Exact solution of finite geometry composite panels under transient surface loading
| dc.contributor.advisor | Madenci, Erdogan | en_US |
| dc.contributor.author | Anderson, Todd Alan, 1971- | |
| dc.creator | Anderson, Todd Alan, 1971- | en_US |
| dc.date.accessioned | 2013-04-03T13:27:22Z | |
| dc.date.available | 2013-04-03T13:27:22Z | |
| dc.date.issued | 1995 | en_US |
| dc.identifier.uri | http://hdl.handle.net/10150/278508 | |
| dc.description.abstract | The exact three-dimensional transient solution of a multi-layer orthotropic panel subjected to transverse loading is presented. The finite geometry panel, supported by rollers, is subjected to an arbitrarily distributed surface load. Governing equations, derived from Reissner's functional, are solved by applying Fourier or Laplace transformation in time and enforcing the continuity of traction and displacement components between the adjacent layers. Material damping is incorporated into the analysis through complex material constants. The accuracy of the present analysis is established by considering a thick and thin laminate under quasi-static and transient loading, respectively. The solution of the static analysis is compared with a known exact solution and the transient analysis is compared with a finite element analysis. Transient responses of a thick laminate and a composite sandwich panel are also investigated. Material damping is found to significantly affect the transient stress and displacement fields of a laminate. | |
| 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, Mechanical. | en_US |
| dc.title | Exact solution of finite geometry composite panels under transient surface loading | en_US |
| dc.type | text | en_US |
| dc.type | Thesis-Reproduction (electronic) | en_US |
| thesis.degree.grantor | University of Arizona | en_US |
| thesis.degree.level | masters | en_US |
| dc.identifier.proquest | 1376074 | en_US |
| thesis.degree.discipline | Graduate College | en_US |
| thesis.degree.discipline | Aerospace and Mechanical Engineering | en_US |
| thesis.degree.name | M.S. | en_US |
| dc.identifier.bibrecord | .b33517034 | en_US |
| refterms.dateFOA | 2018-08-27T15:13:06Z | |
| html.description.abstract | The exact three-dimensional transient solution of a multi-layer orthotropic panel subjected to transverse loading is presented. The finite geometry panel, supported by rollers, is subjected to an arbitrarily distributed surface load. Governing equations, derived from Reissner's functional, are solved by applying Fourier or Laplace transformation in time and enforcing the continuity of traction and displacement components between the adjacent layers. Material damping is incorporated into the analysis through complex material constants. The accuracy of the present analysis is established by considering a thick and thin laminate under quasi-static and transient loading, respectively. The solution of the static analysis is compared with a known exact solution and the transient analysis is compared with a finite element analysis. Transient responses of a thick laminate and a composite sandwich panel are also investigated. Material damping is found to significantly affect the transient stress and displacement fields of a laminate. |
