Nonlinear thermo-mechanical analysis of stiffened composite laminates by a new finite element
| dc.contributor.advisor | Madenci, Erdogan | en_US |
| dc.contributor.author | Barut, Atila, 1966- | |
| dc.creator | Barut, Atila, 1966- | en_US |
| dc.date.accessioned | 2013-04-18T10:02:08Z | |
| dc.date.available | 2013-04-18T10:02:08Z | |
| dc.date.issued | 1998 | en_US |
| dc.identifier.uri | http://hdl.handle.net/10150/282754 | |
| dc.description.abstract | A new stiffened shell element combining shallow beam and shallow shell elements is developed for geometrically nonlinear analysis of stiffened composite laminates under thermal and/or mechanical loading. The formulation of this element is based on the principal of virtual displacements in conjunction with the co-rotational form of the total Lagrangian description of motion. In the finite element formulation, both the shell and the beam (stiffener) elements account for transverse shear deformations and material anisotropy. The cross-section of the stiffener (beam) can be arbitrary in geometry and lamination. In order to combine the stiffener with the shell element, constraint conditions are applied to the displacement and rotation fields of the stiffener. These constraint conditions ensure that the cross-section of the stiffener remains co-planar with the shell section after deformation. The resulting expressions for the displacement and rotation fields of the stiffener involve only the nodal unknowns of the shell element, thus reducing the total number of degrees of freedom. Also, the discretization of the entire stiffened shell structure becomes more flexible. | |
| dc.language.iso | en_US | en_US |
| dc.publisher | The University of Arizona. | en_US |
| dc.rights | Copyright © is held by the author. Digital access to this material is made possible by the University Libraries, University of Arizona. Further transmission, reproduction or presentation (such as public display or performance) of protected items is prohibited except with permission of the author. | en_US |
| dc.subject | Applied Mechanics. | en_US |
| dc.subject | Engineering, Aerospace. | en_US |
| dc.subject | Engineering, Mechanical. | en_US |
| dc.title | Nonlinear thermo-mechanical analysis of stiffened composite laminates by a new finite element | en_US |
| dc.type | text | en_US |
| dc.type | Dissertation-Reproduction (electronic) | en_US |
| thesis.degree.grantor | University of Arizona | en_US |
| thesis.degree.level | doctoral | en_US |
| dc.identifier.proquest | 9906525 | en_US |
| thesis.degree.discipline | Graduate College | en_US |
| thesis.degree.discipline | Aerospace and Mechanical Engineering | en_US |
| thesis.degree.name | Ph.D. | en_US |
| dc.identifier.bibrecord | .b38868337 | en_US |
| refterms.dateFOA | 2018-05-25T22:58:26Z | |
| html.description.abstract | A new stiffened shell element combining shallow beam and shallow shell elements is developed for geometrically nonlinear analysis of stiffened composite laminates under thermal and/or mechanical loading. The formulation of this element is based on the principal of virtual displacements in conjunction with the co-rotational form of the total Lagrangian description of motion. In the finite element formulation, both the shell and the beam (stiffener) elements account for transverse shear deformations and material anisotropy. The cross-section of the stiffener (beam) can be arbitrary in geometry and lamination. In order to combine the stiffener with the shell element, constraint conditions are applied to the displacement and rotation fields of the stiffener. These constraint conditions ensure that the cross-section of the stiffener remains co-planar with the shell section after deformation. The resulting expressions for the displacement and rotation fields of the stiffener involve only the nodal unknowns of the shell element, thus reducing the total number of degrees of freedom. Also, the discretization of the entire stiffened shell structure becomes more flexible. |
