Accession Number : ADA303211
Title : Behavior of Damaged Graphite/Epoxy Laminates Under Compression Loading.
Descriptive Note : Final rept.,
Corporate Author : BOEING COMMERCIAL AIRPLANE CO SEATTLE WA
Personal Author(s) : Byers, B. A.
PDF Url : ADA303211
Report Date : AUG 1980
Pagination or Media Count : 64
Abstract : An experimental program was conducted to evaluate the influence of three different resin systems on the damage tolerance of graphite/polymer laminates. Testing consisted of both static compression and cyclic compression evaluation of 10.2 by 15.2- by 0.5-cm (4- by 6- by 0.2-in) laminates with circular holes, simulated delaminations, and low-velocity impact. Damage growth under steadily increasing compression and cyclic compression loading was monitored. Damage size and impact-induced failures for the three materials were compared. Of the three material systems evaluated, the one most tolerant to impact damage exhibited the least delamination within the cross section due to impact, the highest transverse tension strain to failure, and the largest crack opening force, as determined from double-cantilever-beam tests. jg p3
Descriptors : *COMPRESSION, *LOADS(FORCES), *CRACKS, *GRAPHITE, *EPOXY LAMINATES, *PLASTICS, TEST AND EVALUATION, SIMULATION, IMPACT, DAMAGE, SIZES(DIMENSIONS), POLYMERS, GROWTH(GENERAL), CYCLES, LOW VELOCITY, HOLES(OPENINGS), CROSS SECTIONS, TOLERANCE, STATICS, DELAMINATION, CIRCULAR.
Subject Categories : Laminates and Composite Materials
Distribution Statement : APPROVED FOR PUBLIC RELEASE