Effect of Mode Loading on FCRG Plate with Double Through Crack at Hole
The knowledge of the nature of loading is very
important in order to hold account on the total behavior such as
vibration, shock, fatigue, etc. Fatigue present 90% of failure when
loadings fatigues are very complex. In this paper a study of double
through crack at hole for plate subjected to fatigue loading is
presented. Various modes loading are studied where the applied load
is the same one. The fatigue life is given where the effect of stress
ratio is highlighted. This work is conducted on aluminum alloy 2024
T351 used for much aerospace and aeronautics applications. The
fatigue crack growth behavior with constant amplitude is studied
using the AFGROW code when Forman model is applied. The
fatigue crack growth rate and fatigue life for different loading modes
are compared with variation of others geometrical parameter such as
thickness and dimensions of notch hole.
[1] A.L. Kermanidis, S.P. Pantelakis. Fat. Fract. Engng. Mater. Struct, Vol.
24, pp 699-710, 2001.
[2] D.L. McDiarmid. Aeronautical Journal, p 325-29, 1974.
[3] N. Hong, Q. Xin, F. Weixiun. Fat. Fract. Engng. Mater. Struct Vol.
15(2), pp 225-27, 1992.
[4] W.A. Moussa, R. Bell, C.L. Tan. Int. J. of Pres. Vessels and Piping,
Vol. 76, pp 135-145, 1999.
[5] Qu Jie and Wang Xin. Int. J. of Pressure Vessels and Piping, Vol. 83,
pp 593-606, 2006.
[6] R. Cao, Y.Z. Lin, D. Hu, J.H. Chen. Engn Fract. Mech, Vol. 75, pp
4343-4362, 2008.
[7] W. Elber. Engn. Fract. Mech, Vol. 2(1), pp 37-44, 1970.
[8] L. Ferry, D. Perreux, D. Varchona, N. Sicot. Comp. Scie. and Techn.
Vol. 59, pp 575-582, 1999.
[9] K. Shiozawa, T. Hasegawa, Y. Kashiwagi, L. Lu. Int. J. of Fatigue, Vol.
31, pp 880-888, 2009.
[10] Wang G Y, Qiao DC, Yokoyama Y, Freels M, Inoue A, Liaw PK.
Journal of Alloys and Compounds, Vol. 483, pp 143-145, 2009.
[11] R.G. Forman V.E. Hearney, R.M. Engle. J. of Basic Engng, Trans of
ASME, Vol. 89, 1967.
[12] J.A. Harter. "AFGROW Users guide and technical manual: AFGROW
for Windows 2K/XP, Version 4.0011.14". Air Force Research
Laboratory, 2006.
[13] M. Benachour, M. Benguediab, A. Hadjoui, F. Hadjoui, N. Benachour.
Computational Materials Science, Vol. 44, pp 489-495, 2008.
[1] A.L. Kermanidis, S.P. Pantelakis. Fat. Fract. Engng. Mater. Struct, Vol.
24, pp 699-710, 2001.
[2] D.L. McDiarmid. Aeronautical Journal, p 325-29, 1974.
[3] N. Hong, Q. Xin, F. Weixiun. Fat. Fract. Engng. Mater. Struct Vol.
15(2), pp 225-27, 1992.
[4] W.A. Moussa, R. Bell, C.L. Tan. Int. J. of Pres. Vessels and Piping,
Vol. 76, pp 135-145, 1999.
[5] Qu Jie and Wang Xin. Int. J. of Pressure Vessels and Piping, Vol. 83,
pp 593-606, 2006.
[6] R. Cao, Y.Z. Lin, D. Hu, J.H. Chen. Engn Fract. Mech, Vol. 75, pp
4343-4362, 2008.
[7] W. Elber. Engn. Fract. Mech, Vol. 2(1), pp 37-44, 1970.
[8] L. Ferry, D. Perreux, D. Varchona, N. Sicot. Comp. Scie. and Techn.
Vol. 59, pp 575-582, 1999.
[9] K. Shiozawa, T. Hasegawa, Y. Kashiwagi, L. Lu. Int. J. of Fatigue, Vol.
31, pp 880-888, 2009.
[10] Wang G Y, Qiao DC, Yokoyama Y, Freels M, Inoue A, Liaw PK.
Journal of Alloys and Compounds, Vol. 483, pp 143-145, 2009.
[11] R.G. Forman V.E. Hearney, R.M. Engle. J. of Basic Engng, Trans of
ASME, Vol. 89, 1967.
[12] J.A. Harter. "AFGROW Users guide and technical manual: AFGROW
for Windows 2K/XP, Version 4.0011.14". Air Force Research
Laboratory, 2006.
[13] M. Benachour, M. Benguediab, A. Hadjoui, F. Hadjoui, N. Benachour.
Computational Materials Science, Vol. 44, pp 489-495, 2008.
@article{"International Journal of Mechanical, Industrial and Aerospace Sciences:53584", author = "M. Benachour and N. Benachour and M. Benguediab and A. Hadjoui", title = "Effect of Mode Loading on FCRG Plate with Double Through Crack at Hole", abstract = "The knowledge of the nature of loading is very
important in order to hold account on the total behavior such as
vibration, shock, fatigue, etc. Fatigue present 90% of failure when
loadings fatigues are very complex. In this paper a study of double
through crack at hole for plate subjected to fatigue loading is
presented. Various modes loading are studied where the applied load
is the same one. The fatigue life is given where the effect of stress
ratio is highlighted. This work is conducted on aluminum alloy 2024
T351 used for much aerospace and aeronautics applications. The
fatigue crack growth behavior with constant amplitude is studied
using the AFGROW code when Forman model is applied. The
fatigue crack growth rate and fatigue life for different loading modes
are compared with variation of others geometrical parameter such as
thickness and dimensions of notch hole.", keywords = "Fatigue crack, mode loading, aluminum alloy", volume = "4", number = "10", pages = "962-4", }