CAJ | 학술논문

提供了一种在高超声速飞行器姿态运动数学模型具有强耦合、不确定性以及非线性的特点的情况下，依然能够实现对其姿态运动进行高精度控制的控制器设计方法。该方法首先采用预测滤波器对系统的不确定性进行估计和补偿，通过对系统的不确定性进行补偿，大大减小了模型误差，提高了控制精度；其次在此基础上采用反馈线性化的方法对补偿后的系统进行解耦，并对解耦后的系统设计变结构控制器。通过仿真表明文中所设计的方法确实能够实现高超声速飞行器的高精度姿态控制。
제공료일충재고초성속비행기자태운동수학모형구유강우합、불학정성이급비선성적특점적정황하，의연능구실현대기자태운동진행고정도공제적공제기설계방법。해방법수선채용예측려파기대계통적불학정성진행고계화보상，통과대계통적불학정성진행보상，대대감소료모형오차，제고료공제정도；기차재차기출상채용반궤선성화적방법대보상후적계통진행해우，병대해우후적계통설계변결구공제기。통과방진표명문중소설계적방법학실능구실현고초성속비행기적고정도자태공제。
the attitude kinematic equation of hypersonic vehicle is described as a uncertainty nonlinear system with coupling considered.For this system, this paper presents a new method for the design of a high accuracy attitude control system.Firstly, by combining SMC ( Slide Mode Control) controller with FBL ( Feed Back linearization) , the control of decoupling, linear system is achieved.However, there are two problems in using this method.One problem is that it is unobservable to feedback of system.The other is that control error cannot be removed.Accord-ing to our analysis, control error is caused by uncertainties of model.For solving these problems, the prediction fil-ters are used.The simulation results and their analysis show preliminarily that the method is effective for improving the control precision of hypersonic vehicle.