CAJ | 학술논문

研究了带有前后缘控制面的二元机翼气动弹性颤振主动控制问题. 采用多项式非线性模型建立气动弹性动态方程,然后考虑俯仰方向阻尼和刚度存在参数不确定性的情况下,利用Lyapunov稳定性理论设计了具有全局稳定的反馈线性化自适应和结构化模型参考自适应( SMRAC )控制律.仿真结果显示,在控制面偏转存在限制时,所设计的控制律可以有效地实现颤振的抑制,考虑阻尼不确定性对于颤振抑制具有减小收敛时间的作用,但对于系统响应特性占据主导作用的是刚度不确定性.
연구료대유전후연공제면적이원궤익기동탄성전진주동공제문제. 채용다항식비선성모형건립기동탄성동태방정,연후고필부앙방향조니화강도존재삼수불학정성적정황하,이용Lyapunov은정성이론설계료구유전국은정적반궤선성화자괄응화결구화모형삼고자괄응( SMRAC )공제률.방진결과현시,재공제면편전존재한제시,소설계적공제률가이유효지실현전진적억제,고필조니불학정성대우전진억제구유감소수렴시간적작용,단대우계통향응특성점거주도작용적시강도불학정성.
The question of active flutter control of an aeroelastic airfoil with leading? and trailing?edge control sur?faces is investigated. The dynamical equations of a two?dimensional airfoil with polynomial nonlinearity in pitch are established. Then suppose that there are parametric uncertainties in both pitch stiffness and damping; Lyapunov function is used to design an adaptive control law of feedback linearization and a structured model reference adaptive control law. The simulation results and their analysis show preliminarily that:(1) the nonlinear controllers are effective for flutter suppression even if the control surface deflection is limited;(2) considering damping uncer?tainty has positive effect on reducing the convergence time but stiffness uncertainty plays the leading role for flutter control.