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(Referência obtida automaticamente do Web of Science, por meio da informação sobre o financiamento pela FAPESP e o número do processo correspondente, incluída na publicação pelos autores.)

On the effects of structural coupling on the supersonic flutter and limit cycle oscillations of transversely reinforced panels

Texto completo
Autor(es):
Pacheco, Douglas R. Q. [1] ; Ferreira, Antonio J. M. [2] ; Marques, Flavio D. [1]
Número total de Autores: 3
Afiliação do(s) autor(es):
[1] Univ Sao Paulo, Sao Carlos Sch Engn, Sao Carlos, SP - Brazil
[2] Univ Porto, Fac Engn, Porto - Portugal
Número total de Afiliações: 2
Tipo de documento: Artigo Científico
Fonte: JOURNAL OF FLUIDS AND STRUCTURES; v. 79, p. 158-170, MAY 2018.
Citações Web of Science: 9
Resumo

Panel flutter is an aeroelastic phenomenon that can critically affect aircraft skin in supersonic flight. The majority of works published on this subject treat each skin panel as an isolated structural element. In reality, however, aircraft skin is usually built as large panels stiffened by stringers and frames. Thus, the multiple subpanels sitting between stiffeners are structurally coupled rather than isolated, and therefore can interact during flutter. In the present work, a reinforced panel is simulated as a rectangular plate reinforced by an elastic beam that ``subdivides{''} the panel into two square subpanels (bays). The panel is modeled as a Mindlin-von Karman plate, and the stiffener as a nonlinear eccentric Timoshenko beam. The problem is discretized through the Finite Element Method, and the resulting nonlinear equations of motion are solved via numerical time-marching. This approach is a higher-fidelity extension to the methodology employed by the authors in previous works, where the stiffeners were idealized as immovable simple supports - the so-called multibay model. The present results are compared to those from both the multibay model and the single-panel model. Each bay in the stiffened panel is identical to the reference single panel. Results are produced for several stiffener cross-sectional aspect ratios, r. Linear flutter boundary results show that, as r increases, the critical dynamic pressure asymptotically approaches that of a single panel. Nonlinear post-flutter analyses reveal the occurrence of jump discontinuities in the limit cycle amplitude diagrams. Similarly to what has been seen in the literature for multibay panels, the jumps are related to the nonlinear structural coupling between neighboring bays, and occur when there is a shift in the flutter mechanism. Furthermore, it is shown that reducing the cross-sectional aspect ratio postpones not only the onset of flutter but also the jumps, which can be avoided for sufficiently small r. Important engineering design guidelines can be established from the present study, as the multibay and single-panel models are shown to be generally conservative regarding linear behavior, but potentially unsafe in the post-flutter regime. (C) 2018 Elsevier Ltd. All rights reserved. (AU)

Processo FAPESP: 16/20393-5 - Flutter supersônico não linear de painel usando teoria de deformação-deslocamento de Von Kármán
Beneficiário:Douglas Ramalho Queiroz Pacheco
Linha de fomento: Bolsas no Brasil - Iniciação Científica