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

Abstract

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