基于高阶微分滑模面的不确定飞机控制系统自适应滑模控制

Adaptive sliding mode control for uncertain airplane control systems based on higher-order differential sliding mode surface

飞机控制系统作为典型的多输入多输出(MIMO)非线性系统,具有很强的耦合性和不确定性,导致控制难度大幅度提高。针对这一情况,研究了一类飞机姿态控制系统的跟踪控制问题。首先,将飞机姿态控制系统进行坐标变换,并且考虑输入不确定性的存在情况,提出了一种新的高阶微分滑模面,证明了滑模面的稳定性,然后,基于此高阶微分滑模面和神经网络的逼近能力,设计了光滑的自适应滑模控制器。基于Lyapunov稳定性理论,证明了所设计的控制器既保证了飞机姿态控制系统具有很好的跟踪性能,又避免了传统滑模控制器抖振现象的出现。最后,通过仿真验证了所设计控制器的有效性。与传统的滑模控制器对比,所设计的控制器是光滑的,在实际飞机姿态控制领域中具有很好的应用前景。

Airplane control system is a typical multitude input and multitude output(MIMO)nonlinear system with strong coupling and uncertainties,which would increase the controlling difficulty.The tracking control problem has been investigated for a class of airplane attitude control systems in this paper.Firstly,a new higher-order differential sliding mode surface is presented and its stability of the sliding mode surface is proved by coordinate transformation of airplane attitude control system and considering the existing of the input uncertainties.Then,a smooth adaptive sliding mode controller is design based on this higher-order differential sliding mode surface and the approximation ability of the neural network.Based on Lyapunov stability theory,it is proved that the designed controller not only ensures the airplane attitude control system with good tracking performance,but also avoids the appearance of the chattering phenomenon of traditional sliding mode controllers.Finally,the effectiveness of the proposed controller is verified by simulation results.The controller proposed in this paper has very fine application prospects in the field of airplane attitude control comparing the traditional one.