Design of fiber metal laminate shear panels for ultra-high capacity aircraft
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Appropriate manufacturing and joining technologies required validation for the progressive laminates. Corrosion was a problem to be quantified and resolved with new sizing and treatments. Material models and static failure criteria for the prediction of the material behaviour of FML and ML in both the microscopic and the macroscopic scale would be developed and verified.
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Finally, optimisation criteria for the design of coupons and structural elements would be developed and experimentally verified for laminates with the aim to reduce the overall weight of the aircraft fuselage. Experimental and numerical activities were developed to investigate the behaviour of Fibre Metal Laminates FML shear loaded panels with a bonded window frame.
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Both static and fatigue tests were carried out at the Department of Aerospace Engineering of Pisa on 10 panels manufactured by Alenia Aeronautica. In addition to technological problems, the tested specimens represent very critical components, involving fundamental aspects of the structural design of fuselage panels; in particular, the primary interest to exploit the post buckling behaviour of FML components, as commonly applied in conventional aluminium alloy fuselage structures, is associated with the effort of making reinforced holes which do not alter significantly the stress distribution of the main body of the panel.
The numerical results have shown a very good agreement with the experimental data, thus revealing an effective instrument to study the behaviour of a post buckled shear panel, in presence of the neutral hole issue. Skip to main content. Legal notice Cookies Contact Search.
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Type of funding:. Key Results:. Lead Organisation:. Eads Deutschland Gmbh Address:. Willy- Messerschmitt- Strasse. Organisation Website:. Wittenberg E.
This process is experimental and the keywords may be updated as the learning algorithm improves. This is a preview of subscription content, log in to check access. Kuhn, P. Part I-Methods of Analysis. National Advisory Committee for Aeronautics, May Google Scholar. Part II-Experimental Verification. Van Wimersma, B. Report TD-R Timoshenko, S.
Gerard, G. National Advisory Committee for Aeronautics, July Galambos, T.http://gelatocottage.sg/includes/2019-12-07/4543.php
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Anonymous, Buckling of flat plates in shear. Rankin, C. December