Subcomponent tests for composite fuselage technology readinessAn account is given of a NASA research effort aimed at the development of an all-composite transport aircraft fuselage incorporating joints and cutouts which meets all design requirements. The design, construction, and analysis activities associated with the 30-ft-long fuselage section gave attention to critically important subcomponent specimens, including shear-tee pulloff specimens, stiffened and unstiffened cutout panels, longitudinal and transverse skin splices, longeron runouts, transverse skin-longerons, stiffened shear panels, and window belt panels. The analysis of large cutouts was conducted with coupling FEM analyses incorporating accurate failure criteria for tension and shear; the strategic application of S2 glass fiber plies around cutouts was demonstrated both analytically and experimentally to increase load capacity with virtually no weight penalty.
Document ID
19900046050
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Madan, R. C. (Douglas Aircraft Co., Inc. Long Beach, CA, United States)
Hawley, A. V. (Douglas Aircraft Co. Long Beach, CA, United States)