Aircraft wing rock dynamics and control
Name
44605027-MIT.pdf
Description
Full printable version
Size
19.53 MB
Format
Adobe PDF
Checksum (MD5)
6587b0854fdeea964b988fd0d6ac64cf
Author(s)
Go, Tiauw Hiong
Advisor(s)
Rudrapatna V. Ramnath.
Date Issued
1999
Publisher
Massachusetts Institute of Technology
Abstract
The dynamics of wing rock on rigid aircraft having single, two, and three rotational degrees-of-freedom are analyzed. For the purpose of the analysis, nonlinear mathematical models of the aircraft are developed. The aerodynamic expressions contained in the models can be built by fitting the appropriate aerodynamic data into the model. The dynamic analysis is performed analytically using a technique combining the Multiple Time Scales method, Center Manifold Reduction principle, and bifurcation theory. The technique yields solutions in parametric forms and leads to the separation of fast and slow dynamics, and a great insight into the system behavior. Further, a unified framework for the investigation of wing rock dynamics and control of aircraft is developed. Good agreement between the analytical results and the numerical simulations is demonstrated. Based on the results of the dynamic analysis, appropriate control strategies for the wing rock alleviation are developed. The control power limitation of the conventional aerodynamics control surfaces is considered and its effects on the alleviation of wing rock are investigated. Finally, the potential use of advanced controls to overcome the conventional controls limitation is discussed.
Description
Thesis (Sc.D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1999.
Includes bibliographical references (p. 232-236).
Subjects
Aeronautics and Astronautics.
MIT Department
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics
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copyright. They may be viewed from this source for any purpose, but
reproduction or distribution in any format is prohibited without written
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