Exact solution of finite geometry composite panels under transient surface loading

Persistent Link:
http://hdl.handle.net/10150/278508
Title:
Exact solution of finite geometry composite panels under transient surface loading
Author:
Anderson, Todd Alan, 1971-
Issue Date:
1995
Publisher:
The University of Arizona.
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.
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.
Type:
text; Thesis-Reproduction (electronic)
Keywords:
Applied Mechanics.; Engineering, Mechanical.
Degree Name:
M.S.
Degree Level:
masters
Degree Program:
Graduate College; Aerospace and Mechanical Engineering
Degree Grantor:
University of Arizona
Advisor:
Madenci, Erdogan

Full metadata record

DC FieldValue Language
dc.language.isoen_USen_US
dc.titleExact solution of finite geometry composite panels under transient surface loadingen_US
dc.creatorAnderson, Todd Alan, 1971-en_US
dc.contributor.authorAnderson, Todd Alan, 1971-en_US
dc.date.issued1995en_US
dc.publisherThe University of Arizona.en_US
dc.rightsCopyright © 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.description.abstractThe 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.en_US
dc.typetexten_US
dc.typeThesis-Reproduction (electronic)en_US
dc.subjectApplied Mechanics.en_US
dc.subjectEngineering, Mechanical.en_US
thesis.degree.nameM.S.en_US
thesis.degree.levelmastersen_US
thesis.degree.disciplineGraduate Collegeen_US
thesis.degree.disciplineAerospace and Mechanical Engineeringen_US
thesis.degree.grantorUniversity of Arizonaen_US
dc.contributor.advisorMadenci, Erdoganen_US
dc.identifier.proquest1376074en_US
dc.identifier.bibrecord.b33517034en_US
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