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针对以主动控制为目的的模型降阶中的降阶精度以及控制系统的降阶设计问题,以变体飞机折叠机翼为对象,建立以模态综合法为基础的动力学模型,对该模型分别采用模态价值分析方法和平衡截断降阶方法建立结构的降阶模型;利用可控度、可观度对两种降阶模型的精度进行对比分析,对降阶模型进行设计并施加主动控制律,抑制翼尖的位移响应。结果表明:平衡截断降阶模型具有较高的可控度,模态价值分析降阶模型具有较高的可观度;两种降阶模型均可以快速精确地得到高阶动力学的降阶模型,并且该模型可以有效地应用于主动控制系统的设计。
Aiming at the problem of reduced order precision and the reduced-order design of the control system for the purpose of active control, a dynamic model based on the modal synthesis method is established for the folded wing of a variant aircraft. The modeled value analysis method and the balanced truncation reduction method are respectively used to establish the reduced-order model of the structure. By using the controllability and the observability, the accuracy of the two reduced-order models is compared and analyzed. The reduced-order model is designed and the active control law , Suppress the tip response of the displacement. The results show that the balanced truncated order reduction model has higher controllability and the modal value analysis reduced order model has a higher degree of observability. Both of the order reduction models can obtain the order reduction model of higher order dynamics quickly and accurately, And the model can be effectively applied to the design of active control system.