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Description:
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This thesis describes the implementation of Yao s 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 . |