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Adaptive, Integrated Guidance and Control Design for Automatic Landing of a fixed Wing UAV

Boo Min Kim, Byoung Soo Kim, Cheolgun Ha


This paper presents an automatic landing control design using adaptive, integrated guidance and control (IGC) logic. The proposed IGC design uses a combination of an adaptive output feedback inversion and backstepping techniques. We formulate the problem as an adaptive output feedback control problem for a line-of-sight based chasing flight configuration. The design objective is to regulate relative distance between the aircraft and the moving reference point on a landing pattern and two bearing angles maintaining turn coordination. Adaptive neural networks
are trained online with available measurements to compensate for inversion error due to unmodeled dynamics and modeling error of the aircraft in the design process. In addition, a reference command trajectory for the automatic landing control is designed in a way that the aircraft follows the lading pattern regardless of its initial position. The automatic landing system using IGC logic is evaluated using a sophisticated 6DOF nonlinear simulation program with the approach and landing scenario.

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