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颤振边界
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  flutter boundary
     Focused on the features and requirements of flutter boundary prediction (FBP), the method presented here is introduced and investigated around precision, anti-noise and short sample.
     针对飞机颤振边界预测(Flutter Boundary Prediction,FBP)的数据特征及分析要求,论文从预测精度、抗噪性、短样本效应三个方面考察了所研究方法的适用性和可靠性。
短句来源
     Real-time Flutter Boundary Prediction System for Flutter Test with Progressive Variable Speed
     连续变速颤振试验的实时颤振边界预测系统
短句来源
     THE PREDICTION OF FLUTTER BOUNDARY——THE APPLICATION OF STATE-SPACE MODEL AND LYAPUNOV'S DIRECT METHOD
     颤振边界预测——状态空间模型和李雅普诺夫直接法的应用
短句来源
     Method of Time Frequence Syntony for Flutter Boundary Prediction
     颤振边界预测的时频共振方法研究
短句来源
     The nonlinear flutter boundary of the sandwich wing is obtained by jointly running structural solver and aerodynamic solver.
     通过结构求解器和空气动力求解器联合求解来完成非线性颤振边界的计算。
短句来源
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  flutter boundaries
     Two standard aeroelastic computing examples(2D Isogai wing with S type flutter boundary and 3D transonic flutter example-AGARD445.6 wing) are computed. The computed flutter boundaries based on ROM are well compared with those of the directly coupling CFD/CSD method.
     计算了跨声速具有S型颤振边界的气动弹性标准算例-Isogai wing和三维气动弹性标模算例AGARD445.6,辨识模型计算边界与非定常Euler方程计算结果吻合。
短句来源
     EFFECT OF BLADE MISTUNING AND BLADE-DISK ON CASCADE FLUTTER BOUNDARIES
     叶片失调及盘片耦合对叶栅颤振边界的影响
短句来源
     Effccts of Blade Mistuning Order and Centrifugal on Cascades Flutter Boundaries
     叶片失调阶次及离心力效应对叶栅颤振边界的影响
短句来源
     The panel flutter boundaries are finally determined and the effect of temperature, airflow speed, etc, on the panel flutter characteristics is analyzed.
     最后确定了壁板的颤振边界,分析了温度、来流速度等因素对壁板颤振特性的影响规律。
短句来源
     (4) . The Newmark method is used to solve the panel flutter equations in time domain. The linear flutter boundaries are determined and the effect of temperature on flutter boundaries is analyzed.
     (4).编制了壁板颤振分析的有限元程序,采用Newmark方法在时域中求解了壁板的线性颤振方程,确定了壁板的颤振边界,分析了温度对壁板颤振边界的影响。
短句来源
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  “颤振边界”译为未确定词的双语例句
     The results show that at δ=0.5mm tip clearance due to decrease secondary flows loss the exicted vibration energy of flow is increased, then the scope of blade stall flutter is enlarged and the flutter-boundary is removed forward.
     实验结果表明,对δ=0.5mm的叶尖间隙,由于二次流损失减少,气流激振能量增加,使叶片失速颤振区的范围扩大,颤振边界前移。
短句来源
     The flutter calculation and experiments are performed for two-dimensional wing with external store, the effects of pylon pitching stiffness on the flutter speed are investigated.
     本文对带外挂物二元机翼的颤振特性进行了理论和实验研究,主要分析机翼与外挂物之间俯仰联接刚度对颤振边界的影响。
短句来源
     The flluter boundary is determined by the theory of Hopf bifurcation.
     通过Hopf分叉理论,确定了颤振边界
短句来源
     In order to validate the presented method, the linear flutter equations of the sandwich wing are established using the linear part of the ONERA model.
     为了验证非线性颤振边界的求解方法 ,还利用 ONERA气动力模型中的线性部分建立了夹芯翼的线性颤振方程。
短句来源
     Focused on the nonstationary features and analysis requirements of flutter test data, the application scheme is brought forward for flutter signal processing.
     本文基于颤振试验信号的非平稳特点与分析需求,应用自适应时频分析技术给出并实现了两种新的颤振信号处理方案,重点研究了适用于连续变速颤振试验的颤振边界预测问题。
短句来源
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  flutter boundary
Fixed points of the system are found analytically and regions of limit cycle oscillations are detected for velocities well below the divergent flutter boundary.
      
Our approach is to use the transversality theorem in locating such flutter boundaries using this criterion:at a flutter boundary, the characteristic polynomial does not intersect the axis of the abscissa transversally.
      
AF is linearly interpolated with Dynamic pressure to obtain Flutter boundary.
      
Accurate prediction of flutter boundary prior to and during flight testing is critical for expanding an aircraft's flight envelope.
      
A flutter point obtained in the wind-tunnel test is com pared with a flutter boundary calculated from an analysis based on a Donnell-type theory.
      
更多          
  flutter boundaries
As a check on the current energy methods, the stall flutter boundaries for two real rotors are predicted by using the present method and the results are compared with the experiments and those predicted by using an energy method.
      
A new method of calculating the flutter boundaries of undamped aeroelastic "typical section" models is presented.
      
Our approach is to use the transversality theorem in locating such flutter boundaries using this criterion:at a flutter boundary, the characteristic polynomial does not intersect the axis of the abscissa transversally.
      
