准确估计模态参数在飞机颤振边界的预测中具有重要意义。
The accuracy of modal parameter estimation plays a crucial role in flutter boundary prediction.
随着桥梁跨径的不断增大，悬索桥的颤振稳定问题日益突出。
The flutter stability of suspension bridge is becoming more and more important with increase of the span.
颤振稳定性已成为影响和控制大跨径悬索桥设计的一个重要问题。
Flutter stability is one of major factors governing the design of long span suspension Bridges.
特别是和用活塞理论所做的颤振分析相比，计算精度有了明显提高。
The accuracy of flutter analysis improved by this method is much higher than that obtained by the piston theory.
采用两种或多种数据处理方法，可以提高颤振导数识别结果的可信度。
The identification reliability of flutter derivatives can be improved by introducing two or more data processing methods.
试验是在大展弦比机翼颤振模型上进行的。
The tests are conducted on a wing model with large aspect ratio.
进行了变速磨削对颤振增长率影响的试验研究。
The influence of varying speed grinding on the chatter increasing rate has been studied experimentally.
该辨识方法成功地应用于飞机颤振特性的辨识。
Finally, this method is successfully used in the identification of aircraft buffeting characteristics.
研究了电流变减振器在铣床颤振控制中的应用。
The application of an er damper for milling machine vibration controlling was tested.
将提出的理论和方法应用于车削颤振的建模和分析。
The proposed theory and methods are applied to modeling and analysis of metal cutting chatter .
颤振试验数据处理是飞行颤振试验的重要组成部分。
Flutter test data processing was the important component of flight flutter testing of aircraft.
对镗杆振动学进行了研究，并总结了减小颤振的方法。
The study of dynamics is done for boring bar, and the methods are summarized to alleviate vibration chatter.
提出了带结构刚度非线性的超音速弹翼的颤振分析方法。
We present a method of analyzing flutter characteristics of wing with nonlinear stiffness in supersonic flow.
同时，本文还考虑了结构刚度非线性对颤振速度的影响。
The effect of nonlinear structural stiffness on flutter velocity was considered, too.
这种频率锁定规律可以清楚地解释失速颤振的各种非线性现象。
The characteristic of "lock-in" can be used to explain all kinds of nonlinear phenomenon of the stall flutter.
最后，分析了线性和非线性刚度系数对颤振响应拓扑结构的影响。
Finally, the influences of the linear and non-linear stiffness coefficients on the topological structure of flutter responses were analyzed.
试验表明，这种无颤振的机床技术思想与方法是可行的和有效的。
Experimental results show that the conception of chatter-free machine tools is feasible and effective.
此外还给出了两种叶尖间隙和两种叶型对失速颤振影响的实验结果。
This paper also presents the experimental results of effects of the blade tip clearance and the airfoil shape on the stall flutter boundary.
该方法既保证了控制系统的快速性和鲁棒性，又能够有效地削弱颤振。
This method not only ensures speediness and robustness of the control system, but also can effectively weaken chattering.
将一个二元颤振主动抑制系统视为由若干个滞后环节组成的控制系统。
FAS system can be considered as a control system comprising a number of hysteresis elements.
研究表明仅有竖弯自由度或扭转自由度的平板不可能发生单自由度颤振。
Results showed that flutter instabilities would not occur for the ITP with only one degree-of-freedom.
该方法是一种单参数搜索方法，克服了以往直接颤振分析方法的一些缺陷。
The proposed method overcomes the defects of the previous direct flutter analysis and it is a single parameter searching method.
并以颤振位移作为反馈变量，建立了基于二维模糊控制器的颤振控制系统。
A two-dimensional fuzzy controller using displacement as feedback variable is developed to control the cutting chatter.
使用热刚度计算理论，进行了不同温度场和不同结构材料的热颤振特性研究。
The thermal flutter characteristics of structure in different temperature and different material are researched using the thermal stiffness analysis method.
讨论了亏损系统模态控制的设计方法，并将其应用在飞机机翼颤振的控制问题中。
A modal controller design of defective system was presented, and it was applied in the flutter control problem of an airfoil.
本文首先回顾了大跨度桥梁颤振分析的基本方法和气动导数识别方法的研究现状。
The fundamental methods for flutter analysis and the current status of aerodynamic derivative identification are reviewed at first in this thesis.
通过所建理论模型及铣削试验讨论了铣削过程中强迫振动、颤振的产生条件及特点。
Through the theoretical model and milling experiment they discuss the condition of producing forced vibration and chatter in milling process and the chatter characteristics.
对国内外切削颤振领域的研究工作进行评述，分析了现有的颤振预报方法的优缺点。
The work in the field of prediction of cutting chatter is summarized. The advantages and disadvantages are also analyzed in this paper.
为了提高某型飞机机翼颤振速度，详细探讨利用副翼前缘配重提高颤振速度的方案。
To increase flutter speed of airfoil in aircraft engineering, the schemes that makes use of attached weights in leading-edge of aileron are discussed.
发现板在两端简支、中点联结松动时，结构首先出现屈曲失稳，而不会发生颤振失稳。
For pined_pined, loosed midpoint support plate, it is found that the plate's buckling instability will happen first while the flutter instability will disappear.
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