Abstract
An experimental and numerical investigation was conducted to study the skin–stiffener separation of single T-shape stiffener specimens in postbuckling condition. Three specimens were manufactured with a centrally located Teflon insert, and were loaded in compression until collapse. Deformation patterns and separation evolution were monitored during the tests. To measure the full-field displacements and the strain distributions of the specimens, a digital image correlation (DIC) system was used. Skin–stiffener separation was observed and measured with an ultrasound system. Finite-element (FE) analyses were conducted to capture interlaminar damage mechanism based on the virtual crack closure technique. The numerical analysis accurately predicted the postbuckling deformation and the skin–stiffener separation behavior. The close correlation between the experimental and numerical results allows for further exploitation of the strength reserve in the postbuckling region and wider design options for the next generation of composite aircraft designs.
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Information & Authors
Information
Published In
Journal of Aerospace Engineering
Volume 31 • Issue 4 • July 2018
Copyright
©2018 American Society of Civil Engineers.
History
Received: Mar 24, 2017
Accepted: Nov 17, 2017
Published online: Mar 29, 2018
Published in print: Jul 1, 2018
Discussion open until: Aug 29, 2018
ASCE Technical Topics:
- Analysis (by type)
- Buckling
- Composite materials
- Compression
- Continuum mechanics
- Deformation (mechanics)
- Dynamics (solid mechanics)
- Engineering fundamentals
- Engineering materials (by type)
- Engineering mechanics
- Finite element method
- Materials engineering
- Methodology (by type)
- Numerical analysis
- Numerical methods
- Post buckling
- Solid mechanics
- Stiffening
- Structural behavior
- Structural dynamics
- Structural engineering
- Structural mechanics
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