混合型裂纹的疲劳扩展

本文对受单向拉伸疲劳载荷的中心斜裂纹L₃铝试板进行了研究。根据Erdogan和Sih的最大拉应力理论,推导出以△K作为参变量,以裂纹角β₀进行修正的Paris形式的扩展速率表达式。并且进一步论证以更简单的用裂纹长度在x轴上投影的Paris方程来表示。初始裂纹角β₀有20°、30°、45°、60°、80°、90°等各种角度,裂纹尖端有经预制疲劳裂纹尖端与未经预制疲劳裂纹尖端两种情况,比较了这两种情况下疲劳扩展轨迹及疲劳扩展速率。     

FATIGUE CRACK PROPAGAION UNDER MIXED MODE LOADING

Mixed model fatigue crack propagation is analyzed in this paper, using a centre cracked plate geometry, loaded under uniaxial cyclic tension. Based on maximum principal stress criterion, a modified Paris expression of fatigue crack growth rate is derived in terms of ΔΚ and crack angle β_0 for an inclined crack. It is also shown that it is more convenient to express the Paris equation by means of crack length projected on the x- axis, a_x rather than the actual length, a itself. The crack trajectory due to cyclic loading is predicted. β_0 is varied from 29°to 90°. Experimental data on Type L3 aluminium agree fairly well with predicted values when β_0 exceeds 30°.     

Fatigue crack propagaion under mixed mode loading

Mixed model fatigue crack propagation is analyzed in this paper, using a centre cracked plate geometry, loaded under un-iaxial cyclic tension. Based on maximum principal stress criterion, a modified Paris expression of fatigue crack growth rate is derived in terms of ΔK and crack angle β_α for an inclined crack. It is also shown that it is more convenient to express the Paris equation by means of crack length projected on the x -axis, α_x rather than the actual length, α itself. The crack trajectory due to cyclic loading is predicted, β is varied from 29° to 90°. Experimental data on Type L3 aluminium agree fairly well with predicted values when β_α exceeds 30°.