{"id":{"repo_id":"vt","oai_identifier":"oai:vtechworks.lib.vt.edu:10919/104298"},"canonical_url":"https://search.dev.ndltd.org/etd/vt/oai:vtechworks.lib.vt.edu:10919/104298","repository":{"repo_id":"vt","name":"Virginia Tech","base_url":"https://vtechworks.lib.vt.edu/oai/request"},"display":{"title":"Compressive failure of notched angle-ply composite laminates: three-dimensional finite element analysis and experiment","abstract":"Five angle-ply laminates ([0₄₈], [(±10)₁₂]<sub>s</sub>, [(±20)₁₂]<sub>s</sub>, [(±30)₁₂]<sub>s</sub>, and [(±45)₁₂]<sub>s</sub> with central circular holes were tested under uniaxial compressive loading. The results from these tests show that the [(±45)₁₂]<sub>s</sub> laminate exhibited plastic deformation, with ultimate applied strains exceeding -1%. All other laminates failed in a brittle manner with ultimate strains of less than -0.5%. A three-dimensional finite element stress analysis was performed for the same laminates. A failure analysis based on the three-dimensional stress tensor polynomial predicted that failure will initiate at the intersection of the ply interface with hole edge for all laminates, and be due to a combination of the out-of-plane and in-plane shear stresses. Use of the state of stress directly on the hole edge in the prediction of laminate failure resulted in predictions of laminate ultimate strengths which were less than experimentally observed values by as much as a factor of ten. In addition, symmetry considerations for three-dimensional finite element modelling of composite laminates are discussed, and a two-dimensional finite element model based on shear-deformable plate theory is predicted.","abstract_html":"Five angle-ply laminates ([0₄₈], [(±10)₁₂]&lt;sub&gt;s&lt;/sub&gt;, [(±20)₁₂]&lt;sub&gt;s&lt;/sub&gt;, [(±30)₁₂]&lt;sub&gt;s&lt;/sub&gt;, and [(±45)₁₂]&lt;sub&gt;s&lt;/sub&gt; with central circular holes were tested under uniaxial compressive loading. The results from these tests show that the [(±45)₁₂]&lt;sub&gt;s&lt;/sub&gt; laminate exhibited plastic deformation, with ultimate applied strains exceeding -1%. All other laminates failed in a brittle manner with ultimate strains of less than -0.5%. A three-dimensional finite element stress analysis was performed for the same laminates. A failure analysis based on the three-dimensional stress tensor polynomial predicted that failure will initiate at the intersection of the ply interface with hole edge for all laminates, and be due to a combination of the out-of-plane and in-plane shear stresses. Use of the state of stress directly on the hole edge in the prediction of laminate failure resulted in predictions of laminate ultimate strengths which were less than experimentally observed values by as much as a factor of ten. In addition, symmetry considerations for three-dimensional finite element modelling of composite laminates are discussed, and a two-dimensional finite element model based on shear-deformable plate theory is predicted.","abstract_has_math":false,"creators":["Burns, Stephen W."],"institution":"Virginia Polytechnic Institute and State University","degree_name":"M.S.","degree_level":"masters","degree_discipline":"Engineering Mechanics","degree_department":"Engineering Mechanics","school":null,"contributors":[],"advisors":[],"committee_chairs":[],"committee_members":[],"year":1985,"date_issued":"1985","date_published":"1985","updated_at":"2026-07-22T22:20:27Z","subjects":[],"languages":["en"],"rights":["In Copyright"],"rights_urls":["http://rightsstatements.org/vocab/InC/1.0/"],"identifier_entries":[]},"links":{"outbound_url":"http://hdl.handle.net/10919/104298","outbound_label":"Handle","outbound_source":"dc:identifier.uri"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor.department","label":"Department","values":["Engineering Mechanics"]},{"key":"dc:creator","label":"Author","values":["Burns, Stephen W."]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date.accessioned","label":"Dc Date Accessioned","values":["2021-07-22T18:16:12Z"]},{"key":"dc:date.available","label":"Dc Date Available","values":["2021-07-22T18:16:12Z"]},{"key":"dc:date.issued","label":"Date","values":["1985"]},{"key":"dc:publisher","label":"Institution","values":["Virginia Polytechnic Institute and State University"]},{"key":"dc:type","label":"Dc Type","values":["Thesis"]},{"key":"dc:type.dcmitype","label":"Dc Type Dcmitype","values":["Text"]},{"key":"thesis:degree_discipline","label":"Discipline","values":["Engineering Mechanics"]},{"key":"thesis:degree_level","label":"Degree Level","values":["masters"]},{"key":"thesis:degree_name","label":"Degree Name","values":["M.S."]