{"id":{"repo_id":"buffalo","oai_identifier":"oai:ubir.buffalo.edu:10477/83851"},"canonical_url":"https://search.dev.ndltd.org/etd/buffalo/oai:ubir.buffalo.edu:10477/83851","repository":{"repo_id":"buffalo","name":"Buffalo","base_url":"https://ubir.buffalo.edu/oai/request"},"display":{"title":"A Detailed Dynamic Damage Investigation of a Large Passenger Aircraft Fuselage Section Subject to Emergency Landing Requirements","abstract":"M.S.","abstract_html":"M.S.","abstract_has_math":false,"creators":["Megharaja, Suraj Jain"],"institution":"State University of New York at Buffalo","degree_name":null,"degree_level":null,"degree_discipline":null,"degree_department":null,"school":null,"contributors":["Bayandor, Javid","Mechanical and Aerospace Engineering"],"advisors":[],"committee_chairs":[],"committee_members":[],"year":2022,"date_issued":"2022-06-17T19:54:46Z","date_published":"2022-06-17T19:54:46Z","updated_at":"2026-07-27T19:05:28Z","subjects":["mechanical engineering"],"languages":["eng"],"rights":["Users of works found in University at Buffalo Institutional Repository (UBIR) are responsible for identifying and contacting the copyright owner for permission to reuse. University at Buffalo Libraries do not manage rights for copyright-protected works and cannot assist with permissions.","Copyright retained by author."],"rights_urls":[],"identifier_entries":[]},"links":{"outbound_url":"http://hdl.handle.net/10477/83851","outbound_label":"Handle","outbound_source":"dc:identifier"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor","label":"Contributor","values":["Bayandor, Javid","Mechanical and Aerospace Engineering"]},{"key":"dc:creator","label":"Author","values":["Megharaja, Suraj Jain"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date","label":"Dc Date","values":["2022-06-17T19:54:46Z","2020"]},{"key":"dc:publisher","label":"Institution","values":["State University of New York at Buffalo"]},{"key":"dc:type","label":"Dc Type","values":["Text","Thesis"]}]},{"id":"subjects_keywords","label":"Subjects and Keywords","entries":[{"key":"dc:subject","label":"Dc Subject","values":["mechanical engineering"]}]},{"id":"language_rights","label":"Language and Rights","entries":[{"key":"dc:language","label":"Dc Language","values":["eng"]},{"key":"dc:rights","label":"Dc Rights","values":["Users of works found in University at Buffalo Institutional Repository (UBIR) are responsible for identifying and contacting the copyright owner for permission to reuse. University at Buffalo Libraries do not manage rights for copyright-protected works and cannot assist with permissions.","Copyright retained by author."]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier","label":"Identifier","values":["http://hdl.handle.net/10477/83851"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description","label":"Description","values":["M.S.","Aircraft certification for different impact scenarios currently being used is an expensive and time-consuming process. Recent advancements in the field of numerical simulations have helped in achieving close co-relations with the experimental results for impact modeling, which in the future might subside the need for actual physical experiments for certifications. This research aims at evaluating the modeling techniques that can effectively be used for performing drop tests through simulations. In order to establish the study, preliminary studies are performed on small scale models to validate the technique being used for fuselage section drop tests. Following this, a model of a B-737-200 fuselage is developed to perform a drop test on hard-terrain. An experiment on the same fuselage model was conducted by NASA in 2001, and this research aims at validating the acceleration experienced on the passenger floor in experimental results through numerical simulations. This research also investigates the different techniques to develop an FE model of the fuselage and their ability to capture the response accurately. After having validated the results against the experiment, a more detailed model is developed by incorporating water into the fuel tank of the fuselage and variations seen in the results are noted. Followed by this, similar drop tests are performed on water and soil mediums and are compared against the results from a hard-terrain impact. The combination of the above-mentioned studies provides a detailed overview and modeling ideas for performing drop tests that could potentially be used for aircraft certification.","**To request an accessible version of the file(s) associated with this item, contact library@buffalo.edu. Please include the item's persistent URL [http://hdl.handle.net/. . .] in your request.**"]},{"key":"dc:format","label":"Dc Format","values":["application/pdf"]},{"key":"dc:title","label":"Title","values":["A Detailed Dynamic Damage Investigation of a Large Passenger Aircraft Fuselage Section Subject to Emergency Landing Requirements"]}]}],"canonical_facts":{"dc:contributor":["Bayandor, Javid","Mechanical and Aerospace Engineering"],"dc:creator":["Megharaja, Suraj Jain"],"dc:date":["2022-06-17T19:54:46Z","2020"],"dc:description":["M.S.","Aircraft certification for different impact scenarios currently being used is an expensive and time-consuming process. Recent advancements in the field of numerical simulations have helped in achieving close co-relations with the experimental results for impact modeling, which in the future might subside the need for actual physical experiments for certifications. This research aims at evaluating the modeling techniques that can effectively be used for performing drop tests through simulations. In order to establish the study, preliminary studies are performed on small scale models to validate the technique being used for fuselage section drop tests. Following this, a model of a B-737-200 fuselage is developed to perform a drop test on hard-terrain. An experiment on the same fuselage model was conducted by NASA in 2001, and this research aims at validating the acceleration experienced on the passenger floor in experimental results through numerical simulations. This research also investigates the different techniques to develop an FE model of the fuselage and their ability to capture the response accurately. After having validated the results against the experiment, a more detailed model is developed by incorporating water into the fuel tank of the fuselage and variations seen in the results are noted. Followed by this, similar drop tests are performed on water and soil mediums and are compared against the results from a hard-terrain impact. The combination of the above-mentioned studies provides a detailed overview and modeling ideas for performing drop tests that could potentially be used for aircraft certification.","**To request an accessible version of the file(s) associated with this item, contact library@buffalo.edu. Please include the item's persistent URL [http://hdl.handle.net/. . .] in your request.**"],"dc:format":["application/pdf"],"dc:identifier":["http://hdl.handle.net/10477/83851"],"dc:language":["eng"],"dc:publisher":["State University of New York at Buffalo"],"dc:rights":["Users of works found in University at Buffalo Institutional Repository (UBIR) are responsible for identifying and contacting the copyright owner for permission to reuse. University at Buffalo Libraries do not manage rights for copyright-protected works and cannot assist with permissions.","Copyright retained by author."],"dc:subject":["mechanical engineering"],"dc:title":["A Detailed Dynamic Damage Investigation of a Large Passenger Aircraft Fuselage Section Subject to Emergency Landing Requirements"],"dc:type":["Text","Thesis"]},"updated_at":"2026-07-27T19:05:28Z"}