高超声速飞行器自抗扰PID姿态控制

ADRC PID Attitude Control of a Hypersonic Flight Vehicle

针对高超声速飞行器模型非线性、气动参数变化剧烈的特点,运用自抗扰技术中的跟踪微分器,设计了自抗扰PID控制器,实现了对高超声速飞行器俯仰通道的姿态控制。仿真结果表明,通过两个跟踪微分器构造的自抗扰PID控制器对于高超声速飞行器这样复杂的模型有很好的控制能力,并且有很好的滤波性能和鲁棒性。

The tracking differentiator （TD） of auto-disturbance rejection control （ADRC） was used to design ADRC PID controller considering the hypersonic vehicle model is non-linear and aerodynamic parameters change rapidly. Attitude control of hypersonic vehicle pitch channel was achieved. Simulation results show that ADRC PID controller constructed by two TD can well controls hypersonic vehicle such a complex model, and has good filter performance and robustness