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An examination of impact damage in glass-phenolic and aluminum honeycomb core composite panelsAn examination of low velocity impact damage to glass-phenolic and aluminum core honeycomb sandwich panels with carbon-epoxy facesheets is presented. An instrumented drop weight impact test apparatus was utilized to inflict damage at energy ranges between 0.7 and 4.2 joules. Specimens were checked for extent of damage by cross sectional examination. The effect of core damage was assessed by subjecting impact-damaged beams to four-point bend tests. Skin-only specimens (facings not bonded to honeycomb) were also tested for comparison purposes. Results show that core buckling is the first damage mode, followed by delaminations in the facings, matrix cracking, and finally fiber breakage. The aluminum honeycomb panels exhibited a larger core damage zone and more facing delaminations than the glass-phenolic core, but could withstand more shear stress when damaged than the glass-phenolic core specimens.
Document ID
19900018560
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Nettles, A. T. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Lance, D. G. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Hodge, A. J. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
September 6, 2013
Publication Date
August 1, 1990
Subject Category
Composite Materials
Report/Patent Number
NAS 1.60:3042
NASA-TP-3042
Accession Number
90N27876
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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