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Compression after impact modeling of damage tolerant composite laminates


Reference:

Baker, N. and Butler, R., 2010. Compression after impact modeling of damage tolerant composite laminates. In: 51st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. Reston, VA.: American Institute of Aeronautics and Astronautics.

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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.

Details

Item Type Book Sections
CreatorsBaker, N.and Butler, R.
DepartmentsFaculty of Engineering & Design > Mechanical Engineering
Research CentresAerospace Engineering Research Centre
StatusPublished
ID Code27652
Additional InformationPaper no. 2010-2868 51st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. 12-15 April 2010. Orlando, FL, United States.

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