定气

马苏尔神定气若地指挥乐团。

Masur led the orchestra with assurance

数字PID控制器的设计采用传统的定气隙控制，利用经典的极点配置方法设计了状态反馈控制器，仿真结果表明是完全可以实现稳定悬浮。

Traditional fixed airgap control are adopted in the design of the PID controller , the state feedback controller are designed by using classical pole collocation method . The simulation result demonstrates that this method meets the needs .

从而提出了定气圈式纺纱理论，并在这个基础上对细纱机的自动控制从硬件和软件上进行了设计。

Then a stable loop theory from the research result is brought forward , on this ground , we design automated control system from hardware and software .

中国人从上到下都是神定气闲，就是受过欧洲教育的人也不例外

" The chinese , from the highest to the lowest , have an imperturbable quiet dignity , which is usually not destroyed even by a European education "

与定气隙控制策略比较，两者均能实现大气隙稳定悬浮，基于零功率控制策略的控制系统能耗明显减少，悬浮稳定性稍有下降。

Compared with the system based on fixed gap control strategy , the hybrid suspension system based on zero power control strategy consumes much less energy with a little loss in suspension stability , although both of the systems provide stable suspension with large air gap .

用Green函数法计算每个谐波引起的非定常气动力；

The unsteady aerodynamic load due to each harmonic motion is calculated by the Green ′ s function method ;

本文对基于输出反馈RBF神经网络的大迎角非定常气动特性辨识方法进行了研究。

The unsteady aerodynamic identification method based on RBF neural network is studied in this paper .

跨声速机翼操纵面非定常气动力Euler方程计算

Unsteady Transonic Flow Computation for a Wing with Control Surface Deflections by Euler Equations

基于Volterra级数的非线性非定常气动力降阶模型

Reduced-order model based on volterra series in nonlinear unsteady aerodynamics

基于Volterra级数的跨音速非定常气动力建模

Volterra series based transonic unsteady aerodynamics modeling

运用Fourier函数分析法逼近大攻角非定常气动力阶跃响应模型。

A nonlinear unsteady indicial response model of aerodynamic coefficient could be approximated by the use of Fourier analysis function at high angle of attack .

探讨了CFD／CSD耦合技术预测非线性非定常气动力的基本原理，为非定常气动力降阶模型准备数据。

Investigated the basic theory of the coupled CFD / CSD simulation of nonlinear unsteady aerodynamics and prepared basic data for reduced order model .

还根据流场计算得出的叶片上非定常气动载荷，用ANSYS软件进行了叶片的动应力计算，由于较为接近实际工况，所得动应力值可能具有一定的工程参考价值。

As an application , the dynamic stress of the blade was analysed with ANSYS based on the computation of unsteady flow . The result may be useful in the engineering practice .

通过与CFD计算结果和实验结果的比较证明该综合工程方法具有较广的应用范围，并将其推广到非定常气动力的计算。

Comparing with CFD results and experimental dates , the combined engineer method has a practical application and we extend it to solve the unsteady pressure distribution of supersonic or hypersonic aircraft .

通过CFD（computationfluiddynamics）技术计算得到由结构变形产生的非定常气动力阶跃响应可辨识出Volterra核，由此得到频域的广义非定常气动力影响系数。

Using the unsteady aerodynamics step responses due to the structural deformation calculated by CFD ( computation fluid dynamics ) technique , the Volterra kernels are determined , and the generalized unsteady AIC ( aerodynamics influence coefficients ) in frequency-domain are obtained .

研究了Volterra级数在非定常气动力降阶模型中的应用，特别是Volterra核的计算，并对Volterra级数模型的适用范围和精度进行了评价。

Investigated the reduced order model for nonlinear unsteady aerodynamics based on Volterra series , especially the identification method of the Volterra kernels and studied the application domain and accuracy of the model .

结果表明，Volterra级数方法得到的非定常气动力模型能够反映一定的跨音速气动特性，颤振计算与CFD-CSD（CFD-ComputationStructureDynamics）的计算结果吻合很好。

The results show the aerodynamics model educed by the Volterra series approach can reflect the features of transonic aerodynamics . The Volterra series approach coincides with the CFD-CSD ( computation fluid dynamics-computation structure dynamics ) method in flutter analysis .

本文以CFD理论为基础，建立了一套基于非结构运动对接网格技术求解带旋转边界模型流场的分析方法，并用该方法对旋翼/机身非定常气动干扰问题进行了计算。

Based on the method of the CFD , a technique of unstructured dynamic patched grid is developed to solve unsteady flow that contains rotational boundary . Unsteady aerodynamic problem of rotor / fuselage interference is calculated by using this method .

本文介绍计算亚声速谐振薄翼非定常气动载荷的点偶极子法（DPM）。

In this paper , the doublet point method ( DPM ) is introduced , which is used for calculating the unsteady aerodynamic loadings on harmonically oscillating thin wings in subsonic flow .

使用这种方法计算了F-5机翼在来流马赫数为0.9和0.925时的定常气动力和操纵面振荡的非定常气动力。

As a computational example , the steady and unsteady aerodynamic force of F-5 wing with control surface oscillations is considered .

研究了基于Volterra核直接建立非定常气动力状态空间模型的方法，包括线性状态空间模型和双线性状态空间模型，并提出了将其用于ASE系统建模的一般方法。

Investigated the direct model construction method of unsteady aerodynamics state space equation from Volterra kernels , including linear state space model and bilinear state space model . The general model construction method for ASE was brought forward .

采用亚音速偶极子格网法计算非定常气动力，用状态空间法计算翼面颤振速度，利用最佳控制理论进行最优控制设计，结构固有振动用谱变换Lanczos方法求得。

The optimal control theory is introduced to design the control law . Natural vibration modes are obtained by spectral transformation Lanczos method . The FEM is used to simulate the wing structure .

采用Theodorsen非定常气动理论构建气动模型，获得机翼在平衡位置附近的非线性颤振方程，并利用v-g法判定机翼颤振稳定性。

Flutter equations are obtained by using Theodorsen 's unsteady aerodynamic theory , then flutter stabilities at various wind speeds are determined by the v-g method .

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 .

基于Theodorsen理论和Wagner函数，提出了不可压缩流作用下三自由度二维翼段任意运动非定常气动力表达式。

Based on Theodorsen 's theory and Wagner 's function , the expressions of unsteady aerodynamic forces for arbitrary motions of a two-dimensional airfoil with three degrees of freedom are presented . It is assumed that the airfoil is subjected to an incompressible flow .

分析模型采用了当量铰、弹性约束的刚性桨叶和弹性机翼假设，采用Pitt-Peters动力入流模型计入了非定常气动力的影响。

Assumptions of equivalent hinge with spring restrained , stiff rotor blades and elastic wings are applied , and Pitt-Peters dynamic inflow model is taken into account in order to include unsteady aerodynamics .

振动襟翼的非定常气动力特性研究

The investigation on unsteady Aerodynamical Characteristics of an oscillating trail-edge flap

风力透平叶片振动时的三元非定常气动力

Three dimensional unsteady aerodynamic force on a vibrating wind turbine blade

直升机旋翼非定常气动力及结构动力响应计算

Calculation of Unsteady Aerodynamic Load and Structural Dynamic Response of Helicopter Rotor

关于一维非定常气&固二相流特征理论的讨论

On the Characteristic Theory of One-Dimensional Unsteady Gas-Solid Two-Phase Flows