A backlash identification and compensation method for high-speed aircraft angular rate control

نویسندگان

چکیده

Abstract This paper focus on the hysteresis phenomenon of roll angular rate control resulting from backlash actuators for a high-speed aircraft in real flight. First, is analyzed time and frequency domain, then parameters are identified using statistic method. Second, based inverse model, L 1 adaptive controller with compensation designed. Third, two simulation tests without conducted results compared which show effectiveness backlash-compensation-based controller.

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ژورنال

عنوان ژورنال: Journal of physics

سال: 2023

ISSN: ['0022-3700', '1747-3721', '0368-3508', '1747-3713']

DOI: https://doi.org/10.1088/1742-6596/2478/10/102014