Accession Number : ADA304911
Title : Design and Fabrication of Composite Wing Panels Containing a Production Splice.
Descriptive Note : Contractor rept.,
Corporate Author : GENERAL DYNAMICS FORT WORTH TX FORT WORTH DIV
Personal Author(s) : Reed, D. L.
PDF Url : ADA304911
Report Date : AUG 1975
Pagination or Media Count : 92
Abstract : Bolted specimens representative of both upper and lower wing surface splices of a transport aircraft were designed and manufactured for static and random load tension and compression fatigue testing including ground-air-ground load reversals. The specimens were fabricated with graphite-epoxy composite materials. Multiple tests were conducted at various load levels and the results were used as input to a statistical wearout model. The statically designed specimens performed very well under highly magnified fatigue loadings. Two large panels, one tension and compression, were fabricated for testing by NASA-LRC.
Descriptors : *TRANSPORT AIRCRAFT, *SPLICES, *GRAPHITE EPOXY COMPOSITES, *BOLTED JOINTS, *COMPOSITE WINGS, LOAD DISTRIBUTION, FIBERGLASS, NONDESTRUCTIVE TESTING, COMPOSITE MATERIALS, LAMINATES, PANELS, DISPLACEMENT, TENSILE PROPERTIES, FABRICATION, STRAIN(MECHANICS), STRENGTH(MECHANICS), RELIABILITY, SHEAR STRESSES, BUCKLING, DESIGN CRITERIA, FAILURE(MECHANICS), SKIN(STRUCTURAL), FATIGUE TESTS(MECHANICS), COMPRESSIVE PROPERTIES, HONEYCOMB STRUCTURES.
Subject Categories : Transport Aircraft
Laminates and Composite Materials
Couplers, Fasteners, and Joints
Distribution Statement : APPROVED FOR PUBLIC RELEASE