The tests are conducted on a wing model with large aspect ratio.
试验是在大展弦比机翼颤振模型上进行的。
The ASE system for a wing model is applied to reveal the mechanism of the method by comparing the full model with the reduced order model.
以机翼气动伺服弹性系统为对象，比较了降阶前后模型变化情况。
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；
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%。
On the basis of former rigid wing model and consideration of the velocity change and the distortion of wing plane, a flapping model is developed.
在原有匀速刚性模型的基础上，提出考虑了扑翼扑动速率变化和形状变化的柔性扑翼模型，使之更接近鸟翼真实扑动情况。
If we make a wing model which is similar to sliding mass, we can determine aerodynamic parameters by the wind tunnel testing and thus calculate the lift.
将高速滑体制成相似的机翼模型，进行风洞试验，即可测定滑坡凌空飞行的空气动力学参数，从而计算大型高速滑坡凌空飞行的空气动力升力、飞行速度和飞行距离等。
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。
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。
Based on the data, the RCS distribution characteristics of the flying wing model with azimuth are investigated and the approach of stealth design by shaping is discussed.
在此基础上，分析了飞翼外形rcs随方位角分布的特点以及其外形隐身设计的特点。
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。
Had the French inventor tried to model his plane on every detail of a bird's wing, he would not have succeeded in flying it.
要是那个法国发明家力图模仿鸟翼的每个细节来造他的飞机的话，他就不会使它飞起来。
Applying the reverse reconstruction technique to quantify the geometry information about the nonsmooth leading edge shape of the long eared owl wing, a bionic analogy air foil model was built.
应用逆向重构技术，对长耳鸮翼前缘非光滑形态特征几何信息进行量化，并建立仿生类比模型。
The model, mostly completed in 2003, represents the USS Enterprise and Air-Wing 11 during the ships' 1989 cruise.
在1989船的巡航模式，大多是在2003年完成，代表企业号航空母舰和空军翼11。
As an example of large sized structural component, the mechanical model of load calibration test of an airplane wing was analysed.
以飞机机翼等大型结构为例，探讨了大型结构部件载荷标定试验的力学模型。
The problems of uncertainty modeling and model validation of a wing aeroelastic system are investigated.
研究了机翼气动弹性系统的不确定性建模及其模型确认问题。
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。
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。
Velocity gradient, pressure gradient and circulation gradient are used to model the separated vortex flow field over a leading edge delta wing.
用速度梯度、压力梯度和环量梯度模拟大攻角尖前缘三角翼流场。
Based on model design and rotary wing design of helicopters, this paper introduces a multi targets inverse eigenvalue problem and gives a parallel method.
由模型设计和直升机旋翼设计问题出发，归纳出一类多目标逆特征值问题并提出一种适合在并行计算机上实现的并行算法。
The pressure field measurement results on the wing surface of airplane model by luminescence pressure sensor (LPS) technique and classic tap technique in high speed wind tunnel are presented.
介绍了国内首次在高速风洞中使用荧光压力传感器(LPS)技术对飞机模型机翼表面压力场测量的初步结果。
So you have to work from pictures of the real boat and model and wing it.
所以，你必须从工作的照片，真正的船模型和机翼。
NASA's Glenn Research Center dedicated a model of the hybrid wing body, a futuristic aircraft concept, on July 8, 2009.
美国航空航天局格伦研究中心展出了混合型飞行器模型——下一代未来飞行器的概念模型。
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。
The glider model can replace the wings, the wing bracket and the wing compressed sheets freely and conveniently.
本模型飞机可随意更换机翼、翼台支架以及机翼压片，更换方便。
The glider model can replace the wings, the wing bracket and the wing compressed sheets freely and conveniently.
本模型飞机可随意更换机翼、翼台支架以及机翼压片，更换方便。
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