{"id":{"repo_id":"vt","oai_identifier":"oai:vtechworks.lib.vt.edu:10919/43002"},"canonical_url":"https://search.dev.ndltd.org/etd/vt/oai:vtechworks.lib.vt.edu:10919/43002","repository":{"repo_id":"vt","name":"Virginia Tech","base_url":"https://vtechworks.lib.vt.edu/oai/request"},"display":{"title":"Analysis and design of composite curved frames","abstract":"In this work, methods for rapid analysis and design of composite curved C-section frames subjected to axial tensile loading are developed. Failure is predicted using polynomial in-plane and interlaminar failure criteria. Interlaminar stresses can be directly computed only from three-dimensional finite element models, but the computational expense of these models is prohibitive. Therefore, approximate two-dimensional analysis methods are used here to predict interlaminar stresses in the curved corner regions between the web and flanges and at the free edges of the flanges. A response surface design approach is used to approximate the failure response using a minimum number of finite element analyses. Large degree of freedom 2D/3D global/local finite element models are selectively used in conjunction with the smaller 2D shell element models in the design process to improve the response surface polynomials. This combined use of simple and complex analyses is known as variable complexity modeling. Two design case studies are conducted, one with two design variables and one with five design variables. Three different objective function formulations are used in the two design variable case, minimum weight, maximum strength, and combined minimum weight and maximum strength. Only the minimum weight formulation is used in the five design variable case due to the complexity of the design space. The design studies demonstrate the accuracy and efficiency of the proposed approach.","abstract_html":"In this work, methods for rapid analysis and design of composite curved C-section frames subjected to axial tensile loading are developed. Failure is predicted using polynomial in-plane and interlaminar failure criteria. Interlaminar stresses can be directly computed only from three-dimensional finite element models, but the computational expense of these models is prohibitive. Therefore, approximate two-dimensional analysis methods are used here to predict interlaminar stresses in the curved corner regions between the web and flanges and at the free edges of the flanges. A response surface design approach is used to approximate the failure response using a minimum number of finite element analyses. Large degree of freedom 2D/3D global/local finite element models are selectively used in conjunction with the smaller 2D shell element models in the design process to improve the response surface polynomials. This combined use of simple and complex analyses is known as variable complexity modeling. Two design case studies are conducted, one with two design variables and one with five design variables. Three different objective function formulations are used in the two design variable case, minimum weight, maximum strength, and combined minimum weight and maximum strength. Only the minimum weight formulation is used in the five design variable case due to the complexity of the design space. The design studies demonstrate the accuracy and efficiency of the proposed approach.","abstract_has_math":false,"creators":["Mason, Brian H."],"institution":"Virginia Tech","degree_name":"Master of Science","degree_level":"masters","degree_discipline":"Aerospace Engineering","degree_department":"Aerospace Engineering","school":null,"contributors":[],"advisors":[],"committee_chairs":[],"committee_members":[],"year":1994,"date_issued":"1994","date_published":"1994","updated_at":"2026-07-22T22:19:59Z","subjects":[],"languages":["en"],"rights":["In Copyright"],"rights_urls":["http://rightsstatements.org/vocab/InC/1.0/"],"identifier_entries":[{"key":"dc:identifier.other","label":"Dc Identifier Other","values":["etd-06102009-063304"],"render_values":[{"text":"etd-06102009-063304","href":null,"code":true}]}]},"links":{"outbound_url":"http://hdl.handle.net/10919/43002","outbound_label":"Handle","outbound_source":"dc:identifier.uri"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor.department","label":"Department","values":["Aerospace Engineering"]},{"key":"dc:creator","label":"Author","values":["Mason, Brian H."]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date.accessioned","label":"Dc Date Accessioned","values":["2014-03-14T21:37:27Z"]},{"key":"dc:date.available","label":"Dc Date Available","values":["2014-03-14T21:37:27Z","2009-06-10"]},{"key":"dc:date.issued","label":"Date","values":["1994"]},{"key":"dc:publisher","label":"Institution","values":["Virginia Tech"]},{"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":["Aerospace Engineering"]},{"key":"thesis:degree_level","label":"Degree Level","values":["masters"]},{"key":"thesis:degree_name","label":"Degree Name","values":["Master of Science"]},{"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.other","label":"Dc Identifier Other","values":["etd-06102009-063304"]},{"key":"dc:identifier.uri","label":"Identifier URI","values":["http://hdl.handle.net/10919/43002"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description.abstract","label":"Abstract","values":["In this work, methods for rapid analysis and design of composite curved C-section frames subjected to axial tensile loading are developed. Failure is predicted using polynomial in-plane and interlaminar failure criteria. Interlaminar stresses can be directly computed only from three-dimensional finite element models, but the computational expense of these models is prohibitive. Therefore, approximate two-dimensional analysis methods are used here to predict interlaminar stresses in the curved corner regions between the web and flanges and at the free edges of the flanges. A response surface design approach is used to approximate the failure response using a minimum number of finite element analyses. Large degree of freedom 2D/3D global/local finite element models are selectively used in conjunction with the smaller 2D shell element models in the design process to improve the response surface polynomials. This combined use of simple and complex analyses is known as variable complexity modeling. Two design case studies are conducted, one with two design variables and one with five design variables. Three different objective function formulations are used in the two design variable case, minimum weight, maximum strength, and combined minimum weight and maximum strength. Only the minimum weight formulation is used in the five design variable case due to the complexity of the design space. The design studies demonstrate the accuracy and efficiency of the proposed approach."]},{"key":"dc:description.degree","label":"Dc Description Degree","values":["Master of Science"]},{"key":"dc:format.medium","label":"Dc Format Medium","values":["BTD"]},{"key":"dc:format.mimetype","label":"Dc Format Mimetype","values":["application/pdf"]},{"key":"dc:title","label":"Title","values":["Analysis and design of composite curved frames"]}]}],"canonical_facts":{"dc:contributor.department":["Aerospace Engineering"],"dc:creator":["Mason, Brian H."],"dc:date.accessioned":["2014-03-14T21:37:27Z"],"dc:date.available":["2014-03-14T21:37:27Z","2009-06-10"],"dc:date.issued":["1994"],"dc:description.abstract":["In this work, methods for rapid analysis and design of composite curved C-section frames subjected to axial tensile loading are developed. Failure is predicted using polynomial in-plane and interlaminar failure criteria. Interlaminar stresses can be directly computed only from three-dimensional finite element models, but the computational expense of these models is prohibitive. Therefore, approximate two-dimensional analysis methods are used here to predict interlaminar stresses in the curved corner regions between the web and flanges and at the free edges of the flanges. A response surface design approach is used to approximate the failure response using a minimum number of finite element analyses. Large degree of freedom 2D/3D global/local finite element models are selectively used in conjunction with the smaller 2D shell element models in the design process to improve the response surface polynomials. This combined use of simple and complex analyses is known as variable complexity modeling. Two design case studies are conducted, one with two design variables and one with five design variables. 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