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Characteristics of laminates with delamination control stripsTough resin is needed to resist delamination crack propagation. However, modulus often has to be compromised because it is difficult to retain both high modulus and toughness in a matrix material. A potential solution is to use a hybrid system in which tough resin strips are included within a conventional matrix composite. By adjusting the spacing of the tough resin strips, maximum delamination size can be controlled. Experimental results for impact damage and subsequent damage propagation in laminates containing tough resin strips are reported. Plain adhesive strips and fiber-reinforced tough resin composite strips were used in constructing the hybrid laminates. Test results indicated that size of delamination inflicted by impact was confined between the tough resin strips. As a result, significantly increased residual compressive strength was obtained. Impacted laminates containing tough resin strips were also fatigue tested. It was found that these strips reduced the growth of the impact damage area relative to the growth seen in coupons with no tough resin strips. Damage growth from an open hole under tension fatigue was evaluated using both tough resin strips and glass fiber reinforced tough resin strips. Unreinforced tough resin strips retarded delamination growth from the open hole, but did not stop matrix cracks growing in the fiber direction. Fiber reinforced tough resin strips did not contain axial delamination growth from the open hole. However, they did act as crack arresters, stopping the through-the-thickness tension crack originating from the hole.
Document ID
19950022013
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Sun, C. T.
(Purdue Univ. West Lafayette, IN, United States)
Goering, J. C.
(McDonnell Aircraft Co. Saint Louis, MO., United States)
Alper, J. M.
(Naval Air Development Center Warminster, PA., United States)
Gause, L. W.
(Naval Air Development Center Warminster, PA., United States)
Date Acquired
September 6, 2013
Publication Date
September 1, 1992
Publication Information
Publication: FAA, Ninth DOD(NASA)FAA Conference on Fibrous Composites in Structural Design, Volume 1
Subject Category
Composite Materials
Accession Number
95N28434
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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