{"id":{"repo_id":"mit","oai_identifier":"oai:dspace.mit.edu:1721.1/85773"},"canonical_url":"https://search.dev.ndltd.org/etd/mit/oai:dspace.mit.edu:1721.1/85773","repository":{"repo_id":"mit","name":"MIT","base_url":"https://dspace.mit.edu/oai/request"},"display":{"title":"Design of a folding antenna-integrated micro UAV","abstract":"Micro-UAV devices can be used for a variety of purposes. This project is concerned with the design of such a device that will be used for high altitude antenna calibration. Such a UAV requires that an omni-directional antenna be integrated into the frame of the device to reduce signal interference. The device is to fold into a flare cartridge and withstand high deployment forces out of an aircraft. Design requirements include a rectangular working volume of 1.89\" X 2.44\" X 7.04\", a minimum additional payload of 70 g, hang time requirements, and antenna operating frequencies. A standard design process was used to develop a functional prototype. Several different concepts were developed, analyzed, and tested until a discone parachute device was chosen. An umbrella-like mechanism that utilized aerodynamic forces for deployment was developed for the ground plane. A functional demonstration prototype was built and tested to ensure the device's survivability and deployment functionality. The results of the test were successful and proved that the design is viable and can be further developed and optimized to improve performance.","abstract_html":"Micro-UAV devices can be used for a variety of purposes. This project is concerned with the design of such a device that will be used for high altitude antenna calibration. Such a UAV requires that an omni-directional antenna be integrated into the frame of the device to reduce signal interference. The device is to fold into a flare cartridge and withstand high deployment forces out of an aircraft. Design requirements include a rectangular working volume of 1.89" X 2.44" X 7.04", a minimum additional payload of 70 g, hang time requirements, and antenna operating frequencies. A standard design process was used to develop a functional prototype. Several different concepts were developed, analyzed, and tested until a discone parachute device was chosen. An umbrella-like mechanism that utilized aerodynamic forces for deployment was developed for the ground plane. A functional demonstration prototype was built and tested to ensure the device's survivability and deployment functionality. The results of the test were successful and proved that the design is viable and can be further developed and optimized to improve performance.","abstract_has_math":false,"creators":["Vu, My H"],"institution":"Massachusetts Institute of Technology","degree_name":null,"degree_level":null,"degree_discipline":null,"degree_department":"Massachusetts Institute of Technology. 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See provided URL for inquiries about permission."],"rights_urls":["http://dspace.mit.edu/handle/1721.1/7582"],"identifier_entries":[]},"links":{"outbound_url":"http://hdl.handle.net/1721.1/85773","outbound_label":"Handle","outbound_source":"dc:identifier.uri"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor.advisor","label":"Advisor","values":["David Wallace."]},{"key":"dc:contributor.department","label":"Department","values":["Massachusetts Institute of Technology. Department of Mechanical Engineering."]},{"key":"dc:contributor.other","label":"Dc Contributor Other","values":["Massachusetts Institute of Technology. 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Such a UAV requires that an omni-directional antenna be integrated into the frame of the device to reduce signal interference. The device is to fold into a flare cartridge and withstand high deployment forces out of an aircraft. Design requirements include a rectangular working volume of 1.89\" X 2.44\" X 7.04\", a minimum additional payload of 70 g, hang time requirements, and antenna operating frequencies. A standard design process was used to develop a functional prototype. Several different concepts were developed, analyzed, and tested until a discone parachute device was chosen. An umbrella-like mechanism that utilized aerodynamic forces for deployment was developed for the ground plane. A functional demonstration prototype was built and tested to ensure the device's survivability and deployment functionality. The results of the test were successful and proved that the design is viable and can be further developed and optimized to improve performance."]},{"key":"dc:description.degree","label":"Dc Description Degree","values":["S.M."]},{"key":"dc:title","label":"Title","values":["Design of a folding antenna-integrated micro UAV"]}]}],"canonical_facts":{"dc:contributor.advisor":["David Wallace."],"dc:contributor.department":["Massachusetts Institute of Technology. Department of Mechanical Engineering."],"dc:contributor.other":["Massachusetts Institute of Technology. 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Design requirements include a rectangular working volume of 1.89\" X 2.44\" X 7.04\", a minimum additional payload of 70 g, hang time requirements, and antenna operating frequencies. A standard design process was used to develop a functional prototype. Several different concepts were developed, analyzed, and tested until a discone parachute device was chosen. An umbrella-like mechanism that utilized aerodynamic forces for deployment was developed for the ground plane. A functional demonstration prototype was built and tested to ensure the device's survivability and deployment functionality. The results of the test were successful and proved that the design is viable and can be further developed and optimized to improve performance."],"dc:description.degree":["S.M."],"dc:identifier.uri":["http://hdl.handle.net/1721.1/85773"],"dc:language.iso":["eng"],"dc:publisher":["Massachusetts Institute of Technology"],"dc:rights":["M.I.T. theses are protected by copyright. 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