Numerical Studies of End Effect on Crack Propagation Behavior of Brittle Specimen Containing Pre-Existing Crack under Uniaxial Compression

摘要:

文章预览

In this paper, a Material Failure Process Analysis code (MFPA2D) was employed to investigate the interaction of end effect zone of specimen with the wing crack propagation inside the brittle specimen containing pre-existing flaws under uniaxial compression comparing with the experimental results. The numerical results show that the shorter the distance between the pre-existing flaw and the specimen's end , the slower the crack propagation process and the shorter wing propagation length is , and vice versa. In addition, the end effect zone was also influenced by the wing crack propagation.

信息:

期刊:

编辑:

Yu Zhou, Shan-Tung Tu and Xishan Xie

页数:

1049-1052

引用:

M. L. Huang et al., "Numerical Studies of End Effect on Crack Propagation Behavior of Brittle Specimen Containing Pre-Existing Crack under Uniaxial Compression", Key Engineering Materials, Vols. 353-358, pp. 1049-1052, 2007

上线时间:

September 2007

输出:

价格:

$38.00

[1] C. A. Tang, S.Q. Kou: Eng. Fract. Mech. Vol. 61 (1998), p.311.

[2] R. H. C. Wong, K.T. Chau and C.A. Tang: Int. J. Rock Mech. & Min. Sci. Vol. 38 (2001), p.909.

[3] C. A. Tang, H. Liu and P. K. K. Lee: Int. J. Rock Mech. & Min. Sci. Vol. 37 (2000), p.555.

[4] C. A. Tang, L.G. Tham, P. K. K. Lee and H. Liu: Int. J. Rock Mech. & Min. Sci. Vol. 37 (2000), p.571.

[5] C. A. Tang: Int. J. Rock Mech. & Min. Sci. Vol. 34 (1997), p.249 Fig. 5 Experimental and numerical results for the propagation of the unsymmetrical pre-existing crack.

00.

20.

40.

60.

80.

[1] 00.

[1] 20.

[1] 40.

[1] 60.

[1] 80.

[2] 00.

[2] 20.

[2] 40.

[2] 60 0. 00 0. 10 0. 20 0. 30 0. 40 0. 50 0. 60 0. 70 0. 80 Cur r ent st r ess/ Peak st r ess L/ a The pr opagat i on l engt h f r om poi nt A ( Exper ment al r esul t s) The pr opagat i on l engt h f r om poi nt B ( Exper ment al r esul t s) The pr opagat i on l engt h f r om poi nt A ( Numer i cal r esul t s) The pr opagat i on l engt h f r om Fig6. Numerical results for end effect zone and wing propagation versus the ratio of current stress to peak stress.

00.

10.

20.

30.

40.

50.

60.

70 0 0. 1 0. 2 0. 3 0. 4 0. 5 0. 6 0. 7 0. 8 0. 9 1 1. 1 Cur r ent st r ess/ Peak st r ess h/ b 0.

2.

4.

6.

8 1.

[1] 2.

[1] 4.

[1] 6 L/ a Symmet r i cal pr e- exi st i ng cr ack No pr e- exi st i ng cr ack L/ a.