Short, textile composite columns with a J cross section were tested in axial compression to study the modes of failure. The textile architecture is a 2 x 2, 2-D triaxial braided preform(0 degree18k/ +/-64 degree6k) 39.7% axial, which was resin transfer molded with 3M PR500 epoxy resin. Finite element analyses (FEA) of the test specimens are correlated with the test results. These short column compression tests and analyses were conducted to improve the progressive failure analysis of circular fuselage frame segments having a nominal radius of 120 inches and a forty-eight degree included angle. The fuselage frame segments were subjected to a quasi-static, radially inward load in previous tests. The short column test specimens were cut from some of the fuselage frames. Additional finite element analyses of the forty-eight degree frame segments are discussed that include branched shell models, geometric nonlinearity, contact analysis of the load platen with the frame, and a strain criterion to detect a web-flange junction failure observed in the short column tests.
Response and failure of textile composite fuselage frames under radial inward load
2002
10 Seiten, 5 Quellen
Aufsatz (Konferenz)
Englisch
Response and Failure of Textile Composite Fuselage Frames Under Radial Inward Load
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