Flight Dynamics Simulation Modeling and Control of a Large Flexible Tiltrotor Aircraft
| dc.contributor.advisor | Celi, Roberto | en_US |
| dc.contributor.author | Juhasz, Ondrej | en_US |
| dc.contributor.department | Aerospace Engineering | en_US |
| dc.contributor.publisher | Digital Repository at the University of Maryland | en_US |
| dc.contributor.publisher | University of Maryland (College Park, Md.) | en_US |
| dc.date.accessioned | 2014-06-26T05:37:36Z | |
| dc.date.available | 2014-06-26T05:37:36Z | |
| dc.date.issued | 2014 | en_US |
| dc.description.abstract | A 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.identifier.uri | http://hdl.handle.net/1903/15460 | |
| dc.language.iso | en | en_US |
| dc.subject.pqcontrolled | Aerospace engineering | en_US |
| dc.subject.pquncontrolled | control | en_US |
| dc.subject.pquncontrolled | dynamics | en_US |
| dc.subject.pquncontrolled | flexible | en_US |
| dc.subject.pquncontrolled | multi-body | en_US |
| dc.subject.pquncontrolled | simulation | en_US |
| dc.subject.pquncontrolled | tiltrotor | en_US |
| dc.title | Flight Dynamics Simulation Modeling and Control of a Large Flexible Tiltrotor Aircraft | en_US |
| dc.type | Dissertation | en_US |
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