Post-buckling fatigue behavior of advanced composite shear panels
✍ Scribed by N.M Bhatia
- Publisher
- Elsevier Science
- Year
- 1976
- Tongue
- English
- Weight
- 132 KB
- Volume
- 8
- Category
- Article
- ISSN
- 0013-7944
No coin nor oath required. For personal study only.
✦ Synopsis
Abstracts through-the-thickness tlaws the "average stress criterion" has been shown to be effective in predicting failure [l], this criterion does not take into account the progressive failure process that is known to occur in composites. It is expected, therefore, that there are cases such as general biaxial loading of a flaw where the direction of 5aw growth is not known a priori that will resist prediction by this method. To overcome this decay, as well as to lend insight into the failure process, a new method is currently being studii which is capable of modeling and tracing the damage accumulation in notched or unnotched composite specimens that ultimately leads to failure. The idea is, quite simple, to model the actual constitutive behavior of the laminate both before and after damage has occurred. This allows the ultimate failure of notched laminates to be predicted under general in-plane loading based only on a knowledge of the individual ply behavior.
The development of the incremental finite element program necessary to perform the calculations has been finished and, to date, two examples have been run. These involve failure predictions for two diierent ~~~/e~xy laminates condom holes and subje&ed to uniaxial tensile loads. The strength p~dictions made by computer agreed very well with the test results. Currently, more examples are being mn and refinements are being made to the program itself.