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A Quantitative Damage Tolerance Comparison of High Strength and High Modulus Carbon Fiber Sandwich StructureThis study presents experimental results of the compression after impact (CAI) testing of sandwich structure with face sheets made either with IM7/8552 high strength fiber or HM63/8552 high modulus fiber. While the HM63/8552 face sheet sandwich specimens would not be as damage tolerant as the IM7/8552 face sheet sandwich specimens, a quantitative measure of how much more damage tolerant the IM7/8552 face sheets were than the HM63/8552 face sheets was sought. Due to the IM7/8552 face sheets being 28% thicker than the HM63/8552 face sheets, the impact energies used needed to be adjusted for a fair comparison. The results show that the modulus is 35% lower for the IM7/8552 face sheet sandwich structure while the CAI strength
Document ID
20210026811
Acquisition Source
Marshall Space Flight Center
Document Type
Technical Memorandum (TM)
Authors
A T Nettles
(Marshall Space Flight Center Redstone Arsenal, Alabama, United States)
W E Guin
(Marshall Space Flight Center Redstone Arsenal, Alabama, United States)
C C Wolfe
(Marshall Space Flight Center Redstone Arsenal, Alabama, United States)
Date Acquired
January 12, 2022
Publication Date
January 19, 2022
Publication Information
Subject Category
Composite Materials
Report/Patent Number
M-1536
NASA/TM-20210026811
Funding Number(s)
WBS: 585777.08.50.50.40.14
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Technical Review
NASA Technical Management
Keywords
High modulus carbon fiber
high strength carbon fiber
sandwich structure
damage tolerance
compression after impact (CAI) strength
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