气动力

平板气动力的CFD模拟及参数研究

CFD simulation and parameter study on aerodynamic force of flat plate

该榴弹CAD软件具有以下一些功能模块：计算弹丸质量、极转动惯量等构造特征数，计算内、外弹道特性，计算气动力，威力等。

The software package have some functions as follows : calculating the shrapnel 's diagnostic parameters such as the mass and the pole moment of inertia , the inner and outer ballistic characteristic , the aerodynamic force and power , and so on .

像用气动力控制那样，如果需要滚动控制，那么就增加了复杂性。

There is , as with aerodynamic control additional complication if roll control is required .

因此，本文的DISC设计法为气动力设计提供了一个行之有效的方法。

Thus , the DISC design method offers an efficient approach to aerodynamic design .

TR型磁浮列车气动力特性数值计算研究

Research on Numerical Calculation for Aerodynamic Characteristics of the TR Maglev Train

空空导弹反作用侧向力/气动力复合控制系统设计增强型ABS控制系统及其对汽车侧向稳定性的影响

Reaction jets / aerodynamics blended control system design for air-to-air missile Improved ABS and its influence for vehicle lateral stability

基于Volterra级数的跨音速非定常气动力建模

Volterra series based transonic unsteady aerodynamics modeling

数据采集与处理作为H高超声速风洞气动力试验的关键环节之一，直接影响到后期数据分析的效率和武器选型和正确性。

Data acquisition and processing is one of important part of the aerodynamic test in wind tunnel , because it affects the efficiency and veracity of data analysis and weapon design .

提出了用于加速气动力形状优化过程的分级型Nash基因算法。

New Hierarchical Genetic Algorithms ( HGAs ) mixing Nash game are presented to speed up the optimization of aerodynamic shapes .

基于ADRC的直接侧向力/气动力复合控制系统设计

Design of Lateral Thrust and Aerodynamics Blended Control System Based on Auto Disturbance Rejection Controller

本文基于Navier-Stokes方程，采用非定常流动的预处理方法，求解了翼伞在后缘下拉条件下的二维和三维气动力特性。

Computation of 2-D and 3-D flows past ram-air parachutes was conducted using an unsteady time-derivative preconditioning method for Navier-Stokes equation .

对所设计的EFP战斗部进行成型过程、气动力系数和飞行弹道计算。

The process of formation , aerodynamic coefficient and trajectory of EFP are calculated .

运用基于非定常CFD的气动力辨识技术，得到跨声速非定常气动力降阶模型。

Based on the aerodynamic identification technique in which the unsteady CFD is used , the unsteady aerodynamic reduced order models ( ROM ) are constructed .

采用弹体旋转飞行技术，虽然产生Magnus侧向力，但有效地克服了气动力的随机性。

Although producing the Magnus side force , it can get over the random properties effectively using body revolving techniques .

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 .

此外，本文对飞行仿真进行了研究，用最小二乘方法拟合了气动力特性曲线，在此基础上利用Runge-Kutta方法建立了飞行方程的数值解算程序，并设计了可视化程序。

Aerodynamic characteristic curves are fitted by the least-squares fitting method . Flight equations are solved by Runge-Kutta method , and the visualized program is designed .

发展了一种运用定常CFD方法和活塞理论求解超音速、高超音速非定常气动力的新方法&当地流活塞理论。

Employing Euler based steady solution and piston theory , a new method ( we call it local piston theory in this paper ) to solve supersonic or hypersonic unsteady loads has been developed .

根据势流理论对飞艇艇身线性气动力进行分析计算，由于飞艇艇体是旋成体，故根据Allen的横流阻力理论对其所受的非线性气动力进行计算；

The linear aerodynamic forces of airship hull were calculated in terms of Munk airship theory . The linear aerodynamic forces of airship hull were calculated by Allen viscous cross flow theory .

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 .

通过与非定常Euler方程的比较，证明该气动力模型具有较高的数值精度，放宽了原始活塞理论对翼型厚度、迎角、马赫数的限制。

The results presented by this model agree well with those of solving unsteady Euler equations . This model greatly reduces the limitations of the classical piston theory on flight Mach number , airfoil thickness , and angle of attack .

因此，将计算区域分割为球体、圆柱、圆环、圆桶等简单规范的区域，然后进行了结构化网格划分，并用FLUENT软件对制导炮弹模型气动力参数进行了计算。

Therefore , the computational region is divided into the sphere , cylinder , rings , drums and other simple specification of the region , followed by a structured mesh . And the guided projectile with FLUENT software aerodynamic model parameters were calculated .

270km·h~（-1）高速列车气动力性能研究

The Analysis and Evaluation on the Aerodynamic Behavior of 270 km · h ~ ( - 1 ) High-speed Train

研究一种蝴蝶（Morphopeleides）前飞时的气动力特性.在运动重叠网格上数值求解Navier-Stokes方程，对蝴蝶前飞时左、右翅膀的拍动运动以及跟随身体一起的俯仰运动进行计算。

The aerodynamics force generation of a butterfly ( Morpho peleides ) in forward flight was studied , using the method of numerically solving the Navier-Stokes equations in moving overset grids .

应用强迫振动装置上的天平测量节段模型的气动力时程曲线，实现了随攻角连续变化三分力系数的测量，并由升力时程曲线推算了多组H型和矩形断面的Strouhal数。

The aerodynamic forces of section model are measured by the force balance of forced vibration equipment , which is further used to estimate the Strouhal number of H-shaped and rectangular sections , and the measurements of steady aerodynamic force coefficient continuously varying with attack angles are realized .

模型发散动压的计算是利用NASTRAN的柔度法和自行开发程序的模态法进行的，两种方法均采用亚音速偶极子格网法气动力理论的定常部分进行气动力的计算。

The divergence pressures of these models were calculated by the flexibility method of MSC / NASTRAN and the mode method developed by the authors , while the steady aerodynamics of the subsonic Doublet Lattice method is used for aerodynamic calculation in both the methods .

在此基础上，计算了中国气动力研究与发展中心2.4m×2.4m引射式跨声速风洞第二扩散段在不考虑喷流干扰及常规运行状态下的流场。

Since the confidence of the program was proved , the second diffuser flow fields of the CARDC 2.4m × 2.4m injection driven transonic wind tunnel was calculated under the normal and high pressure conditions without the disturbance of injector .

首先通过桨叶剖面速度三角形及气动力分析给出了1P载荷与测量应变的关系，然后通过地面试验和飞行试验进行了验证。

Firstly , the velocity triangle variation and aerodynamic analysis of blade cross section airfoil give out the relation between the 1 P loads and the measured strains . Then ground and flight tests are carried out to verify the proposed method .

用声子气动力论模型的分析结果与NEMD模拟相一致，表明纳米单晶硅薄膜中声子平均自由程显著减小。

The analytical results of the thermal conductivity based on the kinetic theory of phonon gas model agrees well with the result of NEMD simulation , which indicates that the phonon mean free path in nanoscale silicon films is significantly decreased .

这种铠装热电偶短时工作上限为900℃，长期工作上限为800℃，时间常数小于0.3s，能经受发动机振动和高温气动力的作用而可靠地工作。

The upper temperature limit of this kind of MST is 900 ℃ for short-time use and 800 ℃ for long-time use . Its time constant is less than 0 . 3s and it operates reliably in engine under vibration and hot aerodynamical conditions .