Title:
Finite element-based failure models for carbon/epoxy tape composites

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dc.contributor.advisor Makeev, Andrew
dc.contributor.author Seon, Guillaume en_US
dc.contributor.committeeMember Armanios, Erian A.
dc.contributor.committeeMember Bauchau, Olivier A.
dc.contributor.department Aerospace Engineering en_US
dc.date.accessioned 2009-06-08T18:45:27Z
dc.date.available 2009-06-08T18:45:27Z
dc.date.issued 2009-04-13 en_US
dc.description.abstract Laminated carbon/epoxy composite structures are increasingly used in the aerospace industries. Low weight, elastic tailoring, and high durability make the composite materials well suited for replacement of conventional metallic structures. However the difficulty to capture structural failure phenomena is a significant barrier to more extensive use of laminated composites. Predictions are challenging because matrix (resin) dominated failure mechanisms such as delaminations and matrix cracking contribute to the structural failure in addition to fiber-dominated failures. A key to rigorous failure predictions for composites is availability of measurements to quantify structural model parameters including matrix-dominated stress-strain relations and failure criteria. Novel techniques for measurement of nonlinear interlaminar constitutive properties in tape composites have been recently developed at Georgia Institute of Technology. Development of methods for accurate predictions of failure in carbon/epoxy tape laminate configurations with complex lay-ups is the main focus of this work. Failures through delamination and matrix cracking are considered. The first objective of this effort is to implement nonlinear interlaminar shear stress-strain relations for IM7/8552 carbon/epoxy tape in ABAQUS finite element models and validate structural delamination failure predictions with tests. Test data for composite configurations with wavy fibers confirm that nonlinear interlaminar shear stress-strain response enables accurate failure prediction. The problem of the presence of porosity and its influence on failure was noted. The second objective is to assess the ability to simulate initiation and propagation of matrix-ply cracking. Failure models for IM7/8552 carbon/epoxy tape open-hole tensile coupons are built and validated. en_US
dc.description.degree M.S. en_US
dc.identifier.uri http://hdl.handle.net/1853/28117
dc.publisher Georgia Institute of Technology en_US
dc.subject Open-hole en_US
dc.subject Wavy plies en_US
dc.subject Abaqus en_US
dc.subject Matrix cracking en_US
dc.subject Delamination en_US
dc.subject.lcsh Carbon composites
dc.subject.lcsh Epoxy compounds
dc.subject.lcsh Fracture mechanics
dc.subject.lcsh Deformations (Mechanics)
dc.subject.lcsh Structural failures
dc.title Finite element-based failure models for carbon/epoxy tape composites en_US
dc.type Text
dc.type.genre Thesis
dspace.entity.type Publication
local.contributor.corporatename College of Engineering
local.contributor.corporatename Daniel Guggenheim School of Aerospace Engineering
local.relation.ispartofseries Master of Science in Aerospace Engineering
local.relation.ispartofseries Master of Science in Aerospace Engineering
relation.isOrgUnitOfPublication 7c022d60-21d5-497c-b552-95e489a06569
relation.isOrgUnitOfPublication a348b767-ea7e-4789-af1f-1f1d5925fb65
relation.isSeriesOfPublication 2fef2987-f871-4c1d-acfa-e642641793f5
relation.isSeriesOfPublication 09844fbb-b7d9-45e2-95de-849e434a6abc
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