Title:
Dynamic Wake Distortion Model for Helicopter Maneuvering Flight

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dc.contributor.advisor Prasad, Jonnalagadda V. R.
dc.contributor.author Zhao, Jinggen en_US
dc.contributor.committeeMember He, Chengjian
dc.contributor.committeeMember Peters, David, A.
dc.contributor.committeeMember Sankar, Lakshmi N.
dc.contributor.committeeMember Schrage, Daniel P.
dc.contributor.department Aerospace Engineering en_US
dc.date.accessioned 2005-09-16T14:57:59Z
dc.date.available 2005-09-16T14:57:59Z
dc.date.issued 2005-04-10 en_US
dc.description.abstract A new rotor dynamic wake distortion model, which can be used to account for the rotor transient wake distortion effect on inflow across the rotor disk during helicopter maneuvering and transitional flight in both hover and forward flight conditions, is developed. The dynamic growths of the induced inflow perturbation across the rotor disk during different transient maneuvers, such as a step pitch or roll rate, a step climb rate and a step change of advance ratio are investigated by using a dynamic vortex tube analysis. Based on the vortex tube results, a rotor dynamic wake distortion model, which is expressed in terms of a set of ordinary differential equations, with rotor longitudinal and lateral wake curvatures, wake skew and wake spacing as states, is developed. Also, both the Pitt-Peters dynamic inflow model and the Peters-He finite state inflow model for axial or forward flight are augmented to account for rotor dynamic wake distortion effect during helicopter maneuvering flight. To model the aerodynamic interaction among main rotor, tail rotor and empennage caused by rotor wake curvature effect during helicopter maneuvering flight, a reduced order model based on a vortex tube analysis is developed. Both the augmented Pitt-Peters dynamic inflow model and the augmented Peters-He finite state inflow model, combined with the developed dynamic wake distortion model, together with the interaction model are implemented in a generic helicopter simulation program of UH-60 Black Hawk helicopter and the simulated vehicle control responses in both time domain and frequency domain are compared with flight test data of a UH-60 Black Hawk helicopter in both hover and low speed forward flight conditions. en_US
dc.description.degree Ph.D. en_US
dc.format.extent 7709954 bytes
dc.format.mimetype application/pdf
dc.identifier.uri http://hdl.handle.net/1853/7103
dc.language.iso en_US
dc.publisher Georgia Institute of Technology en_US
dc.subject Rotor inflow
dc.subject Helicopter aerodynamics
dc.subject Flight simulation
dc.subject Maneuvering flight en_US
dc.subject.lcsh Helicopter flight simulators en_US
dc.subject.lcsh Wakes (Aerodynamics) Mathematical models en_US
dc.subject.lcsh Rotors (Helicopters) Aerodynamics en_US
dc.title Dynamic Wake Distortion Model for Helicopter Maneuvering Flight en_US
dc.type Text
dc.type.genre Dissertation
dspace.entity.type Publication
local.contributor.advisor Prasad, Jonnalagadda V. R.
local.contributor.corporatename College of Engineering
local.contributor.corporatename Daniel Guggenheim School of Aerospace Engineering
local.relation.ispartofseries Doctor of Philosophy with a Major in Aerospace Engineering
relation.isAdvisorOfPublication 933b7ff4-7a2e-4eab-9618-bc6303890af3
relation.isOrgUnitOfPublication 7c022d60-21d5-497c-b552-95e489a06569
relation.isOrgUnitOfPublication a348b767-ea7e-4789-af1f-1f1d5925fb65
relation.isSeriesOfPublication f6a932db-1cde-43b5-bcab-bf573da55ed6
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