Please use this identifier to cite or link to this item: http://hdl.handle.net/10397/88249
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dc.contributorInterdisciplinary Division of Aeronautical and Aviation Engineeringen_US
dc.contributorDepartment of Mechanical Engineeringen_US
dc.creatorLi, Ben_US
dc.creatorSun, Jen_US
dc.creatorZhou, Wen_US
dc.creatorWen, Cen_US
dc.creatorLow, Ken_US
dc.creatorChen, Cen_US
dc.date.accessioned2020-10-08T02:59:50Z-
dc.date.available2020-10-08T02:59:50Z-
dc.identifier.issn1083-4435en_US
dc.identifier.urihttp://hdl.handle.net/10397/88249-
dc.language.isoenen_US
dc.publisherInstitute of Electrical and Electronics Engineersen_US
dc.rights© 2020 IEEE. Personal use of this material is permitted. Permission from IEEE must be obtained for all other uses, in any current or future media, including reprinting/republishing this material for advertising or promotional purposes, creating new collective works, for resale or redistribution to servers or lists, or reuse of any copyrighted component of this work in other works.en_US
dc.rightsThe following publication B. Li, J. Sun, W. Zhou, C. Wen, K. H. Low and C. Chen, "Transition Optimization for a VTOL Tail-sitter UAV," in IEEE/ASME Transactions on Mechatronics is available at https://dx.doi.org/10.1109/TMECH.2020.2983255en_US
dc.subjectTail-sitteren_US
dc.subjectUAVen_US
dc.subjectTransitionen_US
dc.subjectTrajectoryen_US
dc.subjectOpti-mizationen_US
dc.subjectFlight Experimentsen_US
dc.titleTransition optimization for a VTOL tail-sitter UAVen_US
dc.typeJournal/Magazine Articleen_US
dc.identifier.spage1en_US
dc.identifier.epage11en_US
dc.identifier.doi10.1109/TMECH.2020.2983255en_US
dcterms.abstractThis paper focuses on the transition process optimization for a vertical takeoff and landing (VTOL) tail-sitter unmanned aerial vehicle (UAV). For VTOL UAVs that can fly with either hover or cruise mode, transition refers to the intermediate phases between these two modes. This work develops a transition strategy with the trajectory optimization method. The strategy is a reference maneuver enabling the vehicle to perform transition efficiently by minimizing the cost of energy and maintaining a small change of altitude. The simplified 3-degree-of-freedom (3-DOF) longitudinal aerodynamic model is used as a dynamic constraint. The transition optimization problem is then modeled by nonlinear programming (NLP) and solved by the collocation method to obtain the reference trajectory of the pitch angle and throttle offline. Simulations with the Gazebo simulator and outdoor flight experiments are carried out with the optimized forward (hover-cruise) and backward (cruise-hover) transition solutions. The simulation and experimental results show that the optimized transition strategy enables the vehicle to finish transition with less time and change of altitude compared with that by using traditional linear transition methods.en_US
dcterms.accessRightsopen accessen_US
dcterms.bibliographicCitationIEEE/ASME transactions on mechatronics, 2020, p. 1-11 (Early Access)en_US
dcterms.isPartOfIEEE/ASME transactions on mechatronicsen_US
dcterms.issued2020-
dc.description.validate202010 bcrcen_US
dc.description.oaAccepted Manuscripten_US
dc.identifier.FolderNumbera0486-n02en_US
dc.description.pubStatusPublisheden_US
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