This thesis describes the implementation of Yaos adaptive robust control to an aircraft
control system. This control law is implemented as a means to maintain stability and tracking
performance of the aircraft in the face of failures and changing aerodynamic response.
The control methodology is implemented as an outer loop controller to an aircraft under
nonlinear dynamic inversion control.
The adaptive robust control methodology combines the robustness of sliding mode
control to all types of uncertainty with the ability of adaptive control to remove steady state
errors. A performance measure is developed in to reflect more subjective qualities a pilot
would look for while flying an aircraft. Using this measure, comparisons of the adaptive
robust control technique with the sliding mode and adaptive control methodologies are
made for various failure conditions. Each control methodology is implemented on a full
envelope, high fidelity simulation of the F-15 IFCS aircraft as well as on a lower fidelity full
envelope F-5A simulation. Adaptive robust control is found to exhibit the best performance
in terms of the introduced measure for several different failure types and amplitudes.
| Identifer | oai:union.ndltd.org:tamu.edu/oai:repository.tamu.edu:1969.1/1515 |
| Date | 17 February 2005 |
| Creators | Fisher, James Robert |
| Contributors | Swaroop, D.V.A.H.G., Smith, S. Craig |
| Publisher | Texas A&M University |
| Source Sets | Texas A and M University |
| Language | en_US |
| Detected Language | English |
| Type | Book, Thesis, Electronic Thesis, text |
| Format | 1222366 bytes, electronic, application/pdf, born digital |
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