactive process. Compared with actual corrosion-fatigue interactive test, theoretical life in short interactive periods is almost same, but actual life is higher in long interactive periods. Afterwards, a modified model based on C(t) curve at different interactive periods is established. The calculation shows that the modified results are in good agreement with the corrosion-fatigue interactive test.

You might also be interested in these eBooks

View Preview

Info:

Periodical:

Applied Mechanics and Materials (Volumes 80-81)

Pages:

27-31

DOI:

https://doi.org/10.4028/www.scientific.net/AMM.80-81.27

Citation:

Cite this paper

Online since:

July 2011

Authors:

Hai Wei Zhang, Yu Ting He, Li Ming Wu, Hua Ding, Qing Shao

Keywords:

2A12 Aluminium Alloy, Corrosion-Fatigue Life, Interactive Period, Modification of C(t) Curve

Export:

RIS, BibTeX

Price:

Permissions CCC:

Request Permissions

Permissions PLS:

Request Permissions

Сopyright:

Citation:

References

[1] Wally Hoppe, William Braisted, Jennifer Pierce etc, Corrosion fatigue assessment program-final report, University of Dayton Research Institute, (2008).

Google Scholar

[2] Liu Wenting, Li Yuhai. Aircraft Structure Calendar Life Evolution Technolog, first ed. Aeronautic Industry Press, Beijing, (2004).

Google Scholar

[3] Chen Yueliang, Naval aircraft structure corrosion control and strength evaluation, National Defense Industry Press, Beijing, (2009).

Google Scholar

[4] Zhang Youhong, Aircraft structure corrosion damage and effects on life, Ph D Northwestern Polytechnical University , Xi'an, (2007).

Google Scholar

[5] Zhang Haiwei, He Yuting, etc : submitted to Applied Mechanics and Materials (2011).

Google Scholar

[6] Fan Chaohua, He Yuting, Shu Wenjun, and Du Jinqiang. Determination of Life Envelope of LY12CZ Aluminum Alloy, J. Structure and Intensity Research. Supplement ( 2008) 466-469.

Google Scholar