{"id":{"repo_id":"uiuc","oai_identifier":"oai:www.ideals.illinois.edu:2142/104730"},"canonical_url":"https://search.dev.ndltd.org/etd/uiuc/oai:www.ideals.illinois.edu:2142/104730","repository":{"repo_id":"uiuc","name":"University of Illinois - Urbana-Champaign","base_url":"https://www.ideals.illinois.edu/oai-pmh"},"display":{"title":"Development of UAV flight test demonstrator for cyclotronic arc-plasma actuator","abstract":"Through a collaborative research effort between the University of Illinois and CU Aerospace through a small business innovation research (SBIR) program, a novel flow control device known as the Cyclotronic Arc-Plasma Actuator (CAPA) actuator is being developed. This actuator uses a series of magnets and electrodes to produces a sweeping plasma arc that can induce a swirling component on a flow. One potential application of this technology is for active flow control, as this technology can potentially be used to delay separation on an airfoil and increase the effectiveness of a control surface. These actuators can be used in a role similar to vortex generators, though with the additional ability of being enabled or disabled for flight regimes such as takeoff and landing. As disabling these actuators during cruise can reduce or eliminate drag penalties, these devices could be used as alternatives to passive vortex generators, which cannot be disabled in flight. This thesis details the work taken to develop an unmanned aerial vehicle (UAV) that will be used as technology demonstrator for the CAPA actuators developed for the SBIR. As part of the integration effort, this thesis will also cover the steps needed to integrate the CAPA system inside a UAV and to evaluate the performance of the system through flight testing.","abstract_html":"Through a collaborative research effort between the University of Illinois and CU Aerospace through a small business innovation research (SBIR) program, a novel flow control device known as the Cyclotronic Arc-Plasma Actuator (CAPA) actuator is being developed. This actuator uses a series of magnets and electrodes to produces a sweeping plasma arc that can induce a swirling component on a flow. One potential application of this technology is for active flow control, as this technology can potentially be used to delay separation on an airfoil and increase the effectiveness of a control surface. These actuators can be used in a role similar to vortex generators, though with the additional ability of being enabled or disabled for flight regimes such as takeoff and landing. As disabling these actuators during cruise can reduce or eliminate drag penalties, these devices could be used as alternatives to passive vortex generators, which cannot be disabled in flight. This thesis details the work taken to develop an unmanned aerial vehicle (UAV) that will be used as technology demonstrator for the CAPA actuators developed for the SBIR. As part of the integration effort, this thesis will also cover the steps needed to integrate the CAPA system inside a UAV and to evaluate the performance of the system through flight testing.","abstract_has_math":false,"creators":["Vahora, Moiz"],"institution":"University of Illinois at Urbana-Champaign","degree_name":"M.S.","degree_level":"Thesis","degree_discipline":"Aerospace Engineering","degree_department":null,"school":null,"contributors":["Ansell, Phillip J."],"advisors":[],"committee_chairs":[],"committee_members":[],"year":2019,"date_issued":"2019-08-23T19:51:21Z","date_published":"2019-08-23T19:51:21Z","updated_at":"2026-07-22T22:24:42Z","subjects":["Flight Testing","Plasma Flow Control","UAV","UAS"],"languages":["en"],"rights":["Copyright 2018 Moiz Vahora"],"rights_urls":[],"identifier_entries":[]},"links":{"outbound_url":"http://hdl.handle.net/2142/104730","outbound_label":"Handle","outbound_source":"dc:identifier"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor","label":"Contributor","values":["Ansell, Phillip J."]},{"key":"dc:creator","label":"Author","values":["Vahora, Moiz"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date","label":"Dc Date","values":["2019-08-23T19:51:21Z","2021-08-29T09:15:17Z","2018-12-13","2019-05"]},{"key":"dc:type","label":"Dc Type","values":["text"]},{"key":"thesis:degree_discipline","label":"Discipline","values":["Aerospace Engineering"]},{"key":"thesis:degree_level","label":"Degree Level","values":["Thesis"]},{"key":"thesis:degree_name","label":"Degree Name","values":["M.S."]