Formulas for computing the flutter boundaries of structures with two degrees of freedom are presented, and extension to multi degree of freedom systems is indicated.
      
Figure 11showsthe predicted symmetric and antisymmeaic flutter boundaries for this configurationwith respect to Mach number.
      
更多          


The coupled flap-lag flutter stability of a helicopter rotor blade in hover is investigated by using a finite element formulation based on the principle of minimum potential energy. Quasisteady two-dimensional airfoil theory is used to obtain the aerodynamic loads. The resulting nonlinear equations of motion are solved for steady state blade deflections. The flutter solution is calculated on the assumption that the blade motion is a small perturbation about the steady solution. Finally, results are presented...

The coupled flap-lag flutter stability of a helicopter rotor blade in hover is investigated by using a finite element formulation based on the principle of minimum potential energy. Quasisteady two-dimensional airfoil theory is used to obtain the aerodynamic loads. The resulting nonlinear equations of motion are solved for steady state blade deflections. The flutter solution is calculated on the assumption that the blade motion is a small perturbation about the steady solution. Finally, results are presented for hingeless rotor blade configurations.

本文用基于最小位能原理的有限元方法研究了直升机悬停时旋翼浆叶挥舞—摆振耦合颤振。利用准定常二维片条理论求出气动载荷。由非线性运动方程求出定常状态浆叶变形,假定浆叶绕定常状态解运动为小扰动,确定颤振边界。最后,给出了无铰旋翼浆叶的一个数字例子。

Some improvements in previous computation models of blade stall flutter in axial-flow compressors have been made on both aerodynamics and structural dynamics so as to make the models more practical.The calculations show that the effect of in-passage shock and separation flow on the aeroelastic stability of a blading system vibrating in a pure bending mode with single degree of freedom is qualitatively different from that in a predominant bending mode with two degrees of freedom.The coupling of bending and torsion...

Some improvements in previous computation models of blade stall flutter in axial-flow compressors have been made on both aerodynamics and structural dynamics so as to make the models more practical.The calculations show that the effect of in-passage shock and separation flow on the aeroelastic stability of a blading system vibrating in a pure bending mode with single degree of freedom is qualitatively different from that in a predominant bending mode with two degrees of freedom.The coupling of bending and torsion degrees of freedom is probably one of the most important factors which cause onset of the stall flutter .Finally, the stall flutter boundary is preliminarily predicted for an actual rotor and the results are compared with the corresponding experimental data.

本文对于现有的叶片失速颤振计算模型进行了一些改进,以期使其更接近于真实物理图画。计算结果表明,就槽道激波以及物面气流分离对于叶片气动弹性稳定性所起的作用来看,在单自由度纯弯振荡和双自由度弯曲主导振荡两种情况之下是具有实质性差别的。在文中对于一个实际转子的失速颤振边界进行了数值预测,并与相应的实验结果进行了对比。

Blade flutter is a challenging problem in the development of modern aerocraft engines of high thrust-weight ratio. The blade stall flutter is more common and serious than other kinds of flutter, which, resulted from aeroelastic instability in varieties of turbomachinery. Because of the complication of the problem, the study on the prediction of the flutter is still in its early stage.Some improvements have been made in this paper to develop a prediction method which can reflect the interaction between the aerodynamic...

Blade flutter is a challenging problem in the development of modern aerocraft engines of high thrust-weight ratio. The blade stall flutter is more common and serious than other kinds of flutter, which, resulted from aeroelastic instability in varieties of turbomachinery. Because of the complication of the problem, the study on the prediction of the flutter is still in its early stage.Some improvements have been made in this paper to develop a prediction method which can reflect the interaction between the aerodynamic and structural factors of the problem.On the basis of a vibration model in two degrees of freedom, which was developed in the case of incompressible or pure supersonic flow around a flat cascade, some systematic coupling terms of structural dynamics are introduced in form of exciting forces according to the characteristics of real rotors. The systematic structural coupling coefficients are determined by solving the vibration equations inversely, which reflected the out-of-phase vibration of bending and torsion due to the existence of travelling wave.The improved model of structural dynamics is combined with the unsteady aerodynamic model incorporating the effect of transonic separation flow around a cascade to simulate the aeroelastic system of blade stall flutter, which is solved in an iteration way.It is shown, by two examples for real rotors, that the predictions by the present method agree well with the experiments. The computation results doesn't show much difference with those by an energy method developed by the authors previously. This means that the application of the energy methods to the study of the blade stall flutter is still acceptable. However, the present method can incorporate the response of structural dynamics of the problem and reflect the interaction between the aerodynamic and structural sides in an iterative way. Therefore, as the research on the problem goes en a.nd the required accuracy of the computation is raised further, this kind of methods will be used more and more.

本文通过将改进的双自由度振荡叶片结构动力学模型与能够计算带分离的跨音叶栅非定常流场的气动模型相匹配,构成了一个具有气动、结构两个方面的耦合系统,用这两个方面相互迭代的方式来求解该系统以反映问题本身气动和结构相互作用的物理背景,对于两个实际转子的失速颤振边界进行了数值预测并与相应的实验结果及能量法模型计算的结果进行了对比。

 
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