Accession Number : ADA306900
Title : Test and Analysis of Graphite-Fiber, Epoxy-Resin Composite Airframe Structural Elements.
Corporate Author : BELL AEROSPACE CO BUFFALO NY
Personal Author(s) : Sayers, K. H. ; Haney, D. P.
PDF Url : ADA306900
Report Date : OCT 1968
Pagination or Media Count : 10
Abstract : A series of graphite fiber Composite stiffened panels was tested in compression and shear to select the best design for a representative fuselage component. A curved Composite stiffened panel and two aluminum panels were also tested in compression. Conventional laboratory equipment and testing techniques were employed. Analytical predictions of behavior were obtained using recently developed methods. Initial buckling data, overall panel stiffnesses, ultimate strengths and failure modes were obtained. These data correlated well with theoretical predictions. An applicable post-buckling analysis for composite stiffened panels is required. A material strength problem was exposed which was subsequently solved, in part, through the use of treated fiber. Substantial strength-weight and high stiffness. weight performances were demonstrated in comparison with conventional materials.
Descriptors : *AIRFRAMES, *EPOXY RESINS, *GRAPHITE EPOXY COMPOSITES, COMPRESSION, STIFFNESS, FIBER REINFORCED COMPOSITES, STIFFENING, COMPOSITE STRUCTURES, STRENGTH(MECHANICS), CURVATURE, ALUMINUM, SHEAR STRESSES, BUCKLING, FUSELAGES, FAILURE(MECHANICS), COMPOSITE AIRCRAFT.
Subject Categories : Aircraft
Laminates and Composite Materials
Distribution Statement : APPROVED FOR PUBLIC RELEASE