},{"key":"thesis:institution_name","label":"Thesis Institution Name","values":["University of Illinois at Urbana-Champaign"]}]},{"id":"subjects_keywords","label":"Subjects and Keywords","entries":[{"key":"dc:subject","label":"Dc Subject","values":["Flight Testing","Plasma Flow Control","UAV","UAS"]}]},{"id":"language_rights","label":"Language and Rights","entries":[{"key":"dc:language","label":"Dc Language","values":["en"]},{"key":"dc:rights","label":"Dc Rights","values":["Copyright 2018 Moiz Vahora"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier","label":"Identifier","values":["http://hdl.handle.net/2142/104730"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description","label":"Description","values":["Through a collaborative research effort between the University of Illinois and CU Aerospace through a small business innovation research (SBIR) program, a novel flow control device known as the Cyclotronic Arc-Plasma Actuator (CAPA) actuator is being developed. This actuator uses a series of magnets and electrodes to produces a sweeping plasma arc that can induce a swirling component on a flow. One potential application of this technology is for active flow control, as this technology can potentially be used to delay separation on an airfoil and increase the effectiveness of a control surface. These actuators can be used in a role similar to vortex generators, though with the additional ability of being enabled or disabled for flight regimes such as takeoff and landing. As disabling these actuators during cruise can reduce or eliminate drag penalties, these devices could be used as alternatives to passive vortex generators, which cannot be disabled in flight. This thesis details the work taken to develop an unmanned aerial vehicle (UAV) that will be used as technology demonstrator for the CAPA actuators developed for the SBIR. As part of the integration effort, this thesis will also cover the steps needed to integrate the CAPA system inside a UAV and to evaluate the performance of the system through flight testing.","Submission original under an indefinite embargo labeled 'Open Access'. The submission was exported from vireo on 2019-08-22 without embargo terms","The student, Moiz Vahora, accepted the attached license on 2018-12-13 at 13:30.","The student, Moiz Vahora, submitted this Thesis for approval on 2018-12-13 at 13:35.","This Thesis was approved for publication on 2018-12-13 at 15:23.","DSpace SAF Submission Ingestion Package generated from Vireo submission #13317 on 2019-08-22 at 14:38:42","Made available in DSpace on 2019-08-23T19:51:21Z (GMT). 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This actuator uses a series of magnets and electrodes to produces a sweeping plasma arc that can induce a swirling component on a flow. One potential application of this technology is for active flow control, as this technology can potentially be used to delay separation on an airfoil and increase the effectiveness of a control surface. These actuators can be used in a role similar to vortex generators, though with the additional ability of being enabled or disabled for flight regimes such as takeoff and landing. As disabling these actuators during cruise can reduce or eliminate drag penalties, these devices could be used as alternatives to passive vortex generators, which cannot be disabled in flight. This thesis details the work taken to develop an unmanned aerial vehicle (UAV) that will be used as technology demonstrator for the CAPA actuators developed for the SBIR. As part of the integration effort, this thesis will also cover the steps needed to integrate the CAPA system inside a UAV and to evaluate the performance of the system through flight testing.","Submission original under an indefinite embargo labeled 'Open Access'. The submission was exported from vireo on 2019-08-22 without embargo terms","The student, Moiz Vahora, accepted the attached license on 2018-12-13 at 13:30.","The student, Moiz Vahora, submitted this Thesis for approval on 2018-12-13 at 13:35.","This Thesis was approved for publication on 2018-12-13 at 15:23.","DSpace SAF Submission Ingestion Package generated from Vireo submission #13317 on 2019-08-22 at 14:38:42","Made available in DSpace on 2019-08-23T19:51:21Z (GMT). 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