模型降阶在折叠机翼主动控制中的应用研究  

Application of Model Reduction in Active Control of a Folding Wing

作　　者：倪迎鸽 万小朋[1] 赵美英[1] 

机构地区：[1]西北工业大学航空学院,西安710072

出　　处：《航空工程进展》2015年第3期326-332,共7页Advances in Aeronautical Science and Engineering

摘　　要：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。For reduced-order accuracy and control system design of model reduction in active control, taking the folding wing as an example, the structural dynamic model is established based on the modal synthesis method. Two different reduced order models are obtained by virtue of modal cost analysis and balanced truncation. The comparisons and analyses of two different reduction models rely on degree of controllability and degree of observability. Finally, the optimal control law is applied to the reduction models to restrain the vertical displacement of the wing tip. The results indicate that the balanced truncation reduction model is of higher degree of controllability, while the modal cost analysis reduction model is of higher degree of observability. The low order model of structural dynamic model can be achieved quickly and precisely by using two different reduction methods. It is effective to design the active control system for the low order model.

关 键 词：模态价值分析 平衡截断 主动控制 可控度 可观度 折叠机翼 

分 类 号：V271.4[航空宇航科学与技术—飞行器设计]