Journal
JOURNAL OF COMPOSITE MATERIALS
Volume 51, Issue 15, Pages 2119-2129Publisher
SAGE PUBLICATIONS LTD
DOI: 10.1177/0021998316669579
Keywords
Composite; fatigue; progressive damage; Helius; strength prediction
Categories
Funding
- Lockheed Martin [FA8650-08-D-3858 DO 0037]
Ask authors/readers for more resources
Finite element simulations of three laminates in open-hole configuration subjected to constant amplitude tension-tension fatigue loading are investigated as part of the Damage Tolerant Design Principles program organized by the Air Force Research Laboratory. All coupons were made from unidirectional IM7/977-3 plies, which are composed of intermediate modulus carbon fibers and a toughened epoxy matrix. Government furnished experimental data from an assortment of fatigue loaded unnotched coupons were used to characterize the behavior of the composite material in the simulations. The commercial software Autodesk Helius PFA was used to model the non-linear response of the material. Blind simulations of coupon stiffness and damage at several cycle numbers and residual coupon tensile and compressive strengths are benchmarked against experimental measurements and X-rays. Upon review of the experimental results, a second round of simulations was performed where the modeling strategy was updated to improve correlation to experiment.
Authors
I am an author on this paper
Click your name to claim this paper and add it to your profile.
Reviews
Recommended
No Data Available