Progressive Damage and Failure Prediction of Open Hole Tension and Open Hole Compression Specimens
Author:
Affiliation:
1. University of Michigan, Ann Arbor
2. Ulsan National Institute of Science and Technology
3. NASA Glenn Research Center
4. The Boeing Company
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.2015-0466
Reference12 articles.
1. A Unified Model for Predicting the Open Hole Tensile and Compressive Strengths of Composite Laminates for Aerospace Applications
2. Numerical implementation of a multiple-ISV thermodynamically-based work potential theory for modeling progressive damage and failure in fiber-reinforced laminates
3. On the relation between the mode I fracture toughness of a composite laminate and that of a 0° ply: Analytical model and experimental validation
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