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Analytical evaluation of the Stress Intensity Factor in stiffened sheets with multiple side damage

  • Received: 04 September 2016 Accepted: 09 November 2016 Published: 22 November 2016
  • A closed form solution of the Stress Intensity Factor (SIF) for stiffened flat sheets, typically used in aircraft construction, in Multiple Site Damage (MSD) conditions, has been developed. The well-known theory of complex variable functions has been used, through the application of functions specifically developed for the case of cracks equally spaced and of equal length. Moreover, the superposition principle has been applied to evaluate the compression loads transmitted by the stringers through the rivets, by imposing the equilibrium on the crack free surfaces and the compatibility of displacements between sheet and stringers at the rivets location. The results have been compared with solutions available in the literature, obtained by combination of various analytical techniques and experimental methodologies, showing a good agreement. The proposed method is a reference for the validation of other numerical or analytical methods and effectively can replace the Finite Element Method for simple geometries.

    Citation: Enrico Troiani. Analytical evaluation of the Stress Intensity Factor in stiffened sheets with multiple side damage[J]. AIMS Materials Science, 2016, 3(4): 1615-1622. doi: 10.3934/matersci.2016.4.1615

    Related Papers:

  • A closed form solution of the Stress Intensity Factor (SIF) for stiffened flat sheets, typically used in aircraft construction, in Multiple Site Damage (MSD) conditions, has been developed. The well-known theory of complex variable functions has been used, through the application of functions specifically developed for the case of cracks equally spaced and of equal length. Moreover, the superposition principle has been applied to evaluate the compression loads transmitted by the stringers through the rivets, by imposing the equilibrium on the crack free surfaces and the compatibility of displacements between sheet and stringers at the rivets location. The results have been compared with solutions available in the literature, obtained by combination of various analytical techniques and experimental methodologies, showing a good agreement. The proposed method is a reference for the validation of other numerical or analytical methods and effectively can replace the Finite Element Method for simple geometries.


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    [1] Goranson U (2007) Damage tolerance facts and fiction. International conference on damage tolerance of aircraft structures, Delft University of Technology, Delft, the Netherlands.
    [2] Nesterenko B, Nesterenko G (2011) Analysis of requirements on fatigue and damage tolerance for civil transport airplanes. In: Komorowski J editor, Proceedings of the 26th Symposium of the international committee on aeronautical fatigue 39–59.
    [3] Bellinger NC, Komorowski JP (1997) Corrosion pillowing stresses in fuselage lap joints. AIAA J 35: 317–320.
    [4] Federal Aviation Administration (2011) Damage Tolerance and Fatigue Evaluation of Structure. Advisory Circular AC 25.571-1D.
    [5] Wang W, Rans C, Alderliesten RC, et al. (2015) Predicting the influence of discretely notched layers on fatigue crack growth in fiber metal laminates. Eng Fract Mech 145: 1–14. doi: 10.1016/j.engfracmech.2015.06.062
    [6] Wang L, Chow WT, Kawai H, et al. (1996) Prediction of widespread fatigue damage threshold. Proceeding of the FAA/NASA Symposium on Continued Airworthiness of Aircraft Structures, Atlanta (GA), USA.
    [7] Gruber ML, Wilkins KE, Worden RE (1996) Investigations of fuselage structure subject to widespread fatigue damage. In: Bigelow C editor. Proceedings from the FAA/NASA Symposium on the Continued Airworthiness of Aircraft Structures 439–460.
    [8] Galatolo R, Nilsson KF (2001) An experimental and numerical analysis of residual strength of butt-joints panels with multiple site damage. Eng Fract Mech 68: 1437–1461. doi: 10.1016/S0013-7944(01)00027-3
    [9] Schijve J (1994) Some calculation on the stress distribution in an infinite sheet with a single crack and with periodic collinear cracks. Report LR-770, TUDelft, the Netherlands.
    [10] Molinari G, Meneghin I, Melega M, et al. (2012) Parametric damage tolerance design of metallic aeronautical stiffened panels. Aeronaut J 1182: 815–831.
    [11] Bloom JM, Sanders JL (1966) The effect of a riveted stringer on the stress of a cracked sheet. ASME J Appl Mech 33: 561–570. doi: 10.1115/1.3625122
    [12] Tada H (1970) Westergaard stress functions for several periodic crack problems. Eng Fract Mech 2: 177–180. doi: 10.1016/0013-7944(70)90023-8
    [13] Poe CC (1971) Stress intensity factor for a cracked sheet with riveted and uniformly spaced stringers. NASA TR R-358, Langley Research Center, Hampton (VA), USA.
    [14] Westergaard HM (1939) Bearing pressures and cracks. J Appl Mech 6: 49–53.
    [15] Eftis J, Leibowitz H (1972) On the modified Westergaard equation for certain plane crack problems. Int J Fracture 8: 383–392.
    [16] Carthwrigth DJ, Rooke DP (1976) Compendium of Stress Intensity Factors, HMSO, London, UK.
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  • © 2016 the Author(s), licensee AIMS Press. This is an open access article distributed under the terms of the Creative Commons Attribution License (http://creativecommons.org/licenses/by/4.0)
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