大气紊流作用下超音速二元机翼的脉动响应  

Pulsation response of a two dimensional wing to atmosphere turbulence in supersonic flow

作　　者：郑国勇[1] 鲁丽[2] 杨翊仁[2] 

机构地区：[1]中南大学土木建筑学院,长沙410075 [2]西南交通大学应用力学与工程系,成都610031

出　　处：《振动与冲击》2009年第4期110-112,共3页Journal of Vibration and Shock

基　　金：国家自然科学基金委与中国工程物理研究院资助项目(10576024);西南交通大学校基金(2006B02)

摘　　要：以二元机翼为研究对象,研究大气紊流作用下系统的脉动响应。将气动力分解为简谐振动气动力和脉动气动力两部分,采用随机场的三角级数合成法得到作用在机翼上的脉动压力,运用随机理论对机翼均方根响应值进行分析,着重考查了平均来流速度、湍流尺度、湍流强度等对系统均方根响应的影响。结果表明,系统的均方根响应随速度的增大而增大,在流体速度小于线性临界颤振速度时,其变化很平缓,当速度超过临界颤振速度时,其均方根响应迅速增大。而均方根响应几乎随紊流强度的变化呈线性增长,但其对紊流尺度的变化不很敏感。The dynamic response of a two-dimensional wing to atmosphere turbulence was investigated. The aerodynamic force was resolved into two parts, free vibrating aerodynamic force and fluctuating aerodynamic force. The fluctuating pressure could be obtained by using the trigonometric series composition method of random field. The mean square root of the system response was calculated with the random theory. It was the focal point to analyze the influences of the mean velocity, the turbulence strength and the turbulence integral measure on the mean square root of the structure response. The results showed that the mean square root of the response slowly and linearly increases when the flow velocity is lower than the flutter critical speed; but, when the flow velocity is over the flutter critical speed, the mean square root of the response prominently and linearly rises with increase in the flow velocity. However, the mean square root of the response is not sensitive to the change of the integral measure of turbulence.

关 键 词：大气紊流 极限环 颤振 活塞理论 随机响应 

分 类 号：V411[航空宇航科学与技术—航空宇航推进理论与工程] O322[理学—一般力学与力学基础]