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Development of an autoland system for general aviation aircraft

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dc.contributor.advisor R. John Hansman. en_US
dc.contributor.author Siegel, Diana en_US
dc.contributor.other Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics. en_US
dc.date.accessioned 2012-07-02T15:43:09Z
dc.date.available 2012-07-02T15:43:09Z
dc.date.copyright 2012 en_US
dc.date.issued 2012 en_US
dc.identifier.uri http://hdl.handle.net/1721.1/71462
dc.description Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2012. en_US
dc.description Cataloged from PDF version of thesis. en_US
dc.description Includes bibliographical references (p. 207-208). en_US
dc.description.abstract Accidents due to engine failure, pilot disorientation or pilot incapacitation occur far more frequently in general aviation than in commercial aviation, yet general aviation aircraft are equipped with less safety-enhancing features than commercial aircraft. This thesis presents the design of an emergency autoland system that includes automatic landing site selection, guidance to the selected landing site and guidance along the final approach, in addition to the automatic landing capability provided by conventional autoland systems. The proposed system builds on the capability of a general aviation autopilot, flight management system and GPS/WAAS augmented, integrated navigation system. The system provides this automatic landing capability without the use of automatic throttle control and without the use of a radar altimeter, which are essential to conventional autoland systems, but are typically lacking on general aviation aircraft. The design addresses the challenge of no automatic throttle control by utilizing only two simple power settings: cruise power and zero power. The lack of radar altimeter is addressed by appropriate flare planning and placement of the target touchdown point. The approach from the point of autoland initiation, to the approach fix at the the landing site, is performed at cruise power, provided that power is available. The final approach from the approach fix to touchdown, is performed at zero power. Control of the touchdown point location during the final approach is achieved through adjustment of the length of the trajectory, whenever the aircraft's glide performance deviates from the expected performance. The aircraft's glide performance is measured online as the aircraft tracks the planned trajectory. The performance of the final design is evaluated in simulation in terms of touchdown point dispersion, sink rate and attitude on touchdown. en_US
dc.description.statementofresponsibility by Diana Siegel. en_US
dc.format.extent 208 p. en_US
dc.language.iso eng en_US
dc.publisher Massachusetts Institute of Technology en_US
dc.rights M.I.T. theses are protected by copyright. They may be viewed from this source for any purpose, but reproduction or distribution in any format is prohibited without written permission. See provided URL for inquiries about permission. en_US
dc.rights.uri http://dspace.mit.edu/handle/1721.1/7582 en_US
dc.subject Aeronautics and Astronautics. en_US
dc.title Development of an autoland system for general aviation aircraft en_US
dc.type Thesis en_US
dc.description.degree S.M. en_US
dc.contributor.department Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics. en_US
dc.identifier.oclc 795183424 en_US


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