The author develops a nonlinear longitudinal model of an aircraft modeled by
rigid fuselage, tail, and wing, where the wing is attached to the fuselage with a torsional
spring. The main focus of this research is to retain the full nonlinearities
associated with the system and to perform gust load alleviation for the model by
comparing the impact of a proportional-integral- lter nonzero setpoint linear controller
with control rate weighting and a nonlinear Lyapunov-based controller. The
four degree of freedom longitudinal system under consideration includes the traditional
longitudinal three degree of freedom aircraft model and one additional degree
of freedom due to the torsion from the wing attachment. Computational simulations
are performed to show the aeroelastic response of the aircraft due to a gust load
disturbance with and without control. Results presented in this thesis show that
the linear model fails to capture the true nonlinear response of the system and the
linear controller based on the linear model does not stabilize the nonlinear system.
The results from the Lyapunov-based control demonstrate the ability to stabilize the
nonlinear response, including the presence of an LCO, and emphasize the importance
of examining the fully nonlinear system with a nonlinear controller.
| Identifer | oai:union.ndltd.org:tamu.edu/oai:repository.tamu.edu:1969.1/ETD-TAMU-2009-08-1504 |
| Date | 2009 August 1900 |
| Creators | Lucas, Amy Marie |
| Contributors | Strganac, Thomas W. |
| Source Sets | Texas A and M University |
| Language | en_US |
| Detected Language | English |
| Type | Book, Thesis, Electronic Thesis, text |
| Format | application/pdf |
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