This thesis describes the implementation of Yao?s adaptive robust control to an aircraftcontrol system. This control law is implemented as a means to maintain stability and trackingperformance 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 undernonlinear dynamic inversion control.The adaptive robust control methodology combines the robustness of sliding modecontrol to all types of uncertainty with the ability of adaptive control to remove steady stateerrors. A performance measure is developed in to reflect more subjective qualities a pilotwould look for while flying an aircraft. Using this measure, comparisons of the adaptiverobust control technique with the sliding mode and adaptive control methodologies aremade for various failure conditions. Each control methodology is implemented on a fullenvelope, high fidelity simulation of the F-15 IFCS aircraft as well as on a lower fidelity fullenvelope F-5A simulation. Adaptive robust control is found to exhibit the best performancein terms of the introduced measure for several different failure types and amplitudes.
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