高超声速飞行器舵机摩擦的影响及其抑制方法

Effection and Restrained of Acutaor Friction on Hypersonic Vehicle

高超声速飞行器非线性影响飞行姿态控制,因此,在某型轴对称高超声速飞行器滚转通道数学仿真模型的基础上,仿真分析了基于静摩擦+库仑摩擦+黏性摩擦模型的舵机摩擦环节对滚转通道控制的影响,指出该摩擦环节会导致滚转通道振荡,最后提出采用非线性PID控制算法作为舵机控制算法抑制该摩擦环节。仿真结果表明,舵机应用该控制算法在不显著改变舵机性能的同时能减少舵机摩擦环节对飞行控制的影响。

The nonlinearity of hypersonic vehicle can effects flight attitude control. On the basis of the axisymmetric hyper- sonic vehicle roll channel mathematical simulation model, the paper analyses the simulation of the effect of the control actua- tor friction to roll channel which is builded by stiction＋coulomb＋viscous mode, indicates that the friction will lead to roll channel oscillation, finally advances that taking nonlinear PID control algorithm as control actuator control algorithm can re- strain the friction part. Simulation results show that the algorithm not only keeps the performance of the control actuator, but also reduces the influence on the part of the flight controls.