Show simple item record

Flight Dynamics Simulation Modeling and Control of a Large Flexible Tiltrotor Aircraft

dc.contributor.advisorCeli, Robertoen_US
dc.contributor.authorJuhasz, Ondrejen_US
dc.date.accessioned2014-06-26T05:37:36Z
dc.date.available2014-06-26T05:37:36Z
dc.date.issued2014en_US
dc.identifier.urihttp://hdl.handle.net/1903/15460
dc.description.abstractA high order rotorcraft mathematical model is developed and validated against the XV-15 and a Large Civil Tiltrotor (LCTR) concept. The mathematical model is generic and allows for any rotorcraft configuration, from single main rotor helicopters to coaxial and tiltrotor aircraft. Rigid-body and inflow states, as well as flexible wing and blade states are used in the analysis. The separate modeling of each rotorcraft component allows for structural flexibility to be included, which is important when modeling large aircraft where structural modes affect the flight dynamics frequency ranges of interest, generally 1 to 20 rad/sec. Details of the formulation of the mathematical model are given, including derivations of structural, aerodynamic, and inertial loads. The linking of the components of the aircraft is developed using an approach similar to multibody analyses by exploiting a tree topology, but without equations of constraints. Assessments of the effects of wing flexibility are given. Flexibility effects are evaluated by looking at the nature of the couplings between rigid-body modes and wing structural modes and vice versa. The effects of various different forms of structural feedback on aircraft dynamics are analyzed. A proportional-integral feedback on the structural acceleration is deemed to be most effective at both improving the damping and reducing the overall excitation of a structural mode. A model following control architecture is then implemented on full order flexible LCTR models. For this aircraft, the four lowest frequency structural modes are below 20 rad/sec, and are thus needed for control law development and analysis. The impact of structural feedback on both Attitude-Command, Attitude-Hold (ACAH) and Translational Rate Command (TRC) response types are investigated. A rigid aircraft model has optimistic performance characteristics, and a control system designed for a rigid aircraft could potentially destabilize a flexible one. The various control systems are flown in a fixed-base simulator. Pilot inputs and aircraft performance are recorded and analyzed.en_US
dc.language.isoenen_US
dc.titleFlight Dynamics Simulation Modeling and Control of a Large Flexible Tiltrotor Aircraften_US
dc.typeDissertationen_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.pquncontrolledcontrolen_US
dc.subject.pquncontrolleddynamicsen_US
dc.subject.pquncontrolledflexibleen_US
dc.subject.pquncontrolledmulti-bodyen_US
dc.subject.pquncontrolledsimulationen_US
dc.subject.pquncontrolledtiltrotoren_US


Files in this item

Thumbnail

This item appears in the following Collection(s)

Show simple item record