The stability of an aircraft during the landing roll

dc.contributor.authorDierksmeier, Douglas Daviden
dc.contributor.departmentMechanical Engineeringen
dc.date.accessioned2017-03-09T21:35:13Zen
dc.date.available2017-03-09T21:35:13Zen
dc.date.issued1983en
dc.description.abstractThe object of this thesis is to determine the directional stability of a tricycle-geared aircraft during the landing roll. The motion of the aircraft is simulated by a computer program based on the appropriate equations of motion. Empirical aircraft and tire data are utilized in order to improve the simulation process. The stability of the aircraft is obtained by analyzing the motion of the vehicle after an initial disturbance about the vertical axis of the aircraft. The influence of the aircraft's velocity and other parameters on the stability is then determined. For the single-engine Cessna, the results show that a steady-state yaw angle is obtained after an initial disturbance. The results are presented graphically to show the effect of various parameters on the aircraft's stability.en
dc.description.degreeMaster of Scienceen
dc.format.extentxv, 69 leavesen
dc.format.mimetypeapplication/pdfen
dc.identifier.urihttp://hdl.handle.net/10919/76011en
dc.language.isoen_USen
dc.publisherVirginia Polytechnic Institute and State Universityen
dc.relation.isformatofOCLC# 9995454en
dc.rightsIn Copyrighten
dc.rights.urihttp://rightsstatements.org/vocab/InC/1.0/en
dc.subject.lccLD5655.V855 1983.D537en
dc.subject.lcshAirplanes -- Landing -- Simulation methodsen
dc.subject.lcshStability of airplanes -- Simulation methodsen
dc.titleThe stability of an aircraft during the landing rollen
dc.typeThesisen
dc.type.dcmitypeTexten
thesis.degree.disciplineMechanical Engineeringen
thesis.degree.grantorVirginia Polytechnic Institute and State Universityen
thesis.degree.levelmastersen
thesis.degree.nameMaster of Scienceen

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