Material Scatter in Crack Growth Rates of 7075-T7351 under Spectrum Loading

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Abstract:

The probabilistic distribution of crack lengths at a critical location is a key input for risk assessment of structural failure of airframes due to fracture. This distribution depends on the initial surface condition of the structural component, the crack growth behaviour of the material, and the applied load history. MIL-STD-1530C suggests the use of a single master crack growth curve to derive the subsequent crack length distributions from the initial crack length distribution, without taking into consideration the well-recognized scatter in crack growth rates due to uncertainties in material properties. In this paper, we report the results of a study that aims to quantify the scatter in crack growth rates of 7075-T7351 aluminium alloy subjected to spectrum loading, and to assess its effect on risk assessment. About 80 middle-tension specimens were planned to be tested under nominally identical conditions, with the crack lengths recorded using crack cameras and direct current differential potential method. Based on the test data and the analyses, crack length distributions are developed for different times. These are then compared to the distributions derived from the master curve approach. This investigation attempts to quantitatively demonstrate the reasonableness, or otherwise, of using a single crack growth curve to derive the distributions of crack lengths for risk analyses, and the conditions under which the observations apply. The results reported here and those from other researchers show that this scatter in crack growth rates cause by variation in material properties cannot be appropriately addressed by the master crack growth curve approach for the purpose of risk analysis.

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Advanced Materials Research (Volumes 891-892)

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1197-1202

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March 2014

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© 2014 Trans Tech Publications Ltd. All Rights Reserved

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[1] Torregosa, R.F. and W. Hu (2013). Probabilistic risk analysis of fracture of aircraft structures using a Bayesian approach to update the distribution of the equivalent initial flaw sizes, Fatigue & Fracture of Engineering Materials & Structures.

DOI: 10.1111/ffe.12103

Google Scholar

[2] Torregosa, R. and W. Hu (2011). C-130H Centre Wing Lower Surface Panel Number 3 Probabilistic Risk Analysis,. DSTO-RR-0371, Defence Science and Technology Organisation.

Google Scholar

[3] US Department of Defence (2005). MIL-STD-1530C, Aircraft Structural Integirty Program (ASIP).

Google Scholar

[4] Virkler, D.A., B.M. Hillberry, and P.K. Geoel (1979). The statistical nature of fatigue crack propagation, Journal of Engineering Materials and Technology. 101(2): pp.148-153.

DOI: 10.1115/1.3443666

Google Scholar

[5] Hu, W. and R. Torregosa (2011). Integrated Probabilistic Analysis of Damage Tolerance and Risk for Airframe Structural Locations,. 26th Symposium of the International Committee on Aeronautical Fatigue. 2011. Montreal, Canada: Springer. pp.615-624.

DOI: 10.1007/978-94-007-1664-3_49

Google Scholar

[6] Ghonem, H. and S. Dore (1987). Experimental study of the constant-probability crack growth curves under constant amplitude loading, Engineering Fracture Mechanics. 27(1): pp.1-125.

DOI: 10.1016/0013-7944(87)90002-6

Google Scholar

[7] Wu, W.F. and C.C. Ni (2007). Statistical aspects of some fatigue crack growth data, Engineering Fracture Mechanics. 74: pp.2952-2963.

DOI: 10.1016/j.engfracmech.2006.08.019

Google Scholar