关键词: 航向控制, 输入非线性, 直升机, 自调整神经元, 外圈滚道轮廓, 旋转精度, 圆度误差, 圆柱滚子轴承, 正态分布

Abstract: The yaw dynamics of helicopter involves input nonlinearity, time-varying parameters and the couplings between main and tail rotor. With respect to such complicated dynamics, the normal proportional integral differential (PID) control is diffi-cult to realize good tracking performance while maintaining stability and robustness simultaneously. A valid control is pro-posed by integrating adaptive neuron into sliding mode control. The stability of the proposed method can be guaranteed by the sliding mode condition, and the time-varying parameters and other uncertainties in the helicopter dynamics can be rejected by the adaptive neuron to achieve small tracking error. The stability of the proposed algorithm is proved and the simu-lations results with respect to the dynamics identified from a real helicopter-on-arm testbed are presented. The simulation results are further compared with those obtained by normal PID control to demonstrate the improvements of the proposed algorithm.

Key words: Adaptive neuron, Helicopter, Input nonlinearity, Yaw control, Cylindrical roller bearing, Normal distribution, Outer raceway profile, Rotational accuracy, Roundness error