Abstract
An existing compression after impact (CAI) model was used as the fitness function in an optimization routine to produce a damage tolerance optimized composite layup. This laminate was tested in a CAI strength experiment, alongside a baseline quasi-isotropic layup. Although a 13% improvement in CAI strength was observed, the analytical model was shown to overpredict the strength of the damage tolerance optimized laminate. It was found that the optimization process eliminated localized failure due to Mode-I buckling-induced propagation, and that the impacted laminate failed instead through globally driven, in-plane effects.
| Original language | English |
|---|---|
| Title of host publication | 51st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference |
| Place of Publication | Reston, VA. |
| Publisher | American Institute of Aeronautics and Astronautics |
| Publication status | Published - 2010 |
Bibliographical note
Paper no. 2010-2868 51st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. 12-15 April 2010. Orlando, FL, United States.Fingerprint
Dive into the research topics of 'Compression after impact modeling of damage tolerant composite laminates'. Together they form a unique fingerprint.Cite this
- APA
- Standard
- Harvard
- Vancouver
- Author
- BIBTEX
- RIS