SYMPOSIA PAPER Published: 01 January 1990

Impact Damage and Residual Strength Analysis of Composite Panels with Bonded Stiffeners


Blade-stiffened, compression-loaded cover panels were designed, manufactured, analyzed, and tested. All panels were fabricated from IM6/1808I interleafed graphite-epoxy. An orthotropic blade stiffener and an orthotropic skin were selected to satisfy the design requirements for an advanced aircraft configuration. All specimens were impact damaged prior to testing. Experimental results were obtained for three- and five-stiffener panels. Analytical results described interlaminar forces caused by impact and predicted specimen residual strength. The analytical results compared reasonably with the experimental results for residual strength of the specimens.

Author Information

Madan, RC
Douglas Aircraft Co., McDonnell Douglas Corp., Long Beach, CA
Shuart, MJ
NASA Langley Research Center, Hampton, VA
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Developed by Committee: D30
Pages: 64–85
DOI: 10.1520/STP24108S
ISBN-EB: 978-0-8031-5120-8
ISBN-13: 978-0-8031-1287-2