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45-percent fiber 45-percent fiber-volume graphite 48 percent 50 percent Aerostructures Directorate agreement with test analyses were conducted based on 50-percent closest agreement compared with test composite density Composite shear elastic composite tail boom conditions of 45 conducted for three contains a detailed degrees of freedom design skin thickness dynamic finite element dynamic model fiber weight fiber-volume graphite skins filament finite element analysis finite element model gave the closest graphite skins gave graphite/epoxy skin Langley Research Center lateral bending lb/in Longitudinal elastic modulus material tests Measured Material Properties measured skin thicknesses NASA nodes obtained from reference OH-58 composite tail orthonormal mode shapes Performing Organization Photomicrographs Research Center Hampton ring frames shear elastic modulus shown in figure Skin thickness measurements static and dynamic station 32 station 49 TABLE tail boom skin Tail boom station test data Test Results Transverse elastic modulus U.S. Army varied from 44.6 vertical and lateral volume wet-filament-wound