摘要
飞机局部复合材料构件存在着因涡流作用诱发的弹性振动问题 .本文首先研究了表面粘贴型压电元件对复合材料构件的传感和驱动原理 ;针对结构待控模态的要求 ,采用了 D-准则优化确定同位压电传感 /驱动器在构件中的布置方案 ;应用自适应振动前馈控制原理和方法 ,构造了闭环控制系统 ;分别利用正弦和方波信号激发气动声场 ,对玻纤 /环氧圆筒构件进行激振和振动控制实验 ;结果表明 :构件主要待控模态的振动得到了有效抑制 ,但也出现了高阶模态被激发的问题 ,导致结构辐射噪声上升 .
The vortex induced buffeting loads on aircraft may cause high cyclic strain and stress in aircraft composite structure and lead to composite delamination. To simulate the active vibration suppression for such composite structures, an experimental system is designed, where collocated piezoeletric sensors/actuators are bonded to the surfuce of a composite cylindrical shell, and the maximum determinant of Fisher Information Matrix criteria is used to arrange the piezoelectric network. With sine and square acoustic fields as exciting source and with the filtered adaptive control algorithm to control the deformation of the actuators, a close loop control is established to minimize the selexted vibration modes of the cylindrical shell. Experiments on the system show that the selected modes can be suppressed effectively but higher modes are also excited and lead to significant noise radiation which should be treated carefully in future research.
出处
《实验力学》
CSCD
北大核心
2000年第4期441-447,共7页
Journal of Experimental Mechanics
基金
国家自然科学基金
航空科学基金!(5 96 35 140 )
江苏省博士后科研基金资助项目
关键词
复合材料
气动冲击
振动抑制
自适应控制
增强纤维
飞机
composite material
aero elastic buffetting
vibration supporession
adaptive control
smart structure
