Bruna Luiza Nolli
Federal University of Minas Gerais, Av Presidente Antônio Carlos, 6627, Belo Horizonte, Minas Gerais, Brazil
Carlos Cimini Jr.
Federal University of Minas Gerais, Av Presidente Antônio Carlos, 6627, Belo Horizonte, Minas Gerais, Brazil
Cristiano Pena
Federal University of Minas Gerais, Av Presidente Antônio Carlos, 6627, Belo Horizonte, Minas Gerais, Brazil
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http://dx.doi.org/10.3384/ecp19162019Published in: FT2019. Proceedings of the 10th Aerospace Technology Congress, October 8-9, 2019, Stockholm, Sweden
Linköping Electronic Conference Proceedings 162:19, p. 164-173
Published: 2019-10-23
ISBN: 978-91-7519-006-8
ISSN: 1650-3686 (print), 1650-3740 (online)
Aeronautic industry is aiming to increase the efficiency and to reduce the costs of their aircrafts, in order to develop airplanes with better performance and lower fuel consumption. Researches have demonstrated that shear panels can carry a significant amount of load after reaching its initial buckling load. Consequently, exploring the post-buckling capacity of composite materials reinforced panels results in lighter and less expensive structures. For the metallic reinforced panels there is a consolidated methodology developed by NASA to calculate the diagonal tension, NACA TN2661. However, a theory for the panel’s post-buckling behaviour in composite reinforced panels is yet to be developed. Therefore, the purpose of this study was to contribute to this new theory and focus on the influence of stacking sequence and fibre orientations on the post-buckling behaviour of composite reinforced panels. The main goals were to develop a method to build a FE model to represents the post-buckling behaviour of the composite reinforced panel in order to avoid having to use experimental results in future projects; study the variations in stacking sequence in post-buckling analysis; choose the material to build a reinforced panel that have the best behaviour during the post-buckling analysis: metal or composite. The results have shown that the FEM, considering the load, boundary conditions and materials described in this study, can represent the behaviour of the composite reinforced panel and its post-buckling behaviour. Also, after the comparison between six composite reinforced panels models with different stacking sequence, the layup that presented the lowest values for the failure indices was the one with +45 and -45 at the outside layers. This laminate was chosen to be compared with the metallic reinforced panel model, and this comparison has shown that the composite reinforced panel could withstand higher loads, so it is considered the best for the post-buckling behaviour analysis.
