J-Integral Decomposition Technical Brief
Abstract: The computation of the energy release rate has been used for many years to determine the onset of crack propagation. In recent years, the use of composite materials has become common practice in the aerospace industry and correlating the energy release rate with crack propagation, originally developed for isotropic materials in a 2D setting, is now been extended to structures made of laminated composites. For most cases of interest, the energy release rate has to be computed in a three dimensional setting for bi material crack interfaces and orthotropic material properties. Moreover, given the typical complexity of the displacement and stress fields associated with composite materials, the analysis requires the computation of the energy release rate components associated with each failure mode (i.e., Modes I, II and III).
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“At DST Group, we have effectively used StressCheck® over the last 10 years to determine accurate stress intensity factors. The results have been used to improve our residual strength and structural life estimates for aircraft in service with the Royal Australian Airforce, including C-130, P-3C and F/A-18 A/B. We have found it to be extremely easy to use and a very versatile code with which to create parametric models.
We have recently used StressCheck® to obtain improved stress intensity factor solutions (Improved stress intensity factors for selected configurations in cracked plates and Improved stress intensity factors for a single corner crack at a loaded fastener hole) for five key generic configurations. These transferable parametric results have been published externally. One specific example is the non-linear contact analysis of a cracked, filled fastener hole, with both fastener and remote plate loading.”
Dr. Manfred Heller, HeadStructural & Damage Mechanics, DST Group