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Delamination stresses in semicircular laminated composite barsUsing anisotropic elasticity theory, delamination stresses in a semicircular laminated composite curved bar subjected to end forces and end moments were calculated, and their radial locations determined. A family of design curves was presented, showing variation of the intensity of delamination stresses and their radial locations with different geometry and different degrees of anisotropy of the curved bar. The effect of anisotropy on the location of peak delamination stress was found to be small.
Document ID
19880010991
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Ko, William L. (NASA Hugh L. Dryden Flight Research Facility Edwards, CA, United States)
Date Acquired
September 5, 2013
Publication Date
January 1, 1988
Subject Category
Composite Materials
Report/Patent Number
NAS 1.15:4026
NASA-TM-4026
H-1417
Accession Number
88N20375
Funding Number(s)
PROJECT: RTOP 532-09-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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