Accession Number : ADA304623
Title : Analysis of Edge Impact Stresses in Composite Plates.
Descriptive Note : Topical rept. May 73-May 74,
Corporate Author : PRINCETON UNIV NJ DEPT OF AEROSPACE AND MECHANICAL SCIENCES
Personal Author(s) : Moon, F. C. ; Kang, C. K.
PDF Url : ADA304623
Report Date : JUL 1974
Pagination or Media Count : 79
Abstract : The in-plane edge impact of composite plates, with or without a protection strip, is investigated in this work. A computational analysis based on the Fast Fourier Transform technique is presented. The particular application of the present method is in the understanding of the foreign object damage problem of composite fan blades. However, the method is completely general and may he applied to the study of other stress wave propagation problems in a half space. Results indicate that for the protective strip to be effective in reducing impact stresses in the composite the thickness must be equal or greater than the impact contact dimension. Also large interface shear stresses at the strip - composite boundary can be induced under impact. (MM)
Descriptors : *FIBER REINFORCED COMPOSITES, *FAN BLADES, *JET ENGINES, *IMPACT STRENGTH, STRESS STRAIN RELATIONS, COMPUTER PROGRAMS, IMPACT, STRESS ANALYSIS, COMPOSITE MATERIALS, DISPLACEMENT, COMPOSITE STRUCTURES, MATRIX MATERIALS, STEEL, PLATES, SHEAR STRESSES, HAIL, BIRD STRIKES, FAST FOURIER TRANSFORMS, LEADING EDGES, FAILURE(MECHANICS), POISSON RATIO, GRAPHITE EPOXY COMPOSITES.
Subject Categories : Laminates and Composite Materials
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE