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.
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.
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.
本文采用谐波平衡法，定量地解释了机翼颤振主动抑制风洞试验中出现的极限环现象。
The phenomena "limit cycle" occurred in wind tunnel test for active flutter suppression of a wing model are numerically explained using Harmonic Balance Method.
结合某大型飞机机翼颤振吹风模型的动力设计，本文给出了工程应用的具体数值例子。
Combining dynamic design of wing flutter model for a giant transport aircraft, a numerical example of engineering application is presented.
提出了一种局部形式的流固耦合问题界面插值方法，并应用于机翼颤振计算的界面插值。
A local form of interface interpolation method for fluid-structure interaction problems was presented and applied to interpolation of wing flutter calculation.
根据实际问题的物理模型，并通过对机翼颤振模型设计原理的分析，建立了优化设计的数学模型；
The math model, based on real physical one, was modeled according the essential theory and design course of the flutter wing model designing.
应用中心流形理论将二元机翼颤振这一四维系统降为二维系统，用后继函数判别法对分叉点的真假中心及稳定性问题进行了分析。
The type and stability of the bifurcation points in the subsequent reduced two dimensional system are analyzed by the method of succeeding function.
在此基础上建立了完整的机翼颤振模型工程优化设计方法，使该方法能够应用在模型设计的很多方面，为工程设计提供了一种有效的手段。
An optimization method of flutter wing model was developed and was used in many aspects of model designing, providing an efficient design method in engineering.
分析了飞机机翼—外挂干扰颤振特性。
The paper analyzes the external stores jam flutter characteristics of aircraft wing.
本文简要地阐述了具有后缘控制面的二元机翼模型主动颤振抑制低速风洞试验的全过程。
This paper gives a brief description of the whole process of the low-speed wind tunnel test for active flutter suppression of a two-dimensional wing model with trailing edge control surface.
使用解析方式推导得到机翼的临界颤振速度、颤振频率对于设计变量的灵敏度表达式。
Then the gradients of flutter speed and frequency of wing with respect to the design variables were deduced with analytical method.
本文研究了机翼跨音速颤振的频域计算方法。
Computation of wing flutter for unsteady transonic flows in the frequency domain is studied in this thesis.
根据热气动弹性特点，探讨了气动加热温度对三角机翼模态特性和颤振特性的影响。
From the characteristics of aerothermoelasticity, the effects of temperature in aerodynamic heating on the mode of a delta wing and the characteristic of its flutter were researched.
研究了在不可压缩流中具有立方非线性俯仰刚度的二元机翼的颤振问题。
This paper studies the flutter of a two-dimensional airfoil in the incompressible flow with cubic non-linearity in the plunging direction.
探讨了由于振动频率、颤振自由度、广义质量等参数的变化对机翼—外挂干扰颤振特性影响的一些特点。
This paper probes the features of the effect on the external stores jam flutter characteristics due to the variation of parameters of vibration frequency, flutter freedom and generalized mass.
将增量谐波平衡法推广应用于二元机翼的颤振问题，为强非线性颤振分析提供了一条有效的新途径。
The incremental harmonic balance method is extended to analyze the flutter of two dimensional airfoils. The present procedure provides a new effective way to the strongly nonlinear flutter analysis.
对跨声速飞机机翼作了跨声速非定常气动力计算，对跨声速民航机机翼的颤振模型作了颤振计算，与TDLM的比较表明，两者结果有较好的一致性。
The unsteady aerodynamic results of the transonic wing are presented, and flutter calculation is made. The comparison with TDLM shows that the agreement is very good.
风洞试验结果说明，采用颤振主动抑制控制系统后，机翼的颤振临界速度可提高37%。
The results of the wind tunnel test show the flutter critical speed of the wing model increases by 37% after the implementation of AFS system.
从理论及实验两方面，研究了带外挂后掠机翼的极限环颤振分叉现象，得到了稳定、半稳定及不稳定极限环。
Both theoretical and experimental analyses are performed to investigate the limit cycle flutter bifurcation of a sweepback wing with an external store in the tip of the wing.
本文编制了可用于分析带有颤振主动抑制系统的机翼的根轨迹法程序。
A flutter analysis based on root locus method is programmed. It can be applied to a wing equipped with an active flutter suppression system.
机翼的非线性颤振计算表明了方法的有效性。
The nonlinear flutter calculation demonstrates the validity of the presented method.
充气机翼的颤振形式除常规的弯扭模态耦合外，弦向弯曲模态同样会发生颤振；
Except for the typical bending and torsion modes, the chord-wise bending modes have low frequencies.
通过跨声速标模算例AGARD445.6机翼的颤振计算，计算的颤振临界速度与实验值有5%左右的误差，验证本方法的正确性。
The computing AGARD445.6 wing flutter results validate the physical law of a typical transonic flutter "dip" with the bottom near the domain which Mach number is 1.
文中运用该方法对十个不同平面形状的机翼进行了二十九种状态的颤振计算，并和风洞颤振实验结果作了比较。
This method was applied to flutter calculations of 29 cases for wings with 10 different types of plan forms.
文中运用该方法对十个不同平面形状的机翼进行了二十九种状态的颤振计算，并和风洞颤振实验结果作了比较。
This method was applied to flutter calculations of 29 cases for wings with 10 different types of plan forms.
应用推荐