铝合金结构腐蚀疲劳裂纹扩展与剩余强度研究

ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2007, Vol. 28 ›› Issue (2): 332-335.

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Investigation on Corrosion Fatigue Crack Growth and Residual Strength of Aluminum Alloy Structure

ZHANG You-hong¹, LU Guo-zhi¹, LI;Zhong^1,2, CHEN Yue-liang³, REN Ke-liang¹

1 School of Aeronautics,Northwest Polytechnical University 2 Aircraft Strength Research Institute of China 3 Qingdao Branch, Naval Aeronautical Engineering Academy

Received:2005-11-18 Revised:2006-06-12 Online:2007-03-10 Published:2007-03-10
Contact: ZHANG Youhong¹

Abstract

Abstract:

The fatigue crack propagation behavior of LY12 CZ aluminum alloy fastener involving center hole in 3.5%NaCl solution is investigated.The corrosion fatigue crack growth curves of the specimens at three different frequencies are presented.Experimental research shows that the corrosion fatigue crack growth rate decreases with the increasing of the loading frequencies,and in corrosive environment,the crack growth rate is larger than the rate in air.

Key words: aluminum , alloy, , corrosion , fatigue, , residual , strength, , crack , growth, , loading , frequency

CLC Number:

ZHANG You-hong;LU Guo-zhi;LI Zhong;CHEN Yue-liang;REN Ke-liang. Investigation on Corrosion Fatigue Crack Growth and Residual Strength of Aluminum Alloy Structure[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2007, 28(2): 332-335.

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Investigation on Corrosion Fatigue Crack Growth and Residual Strength of Aluminum Alloy Structure

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