{"id":{"repo_id":"wvu","oai_identifier":"oai:researchrepository.wvu.edu:etd-1985"},"canonical_url":"https://search.dev.ndltd.org/etd/wvu/oai:researchrepository.wvu.edu:etd-1985","repository":{"repo_id":"wvu","name":"West Virginia University","base_url":"https://researchrepository.wvu.edu/do/oai/"},"display":{"title":"Compressive strength prediction for composite unmanned aerial vehicles","abstract":"A rational methodology is presented to predict the compressive strength of carbon/epoxy compression specimens and prototype production parts using the model presented by Barbero in the Journal of Composite Materials, Vol. 32, No.5/1998. The experimental technique is an adaptation of the optical method first proposed by Yurgartis (1987) and can be directly applied to actual development, quality control or failure investigation programs. There is very good agreement between actual and predicted compressive strength at -125F and room temperature. At 180F, the predicted strength is conservative. Aurora Flight Sciences provided the prototype production parts and partial funding under the \"Material Characterization Study for UAV Wing Development\" contract. The results of the material characterization study of two carbon/epoxy prepregs presented to Aurora Flight Sciences are also shown here. An extension of the method presented by Barbero is also proposed for laminates with average global misalignment alphaG, in [+alphaG]n or [-alpha G]n stacking sequence.","abstract_html":"A rational methodology is presented to predict the compressive strength of carbon/epoxy compression specimens and prototype production parts using the model presented by Barbero in the Journal of Composite Materials, Vol. 32, No.5/1998. The experimental technique is an adaptation of the optical method first proposed by Yurgartis (1987) and can be directly applied to actual development, quality control or failure investigation programs. There is very good agreement between actual and predicted compressive strength at -125F and room temperature. At 180F, the predicted strength is conservative. Aurora Flight Sciences provided the prototype production parts and partial funding under the "Material Characterization Study for UAV Wing Development" contract. The results of the material characterization study of two carbon/epoxy prepregs presented to Aurora Flight Sciences are also shown here. An extension of the method presented by Barbero is also proposed for laminates with average global misalignment alphaG, in [+alphaG]n or [-alpha G]n stacking sequence.","abstract_has_math":false,"creators":["Wen, Edward Albert"],"institution":null,"degree_name":"MS","degree_level":"Thesis","degree_discipline":"Mechanical and Aerospace Engineering","degree_department":null,"school":null,"contributors":["Ever Barbero."],"advisors":[],"committee_chairs":[],"committee_members":[],"year":1999,"date_issued":"1999-08-01T07:00:00Z","date_published":"1999-08-01T07:00:00Z","updated_at":"2026-07-24T06:15:08Z","subjects":["Aerospace engineering","Mechanical engineering","Materials science"],"languages":[],"rights":[],"rights_urls":[],"identifier_entries":[{"key":"dc:identifier","label":"Identifier","values":["https://researchrepository.wvu.edu/etd/982"],"render_values":[{"text":"https://researchrepository.wvu.edu/etd/982","href":"https://researchrepository.wvu.edu/etd/982","code":true}]}]},"links":{"outbound_url":"https://doi.org/10.33915/etd.982","outbound_label":"DOI","outbound_source":"dc:identifier"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor","label":"Contributor","values":["Ever Barbero."]},{"key":"dc:creator","label":"Author","values":["Wen, Edward Albert"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date.available","label":"Dc Date Available","values":["2019-01-17T08:00:00Z"]},{"key":"thesis:degree_discipline","label":"Discipline","values":["Mechanical and Aerospace Engineering"]},{"key":"thesis:degree_level","label":"Degree Level","values":["Thesis"]},{"key":"thesis:degree_name","label":"Degree Name","values":["MS"]}]},{"id":"subjects_keywords","label":"Subjects and Keywords","entries":[{"key":"dc:subject","label":"Dc Subject","values":["Aerospace engineering","Mechanical engineering","Materials science"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier","label":"Identifier","values":["https://doi.org/10.33915/etd.982","https://researchrepository.wvu.edu/etd/982"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description.abstract","label":"Abstract","values":["A rational methodology is presented to predict the compressive strength of carbon/epoxy compression specimens and prototype production parts using the model presented by Barbero in the Journal of Composite Materials, Vol. 32, No.5/1998. The experimental technique is an adaptation of the optical method first proposed by Yurgartis (1987) and can be directly applied to actual development, quality control or failure investigation programs. There is very good agreement between actual and predicted compressive strength at -125F and room temperature. At 180F, the predicted strength is conservative. Aurora Flight Sciences provided the prototype production parts and partial funding under the \"Material Characterization Study for UAV Wing Development\" contract. The results of the material characterization study of two carbon/epoxy prepregs presented to Aurora Flight Sciences are also shown here. An extension of the method presented by Barbero is also proposed for laminates with average global misalignment alphaG, in [+alphaG]n or [-alpha G]n stacking sequence."]},{"key":"dc:title","label":"Title","values":["Compressive strength prediction for composite unmanned aerial vehicles"]}]}],"canonical_facts":{"dc:contributor":["Ever Barbero."],"dc:creator":["Wen, Edward Albert"],"dc:date.available":["2019-01-17T08:00:00Z"],"dc:description.abstract":["A rational methodology is presented to predict the compressive strength of carbon/epoxy compression specimens and prototype production parts using the model presented by Barbero in the Journal of Composite Materials, Vol. 32, No.5/1998. The experimental technique is an adaptation of the optical method first proposed by Yurgartis (1987) and can be directly applied to actual development, quality control or failure investigation programs. There is very good agreement between actual and predicted compressive strength at -125F and room temperature. At 180F, the predicted strength is conservative. Aurora Flight Sciences provided the prototype production parts and partial funding under the \"Material Characterization Study for UAV Wing Development\" contract. The results of the material characterization study of two carbon/epoxy prepregs presented to Aurora Flight Sciences are also shown here. An extension of the method presented by Barbero is also proposed for laminates with average global misalignment alphaG, in [+alphaG]n or [-alpha G]n stacking sequence."],"dc:identifier":["https://doi.org/10.33915/etd.982","https://researchrepository.wvu.edu/etd/982"],"dc:subject":["Aerospace engineering","Mechanical engineering","Materials science"],"dc:title":["Compressive strength prediction for composite unmanned aerial vehicles"],"thesis:degree_discipline":["Mechanical and Aerospace Engineering"],"thesis:degree_level":["Thesis"],"thesis:degree_name":["MS"]},"updated_at":"2026-07-24T06:15:08Z"}