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利用大展弦比机翼后缘不同位置上的操纵面进行颤振主动控制,通过将大展弦比机翼简化为包含弯曲和扭转两种模态的悬臂梁结构,根据片条理论,建立包含操纵面运动规律的大展弦比机翼气动弹性方程.由于简化的数值模型与实际模型之间存在一定的误差,通常模型的运动方程包含有不确定参量用来表示建模误差.鲁棒控制方法能够得到一个有效控制器,控制这种带有模型不确定参量的运动方程.文中论述利用鲁棒μ控制方法,研究有两个操纵面大展弦比机翼的鲁棒控制问题.仿真结果表明鲁棒μ控制可以有效地抑制大展弦比机翼的受扰振动,提高颤振临界速度,且两个操纵面共同控制效果比单操纵面显著.
Active control of flutter is controlled by the control surfaces at different positions on the trailing edge of the large aspect ratio wing. By simplifying the large aspect ratio wing to a cantilever structure including two modes of bending and twisting, according to the slice theory, Aeroelastic equations with large aspect ratio wings that contain the motion of the control surface. Because of the error between the simplified numerical model and the actual model, the motion equation of the model usually contains uncertain parameters to represent the modeling error. The control method can obtain an effective controller to control the motion equation with uncertain parameters of the model.In this paper, the problem of robust control of a large aspect ratio airfoil with two control surfaces is studied by using the robust μ control method. The results show that the robust μ control can effectively restrain the disturbed vibration of the large aspect ratio wing and increase the flutter critical speed. The joint control effect of the two control surfaces is more significant than the single control surface.