The structure of the aircraft can not be reflected in the conventional wind tunnel flutter model.
传统的飞机风洞颤振模型不能反映飞机的结构特性。
The study is focused on the bifurcation and chaos characteristics of the flutter model, and the influence of viscoelastic damping.
通过数值模拟研究了该系统在粘弹阻尼作用下的动力学行为以及粘弹阻尼的影响。
Combining dynamic design of wing flutter model for a giant transport aircraft, a numerical example of engineering application is presented.
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。
Modal test and parameter identification of a wind tunnel flutter model simulating a wing with external missiles are presented in this paper.
本文介绍了带外挂风洞颤振模型模态试验与参数识别方法。
Modal test and parameter identification of a wind tunnel flutter model, similar to a wing with external missiles, are presented in this paper.
本文介绍了带外挂风洞颤振模型模态试验与参数识别方法。
Design of flutter model from aircraft metal structure to composite structure can be achieved by equation of stiffness, yet it may cost much time for general design method.
金属飞机结构到复合材料结构的颤振模型设计，要求采用刚度等代法来完成，然而一般的设计方法通常需要消耗大量时间。
An experimental technique and method for flutter research of helicopter blade model are proposed.
提出了直升机模型桨叶颤振试验技术及试验方法。
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.
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。
This paper makes use of free vibration method, using the same model and measuring device to identify the flutter derivatives of the girder.
本文对主梁的颤振导数识别，采用与主梁颤振分析试验相同的节段模型和测量装置，以自由振动法进行试验。
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。
It incorporates organically the flight test data and the flutter theory model by the structured singular value theories, to process the flutter boundary estimate.
利用结构奇异值理论将颤振理论模型和试飞数据有机结合起来，进行了颤振边界预测。
The math model, based on real physical one, was modeled according the essential theory and design course of the flutter wing model designing.
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；
ARMAX model method and subspace-based state space method were used to process the flight flutter test data, and identify the flutter modal parameters of aircraft.
论文使用了现代参数辨识技术的ARMAX模型递推法和状态子空间辨识法，对飞行颤振试验数据进行处理，辨识飞机的颤振模态参数。
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.
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。
The aim of this thesis is to analyze the panel flutter mechanism and establish a mechanical model for panel flutter analysis and this work is the basis of panel flutter control studies.
本文的目的就是对壁板的热颤振特性进行系统深入的分析和研究，为高速飞行器的壁板结构的防颤振设计和壁板颤振抑制的研究建立理论基础。
Pass to incorporate organically the flight test data and the system model, make use of the structured singular value theories proceed the flutter boundary estimate.
一种新的颤振分析方法——鲁棒颤振裕度法被介绍，它利用结构奇异值理论将系统模型和试飞数据有机结合起来进行颤振边界预测。
Model stiffness and support location effect on flutter derivatives is studied in bridge deck section dynamical test.
通过试验研究了桥梁节段模型动力试验中模型本身的刚度和支撑位置对颤振导数测量结果的影响。
A thin plate and the sectional model of the Jiangyin Bridge were tested in turbulent wind in a wind tunnel to extract their flutter derivatives.
在模拟的紊流风场中，应用这一方法对平板和江阴长江大桥的节段模型进行了试验，识别了其气动导数。
As the three-dimensional flutter theory is still not satisfactory at present, it seems necessary to have a full-model wind tunnel test for such a type of bridge.
斜张桥的三维颤振理论目前尚不成熟，有必要进行这种桥型的全模型风洞试验。
Based on a full discretized model of structure, a new full order method for analyzing coupled flutter problems of long span Bridges is proposed in this paper.
基于结构的有限元全物理模型，提出了用于分析大跨度桥梁耦合颤振问题的全阶分析方法。
This paper proposes a new direct flutter analysis of long span Bridges, based on the full order discretized physical model of structure.
基于结构的有限元全物理模型，提出了用于分析大跨度桥梁耦合颤振新的直接分析方法。将系统的气动运动控制方程转化成广义特征值问题。
The identification of flutter derivatives for bridge sectional model has long been a key issue in long-span bridge flutter and buffeting analysis.
长期以来，桥梁断面颤振导数的识别都是大跨度桥梁颤抖振响应分析中的重点和难点问题。
A fourth model may be tested for flutter speed.
第四个模型可用来进行颤振试验。
In this paper, the flutter derivatives of a thin plate model under the simultaneous actions of wind and rain are identified by using the Covariance-Driven Stochastic Subspace Identification method.
对薄平板二维节段模型做了颤振导数识别，颤振导数的计算结果与风洞试验值有很好的一致性。
In this paper, the flutter derivatives of a thin plate model under the simultaneous actions of wind and rain are identified by using the Covariance-Driven Stochastic Subspace Identification method.
本文采用随机系统识别方法，在模拟的风雨共同作用条件下识别了薄平板模型的气动导数。
A new approach of full-mode flutter analysis with double parameters is proposed, which is realized in ANSYS, based on the full-order discretized physical model of structure.
基于结构的有限元全物理模型，提出了一种双参数全模态颤振分析方法，并在ANSYS中实现。
The phenomena "limit cycle" occurred in wind tunnel test for active flutter suppression of a wing model are numerically explained using Harmonic Balance Method.
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。
In this paper, the flutter derivatives of a thin plate model under the simultaneous actions of wind and rain are identified by using the Covariance-Driven Stochastic Subspace Identification method.
气动导数是大跨桥梁结构颤振和抖振分析中确定颤振临界风速和抖振响应的重要依据。
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.
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%。
Some typical numerical results are presented from application of the model to static analysis, dynamic analysis, static aeroelasticity and flutter analysis of a wing-box and a wing.
将等效板模型推广应用到典型机翼结构的静力学、动力学以及静、动气动弹性分析中。
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