Buckling Response of Transversely Loaded Composite Shells, Part 1: Experiments
| Autor: | Brian L. Wardle, Paul A. Lagace, Mark A. Tudela |
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| Rok vydání: | 2004 |
| Předmět: | |
| Zdroj: | AIAA Journal. 42:1457-1464 |
| ISSN: | 1533-385X 0001-1452 |
| DOI: | 10.2514/1.11884 |
| Popis: | The transverse loading response of convex composite shell structures typical of aircraft fuselage sections was investigated, and the experimental work is reported. Important mechanisms in the response, particularly instabilities (buckling), were studied by investigation of the force-deflection response and the evolution of full-field deformation shapes. Quasi-static tests were conducted to simulate impact of convex shells. The specimens were laminated, cylindrical shell sections in [±45 n /0 n ] s configurations, where n takes on values of 1, 2, and 3. The three structural parameters of radius, span, and thickness were varied according to a scaling relation and were chosen to represent approximate fuselage dimensions of general aviation and commercial transport aircraft. All specimens were evaluated for damage with dye-penetrant enhanced x radiography and sectioning after mechanical testing. The structural response changes both quantitatively and qualitatively for the different shell geometries and was categorized into three types based on the existence of the instability transition characteristics such as deformation shapes. The presence of the instability becomes more likely for deeper, thinner specimens where the ratio of membrane stiffness to bending stiffness is higher. This can be characterized by a structural parameter involving geometric and material factors. The majority of the specimens showed no damage, but the limited experimental evidence did show plate-like damage occurring in the shell specimens before any instability. Suggestions for further work to extend these findings are made. |
| Databáze: | OpenAIRE |
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