Accession Number : ADA301305
Title : Effect of Measured Material Properties on the Finite Element Analysis of an OH-58 Composite Tail Boom.
Descriptive Note : Technical memorandum,
Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CEN TER
Personal Author(s) : Bowman, Lynn M.
PDF Url : ADA301305
Report Date : OCT 1985
Pagination or Media Count : 29
Abstract : A static and dynamic finite element analysis was conducted on a U.S. Army OH-58 composite tail boom and compared with test data. The tail boom was a filament-wound graphite/epoxy monocoque structure. The structural design of the composite tail boom skin was based on 50-percent graphite fiber volume. However, material tests on representative samples of the tail boom skin revealed that the graphite fiber-volume fraction varied from 44.6 to 49.3 percent. To determine the effect of using measured material properties, static and dynamic finite element analyses were conducted for three fiber-volume conditions of 45, 48, and 50 percent. The static and dynamic model with the 45-percent fiber-volume graphite skins gave the closest agreement with test data. (AN)
Descriptors : *COMPOSITE STRUCTURES, *HELICOPTERS, *TAILS(AIRCRAFT), MATHEMATICAL MODELS, FILAMENT WOUND CONSTRUCTION, FINITE ELEMENT ANALYSIS, STATIC LOADS, STRUCTURAL ANALYSIS, SHEAR MODULUS, FIBER REINFORCED COMPOSITES, MODULUS OF ELASTICITY, DYNAMIC LOADS, SKIN(STRUCTURAL), STATIC TESTS, DYNAMIC TESTS, GRAPHITE EPOXY COMPOSITES, STRUCTURAL ENGINEERING, TAIL HELICOPTER ROTORS.
Subject Categories : Helicopters
Laminates and Composite Materials
Distribution Statement : APPROVED FOR PUBLIC RELEASE