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Properties of five toughened matrix composite materialsThe use of toughened matrix composite materials offers an attractive solution to the problem of poor damage tolerance associated with advanced composite materials. In this study, the unidirectional laminate strengths and moduli, notched (open-hole) and unnotched tension and compression properties of quasi-isotropic laminates, and compression-after-impact strengths of five carbon fiber/toughened matrix composites, IM7/E7T1-2, IM7/X1845, G40-800X/5255-3, IM7/5255-3, and IM7/5260 have been evaluated. The compression-after-impact (CAI) strengths were determined primarily by impacting quasi-isotropic laminates with the NASA Langley air gun. A few CAI tests were also made with a drop-weight impactor. For a given impact energy, compression after impact strengths were determined to be dependent on impactor velocity. Properties and strengths for the five materials tested are compared with NASA data on other toughened matrix materials (IM7/8551-7, IM6/1808I, IM7/F655, and T800/F3900). This investigation found that all five materials were stronger and more impact damage tolerant than more brittle carbon/epoxy composite materials currently used in aircraft structures.
Document ID
19930003402
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Cano, Roberto J. (NASA Langley Research Center Hampton, VA, United States)
Dow, Marvin B. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
October 1, 1992
Subject Category
Composite Materials
Report/Patent Number
NASA-TP-3254
NAS 1.60:3254
L-17083
Accession Number
93N12590
Funding Number(s)
PROJECT: RTOP 505-63-50
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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