Enhanced vibration correlation technique to predict the buckling load of unstiffened composite cylindrical shells

Franzoni, Felipe; Gliszczyński, Adrian; Baciu, T.D.; Arbelo, Mariano A.; Degenhardt, Richard

doi:10.1016/j.jsv.2022.117280

Cited by 3 publications

(2 citation statements)

References 25 publications

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“…The numerical models used in this study were defined for a family of nominally identical, unstiffened, CFRP cylindrical shells, shown also in the work of Degenhardt et al [40]. The actual cylinders used were Z15, Z17, Z18, and Z20-Z26 and for which VCT results were shown in [19,41]. The cylinder's layup is [±24, ±41], with a thickness of 0.5 mm, a total length of 540 mm, a free length of 500 mm (between the potted ends), and a radius of 250 mm (nominal dimensions).…”

Section: Sensitivity Study Based On Fe Resultsmentioning

confidence: 99%

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Sensitivity analysis for buckling characterisation using the vibration correlation technique

Baciu

Degenhardt

Franzoni³

et al. 2023

Thin-Walled Structures

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Section: Sensitivity Study Based On Fe Resultsmentioning

confidence: 99%

“…The CFRP cylinder is modelled with S8R shell elements, while the potting is modelled with C3D20R brick elements. A more detailed description on the FE models used can be found in [41].…”

Section: Tablementioning

confidence: 99%

Sensitivity analysis for buckling characterisation using the vibration correlation technique

Baciu

Degenhardt

Franzoni³

et al. 2023

Thin-Walled Structures

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Towards the fast buckling load prediction of composite shells via Bloch wave based numerical vibration correlation technique

Lai,

Sun,

Huang

et al. 2024

Thin-Walled Structures

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Static stability of sandwich panels with honeycomb cores made by additive technologies

Chernobryvko,

Avramov,

Uspenskyi

et al. 2023

Teh. Meh.

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This paper presents approaches to and the results of finite-element analysis of static buckling in cylindrical sandwich panels. The core layer of the panels is a polylactide honeycomb core 3D printed using the Fused Deposition Modeling (FDM) additive technology. The two thin face layers are made of carbon fiber reinforced polymer. Such structures are promising for use as structural elements of rockets and drones. For them, the determination of stability under longitudinal and radial loads is an important issue. The global buckling of a cylindrical panel under longitudinal loads and the local buckling of a honeycomb core as a plate structure under radial loads are studied. The geometrically nonlinear deformation of a cylindrical panel under a combination of transverse and radial loads is studied. Seven cylindrical sandwich panels with the radius-to-thickness ratio in the range 5 ? R/h ? 50 and a sandwich plate are considered. The effect of the radius of curvature on the characteristics of local and global buckling is investigated. The problem is solved by the finite element method using the ANSYS software system. The convergence of the finite element model was investigated. For this purpose, a strained state under the action of a longitudinal load was studied. The finite-element mesh parameters were selected to ensure the convergence of the results. Two finite element models, an “exact” one and an “approximate” one, were constructed to investigate global buckling under longitudinal loads. The «exact» model includes a honeycomb core represented by its geometry. In the «approximate» model of the sandwich panel, the honeycomb core is replaced with an equivalent homogenized layer. It was found that for longitudinal loads the modes of the global buckling of the cylindrical sandwich panels and the sandwich plate under study are almost the same. It was shown that the critical loads obtained by the «exact» and the «approximate» model are close. It was found that when a cylindrical panel is deformed under the action of a combination of longitudinal and radial subcritical loads, the calculated results for the «exact» and the «approximate» model are close. Therefore, longitudinal buckling can be considered using the homogenized model, which is much simpler in terms of computations.

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Enhanced vibration correlation technique to predict the buckling load of unstiffened composite cylindrical shells

Cited by 3 publications

References 25 publications

Sensitivity analysis for buckling characterisation using the vibration correlation technique

Sensitivity analysis for buckling characterisation using the vibration correlation technique

Towards the fast buckling load prediction of composite shells via Bloch wave based numerical vibration correlation technique

Static stability of sandwich panels with honeycomb cores made by additive technologies

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