Show simple item record

dc.contributor.advisorSteven Barrett.en_US
dc.contributor.authorHennick, Cooper Curtisen_US
dc.contributor.otherMassachusetts Institute of Technology. Department of Aeronautics and Astronautics.en_US
dc.date.accessioned2018-02-16T20:04:11Z
dc.date.available2018-02-16T20:04:11Z
dc.date.copyright2017en_US
dc.date.issued2017en_US
dc.identifier.urihttp://hdl.handle.net/1721.1/113747
dc.descriptionThesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2017.en_US
dc.descriptionCataloged from PDF version of thesis.en_US
dc.descriptionIncludes bibliographical references (pages 73-75).en_US
dc.description.abstractElectroaerodynamic (EAD) propulsion is a form of in-atmosphere electric thrust generation with no direct emissions, no moving parts, and is nearly silent. Previous work has quantified the thrust-to-power and thrust density of EAD propulsion. An unmanned aerial vehicle (UAV) was designed with the optimization tool GPkit and with the flight mission goal of steady-level flight. This thesis describes the design and testing of several subsystems of the UAV, including the power system, the communication system, the aircraft tail, and the aircraft launching system. The power system is tested to deliver up to a maximum of 600 W at 40 kV. A system to collect flight data is also designed, based on a video camera and Kalman filter that measures the horizontal and vertical velocities of the aircraft throughout a flight. Seven powered, indoor flight tests on the order of 5 s are performed at a voltage level of 36.2 kV, 2.44 N of thrust, a thrust-to-power ratio of 7.2 N/kW and an average lift-to-drag ratio of 10.0. The average specific excess power (SEP) of the aircraft measured from the seven flight tests is -0.053 m/s.en_US
dc.description.statementofresponsibilityby Cooper Curtis Hennick.en_US
dc.format.extent75 pagesen_US
dc.language.isoengen_US
dc.publisherMassachusetts Institute of Technologyen_US
dc.rightsMIT theses are protected by copyright. They may be viewed, downloaded, or printed from this source but further reproduction or distribution in any format is prohibited without written permission.en_US
dc.rights.urihttp://dspace.mit.edu/handle/1721.1/7582en_US
dc.subjectAeronautics and Astronautics.en_US
dc.titleSubsystem development and flight testing of an electroaerodynamic UAVen_US
dc.typeThesisen_US
dc.description.degreeS.M.en_US
dc.contributor.departmentMassachusetts Institute of Technology. Department of Aeronautics and Astronautics.en_US
dc.identifier.oclc1021853687en_US


Files in this item

Thumbnail

This item appears in the following Collection(s)

Show simple item record