Accession Number : ADA305443
Title : Lamination Residual Stresses in Multilayered Fiber Composites.
Descriptive Note : Technical note,
Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH LEWIS RESEARCH CEN TER
Personal Author(s) : Chamis, Christos C.
PDF Url : ADA305443
Report Date : FEB 1971
Pagination or Media Count : 31
Abstract : Residual stresses arising from the lamination fabrication process are investigated using linear laminate theory. An equation to predict the residual stresses is given. The pertinent variables that influence residual stresses are identified. Several composite systems with various ply layup configurations are examined. Results are presented to illustrate the dependence of the residual stresses on the pertinent variables. The residual stresses are very sensitive to constituent material properties, composite stacking sequence and orientation, fiber content, and processing temperature. It is found that ply transverse tensile and in-plane shear residual stresses can reach magnitudes comparable to corresponding ply strengths and cause transply cracks in the composites. Residual stresses can also cause interply delamination. Ways to prevent transply cracking and interply delamination are recommended. (AN)
Descriptors : *FIBER REINFORCED COMPOSITES, *RESIDUAL STRESS, *GRAPHITE EPOXY COMPOSITES, TENSILE STRENGTH, STRESS ANALYSIS, ALUMINUM ALLOYS, LAMINATES, STRUCTURAL ANALYSIS, TENSILE STRESS, CRACKING(FRACTURING), MODULUS OF ELASTICITY, CARBON FIBERS, MATRIX MATERIALS, GLASS, TEMPERATURE GRADIENTS, STRUCTURAL RESPONSE, THERMAL EXPANSION, SHEAR STRESSES, BORON, COMPRESSIVE STRENGTH, STACKING, THERMAL STRESSES, DELAMINATION, SHEAR STRENGTH.
Subject Categories : Laminates and Composite Materials
Distribution Statement : APPROVED FOR PUBLIC RELEASE