It is widely recognised that the optimal lay-up to resist classical local buckling of a laminated cylindrical shell subject to compression loading is one that is quasi-isotropic in nature. This ideal is difficult to achieve in practice due to manufacturing and additional design constraints. The minimum number of unidirectional layers, based on 0Â°, 90Â°, Â±45Â° angles, is 48 â€“ an example lay-up is shown. Balanced and symmetric laminates, that exhibit quasi-isotropic properties in-plane, are shown to give reduced buckling capacity depending on two factors. The first concerns the overall homogeneity of the laminate whilst the second is a function of the amount of flexural/torsional coupling. The former is shown to have the greater influence. In the absence of closed-form solutions these effects have been numerically quantified using finite element (FE) analysis techniques. Practical design guidelines are deduced.
|Translated title of the contribution||The effect of flexural/twist anisotropy on compression buckling of quasi-isotropic laminated cylindrical shells|
|Pages (from-to)||195 - 204|
|Number of pages||10|
|Publication status||Published - Feb 2002|