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dc.contributor.advisorCeli, Robertroen_US
dc.contributor.authorNelson, Hunter Bartonen_US
dc.date.accessioned2016-02-09T06:37:11Z
dc.date.available2016-02-09T06:37:11Z
dc.date.issued2015en_US
dc.identifierhttps://doi.org/10.13016/M2672P
dc.identifier.urihttp://hdl.handle.net/1903/17391
dc.description.abstractA simplified second-order transfer function actuator model used in most flight dynamics applications cannot easily capture the effects of different actuator parameters. The present work integrates a nonlinear actuator model into a nonlinear state space rotorcraft model to determine the effect of actuator parameters on key flight dynamics. The completed actuator model was integrated with a swashplate kinematics where step responses were generated over a range of key hydraulic parameters. The actuator-swashplate system was then introduced into a nonlinear state space rotorcraft simulation where flight dynamics quantities such as bandwidth and phase delay analyzed. Frequency sweeps were simulated for unique actuator configurations using the coupled nonlinear actuator-rotorcraft system. The software package CIFER was used for system identification and compared directly to the linearized models. As the actuator became rate saturated, the effects on bandwidth and phase delay were apparent on the predicted handling qualities specifications.en_US
dc.language.isoenen_US
dc.titleAnalysis of Helicopter Flight Dynamics through Modeling and Simulation of Primary Flight Control Actuation Systemen_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.pqcontrolledAerospace engineeringen_US
dc.subject.pquncontrolledActuatoren_US
dc.subject.pquncontrolledDynamicsen_US
dc.subject.pquncontrolledFlight Controlsen_US
dc.subject.pquncontrolledHelicopteren_US


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