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Comparison of Open-Hole Compression Strength and Compression After Impact Strength on Carbon Fiber/Epoxy Laminates for the Ares I Composite InterstageNotched (open hole) composite laminates were tested in compression. The effect on strength of various sizes of through holes was examined. Results were compared to the average stress criterion model. Additionally, laminated sandwich structures were damaged from low-velocity impact with various impact energy levels and different impactor geometries. The compression strength relative to damage size was compared to the notched compression result strength. Open-hole compression strength was found to provide a reasonable bound on compression after impact.
Document ID
20110008641
Acquisition Source
Marshall Space Flight Center
Document Type
Technical Publication (TP)
Authors
Hodge, Andrew J. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Nettles, Alan T. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Jackson, Justin R. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
August 25, 2013
Publication Date
March 1, 2011
Subject Category
Composite Materials
Report/Patent Number
M-1309
NASA/TP-2011-216460
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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