Abstract

Presented here is an L <sub xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xlink="http://www.w3.org/1999/xlink">1</sub> adaptive control architecture for a generic transport aircraft. At its core, this architecture features a three-axis, non-linear, dynamic inversion controller. Command inputs for this baseline controller are provided by pilot roll-rate, pitch-rate, and sideslip commands. This paper will first thoroughly present the baseline controller followed by a description of the L <sub xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xlink="http://www.w3.org/1999/xlink">1</sub> adaptive augmentation to this control system. Results are presented via a full-scale, non-linear simulation of NASA's Generic Transport Model (GTM).

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