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dc.contributor.advisorSteven R. Hall.en_US
dc.contributor.authorPatterson, Byron Wainen_US
dc.contributor.otherMassachusetts Institute of Technology. Department of Aeronautics and Astronautics.en_US
dc.date.accessioned2016-12-05T19:10:47Z
dc.date.available2016-12-05T19:10:47Z
dc.date.copyright2016en_US
dc.date.issued2016en_US
dc.identifier.urihttp://hdl.handle.net/1721.1/105564
dc.descriptionThesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2016.en_US
dc.descriptionThis electronic version was submitted by the student author. The certified thesis is available in the Institute Archives and Special Collections.en_US
dc.descriptionCataloged from student-submitted PDF version of thesis.en_US
dc.descriptionIncludes bibliographical references (pages 155-159).en_US
dc.description.abstractVibration in helicopters can have a significant impact on their utility, maintenance, weight, performance, and cost of operation. This thesis focuses on the design of a vibration reduction controller that is effective throughout the flight envelope of the helicopter, in spite of variations in vibration levels and dynamics with flight condition. Analysis of a UH-60 Black Hawk helicopter modeled in the Rotorcraft Comprehensive Analysis System (RCAS) aeromechanical simulation environment indicates that the steady state vibration levels and the helicopter dynamics depend primarily on the advance ratio. Two baseline vibration controllers are developed, specifically the Continuous Time Higher Harmonic Controller (CTHHC) and an H[subscript of infinity] based controller, over a range of advance ratios. The unique controller developed in this thesis uses the Linear Parameter Varying (LPV) synthesis method, which provides performance and stability guarantees over the advance ratio parameter space. The three controllers are evaluated in the RCAS environment at fixed and maneuvering flight conditions. The results indicate that the full envelope controller designed using the LPV method exhibits increased performance over the CTHHC and H[subscript of infinity] controllers.en_US
dc.description.statementofresponsibilityby Byron Wain Patterson.en_US
dc.format.extent159 pagesen_US
dc.language.isoengen_US
dc.publisherMassachusetts Institute of Technologyen_US
dc.rightsM.I.T. theses are protected by copyright. They may be viewed from this source for any purpose, but reproduction or distribution in any format is prohibited without written permission. See provided URL for inquiries about permission.en_US
dc.rights.urihttp://dspace.mit.edu/handle/1721.1/7582en_US
dc.subjectAeronautics and Astronautics.en_US
dc.titleA linear parameter varying control methodology for reduction of helicopter higher harmonic vibrationen_US
dc.typeThesisen_US
dc.description.degreeS.M.en_US
dc.contributor.departmentMassachusetts Institute of Technology. Department of Aeronautics and Astronautics
dc.identifier.oclc962735855en_US


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