},{"key":"thesis:institution_name","label":"Thesis Institution Name","values":["Virginia Polytechnic Institute and State University"]}]},{"id":"language_rights","label":"Language and Rights","entries":[{"key":"dc:language.iso","label":"Language (ISO)","values":["en"]},{"key":"dc:rights","label":"Dc Rights","values":["In Copyright"]},{"key":"dc:rights.uri","label":"Rights URI","values":["http://rightsstatements.org/vocab/InC/1.0/"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier.uri","label":"Identifier URI","values":["http://hdl.handle.net/10919/104298"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description.abstract","label":"Abstract","values":["Five angle-ply laminates ([0₄₈], [(±10)₁₂]<sub>s</sub>, [(±20)₁₂]<sub>s</sub>, [(±30)₁₂]<sub>s</sub>, and [(±45)₁₂]<sub>s</sub> with central circular holes were tested under uniaxial compressive loading. The results from these tests show that the [(±45)₁₂]<sub>s</sub> laminate exhibited plastic deformation, with ultimate applied strains exceeding -1%. All other laminates failed in a brittle manner with ultimate strains of less than -0.5%. A three-dimensional finite element stress analysis was performed for the same laminates. A failure analysis based on the three-dimensional stress tensor polynomial predicted that failure will initiate at the intersection of the ply interface with hole edge for all laminates, and be due to a combination of the out-of-plane and in-plane shear stresses. Use of the state of stress directly on the hole edge in the prediction of laminate failure resulted in predictions of laminate ultimate strengths which were less than experimentally observed values by as much as a factor of ten. In addition, symmetry considerations for three-dimensional finite element modelling of composite laminates are discussed, and a two-dimensional finite element model based on shear-deformable plate theory is predicted."]},{"key":"dc:description.degree","label":"Dc Description Degree","values":["M.S."]},{"key":"dc:format.mimetype","label":"Dc Format Mimetype","values":["application/pdf"]},{"key":"dc:title","label":"Title","values":["Compressive failure of notched angle-ply composite laminates: three-dimensional finite element analysis and experiment"]}]}],"canonical_facts":{"dc:contributor.department":["Engineering Mechanics"],"dc:creator":["Burns, Stephen W."],"dc:date.accessioned":["2021-07-22T18:16:12Z"],"dc:date.available":["2021-07-22T18:16:12Z"],"dc:date.issued":["1985"],"dc:description.abstract":["Five angle-ply laminates ([0₄₈], [(±10)₁₂]<sub>s</sub>, [(±20)₁₂]<sub>s</sub>, [(±30)₁₂]<sub>s</sub>, and [(±45)₁₂]<sub>s</sub> with central circular holes were tested under uniaxial compressive loading. The results from these tests show that the [(±45)₁₂]<sub>s</sub> laminate exhibited plastic deformation, with ultimate applied strains exceeding -1%. All other laminates failed in a brittle manner with ultimate strains of less than -0.5%. A three-dimensional finite element stress analysis was performed for the same laminates. A failure analysis based on the three-dimensional stress tensor polynomial predicted that failure will initiate at the intersection of the ply interface with hole edge for all laminates, and be due to a combination of the out-of-plane and in-plane shear stresses. Use of the state of stress directly on the hole edge in the prediction of laminate failure resulted in predictions of laminate ultimate strengths which were less than experimentally observed values by as much as a factor of ten. In addition, symmetry considerations for three-dimensional finite element modelling of composite laminates are discussed, and a two-dimensional finite element model based on shear-deformable plate theory is predicted."],"dc:description.degree":["M.S."],"dc:format.mimetype":["application/pdf"],"dc:identifier.uri":["http://hdl.handle.net/10919/104298"],"dc:language.iso":["en"],"dc:publisher":["Virginia Polytechnic Institute and State University"],"dc:rights":["In Copyright"],"dc:rights.uri":["http://rightsstatements.org/vocab/InC/1.0/"],"dc:title":["Compressive failure of notched angle-ply composite laminates: three-dimensional finite element analysis and experiment"],"dc:type":["Thesis"],"dc:type.dcmitype":["Text"],"thesis:degree_discipline":["Engineering Mechanics"],"thesis:degree_level":["masters"],"thesis:degree_name":["M.S."],"thesis:institution_name":["Virginia Polytechnic Institute and State University"]},"updated_at":"2026-07-22T22:20:27Z"}