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Development of a Forced Oscillation Test Technique for Determination of MAV Stability Characteristics

dc.contributor.advisorPines, Darryllen_US
dc.contributor.authorEverson, Daniel Peteren_US
dc.date.accessioned2006-02-04T07:49:00Z
dc.date.available2006-02-04T07:49:00Z
dc.date.issued2005-12-08en_US
dc.identifier.urihttp://hdl.handle.net/1903/3236
dc.description.abstractThis thesis presents the development and validation of a forced oscillation test technique for the determination of Micro Air Vehicle (MAV) stability characteristics. The test setup utilizes a scotch yoke mechanism to oscillate a MAV along a single axis at a fixed amplitude and frequency. The aerodynamic reaction forces to this sinusoidal perturbation are measured and converted into meaningful stability parameters. The purpose of this research is to demonstrate that forced oscillation testing is an effective means of measuring the stability parameters of a MAV. Initial tests show that the forced oscillation test process is returning results which match the expected trends. Comparison of the results to an analytical model of blade flapping shows that the experimental results are of the proper magnitude. It can be concluded from this research that forced oscillation testing is a feasible method for determining the stability parameters of MAVs.en_US
dc.format.extent1383622 bytes
dc.format.mimetypeapplication/pdf
dc.language.isoen_US
dc.titleDevelopment of a Forced Oscillation Test Technique for Determination of MAV Stability Characteristicsen_US
dc.typeThesisen_US
dc.contributor.publisherDigital Repository at the University of Marylanden_US
dc.contributor.publisherUniversity of Maryland (College Park, Md.)en_US
dc.contributor.departmentAerospace Engineeringen_US
dc.subject.pqcontrolledEngineering, Aerospaceen_US
dc.subject.pquncontrolledMAVen_US
dc.subject.pquncontrolledForced Oscillationen_US
dc.subject.pquncontrolledSystem Identificationen_US
dc.subject.pquncontrolledStability Testingen_US


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