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Impact damage and residual strength analysis of composite panels with bonded stiffenersBlade-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.
Document ID
19900053075
Document Type
Conference Paper
Authors
Madan, Ram C. (Douglas Aircraft Co. Long Beach, CA, United States)
Shuart, Mark J. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1990
Subject Category
AIRCRAFT DESIGN, TESTING AND PERFORMANCE
Meeting Information
Symposium on Composite Materials: Testing and Design(Sparks, NV)
Funding Number(s)
CONTRACT_GRANT: NAS1-17970
Distribution Limits
Public
Copyright
Other