大迎

多段翼型大迎角分离流动的DELAYEDRANS/LES混合算法

DELAYED RANS / LES Method For High Attack Angle Flow over Multi-element Airfoil

跨音速大迎角Euler方程数值分析

A numerical solution of transonic Euler equation at high angles of attack

本文采用求解N－S方程方法计算了轴对称钝头倒锥体外形的跨声速大迎角层流流动。

The computation of the transonic flow at high angles of attack for the blunt reverse conical body by solving N S equations is made .

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 .

基于RBF神经网络的大迎角机动空空导弹控制系统设计

A / A Missile Control System Design for High Angle of Attack Maneuvering Based on RBF Neural Networks

大迎角体涡、翼涡干扰的Euler方程数值模拟

Numerical Simulation of the Interaction for the Wing-and Body-vortices at High Angle of Attack Using Euler Equations

旋成体大迎角分离流的Euler方程数值模拟

Numerical Simulation of Separation Flow on Bodies of Revolution at High Angle of Attack Using Euler Equations

基于LS-SVM飞机大迎角动态辨识方法研究

A High Angle of Attack Dynamical System Identification Algorithm Based on LS-SVM

研究表明：MEMS器件对控制大迎角细长旋成体非对称涡和复杂流场具有良好的控制能力。

The research indicated that MEMS device generate excellent control effect on asymmetric vortices over slender body as well as on complex flow field .

通过数值求解雷诺平均NS方程，研究了二维翼型的大迎角粘性绕流，并分析了翼型的近场旋涡分离流动特性。

Turbulent flows over an airfoil at high angles of attack are investigated numerically by solving the Reynolds averaged Navier Stokes equations .

F-16飞机大迎角飞行偏离/尾旋特性分析

Analysis of Departure / Spin Characteristics of F-16 at High Angle of Attack

本文运用频率域建模法，分别建立了飞机大迎角滚转运动的Fourier变换模型及非线性代数模型，并从数学模型中提取动导数。

The method of modeling in frequency domain is used to establish the Fourier model and nonlinear algebra model of a rolling aircraft model at high angle of attack . The general dynamic derivatives are extracted from these mathematical models .

为验证设计的有效性，在大迎角和两种飞行条件下，将非线性H∞飞行控制系统与线性H∞飞行控制系统的性能进行了对比闭环仿真研究。

To verifying the valid ability , closed simulation comparisons between the performance of the nonlinear H ∞ flight control system and the linear H ∞ flight control system are made on the basis of aircraft dynamic response at high angles of attack and two flight conditions .

将分支分析与突变理论方法（BACTM）和模糊逻辑控制（FLC）方法相结合，形成BACTMFLC方法，实现飞机大迎角下的动力学特性分析和模糊控制律设计一体化。

The bifurcation analysis and catastrophe theory methodology-fuzzy logic control ( BACTM-FLC ) method is developed from bifurcation analysis and catastrophe theory methodology and fuzzy logic control .

基于多重线涡模型（MLVM），本文建立了一种计算机时少、收敛性强的适用于大迎角涡流势流数值模拟的迭代算法。

A robust iterative method suitable for the numerical simulation of vortex flows at high angles-of-attack is established based upon the multiple line-vortex model ( MLVM ) .

介绍了2.4m跨声速风洞的大迎角试验机构、试验技术，以及大迎角标模（CT-1）和某四代机等两个模型的调试试验情况。

The tests in 2.4m transonic wind tunnel on the high alpha setup and tests technology with two models , including the CT-1 model and an advanced fighter model , are introduced in this paper .

试验研究初步揭示了航天飞机OV102模型高速大迎角俯仰运动的动态气动特性。

The dynamic aerodynamics performances of OV102 space shuttle model pitching oscillation in large amplitude in high speed is simply presented in the paper .

试飞结果表明，JL8飞机具有良好的大迎角特性及低速和高速失速特性。

The results of flight test show that JL8 aircraft has very good characteristics of high angle of attack , low speed and high speed stalls .

利用建立的非线性飞机模型和大迎角控制律，对两种典型的过失速机动&眼镜蛇机动和Herbst机动进行了仿真研究，进一步揭示了飞机过失速机动的飞行力学机理。

Basing on the fighter nonlinear model and the high-attack-angle control law , the dynamic characteristics of post-stall maneuver are studied , with the successful simulations of two typical post-stall maneuver - " Cobra " and " Herbst " maneuver .

针对某静不稳定飞机的非线性动力学模型，采用分叉与突变理论（BACTM）计算了常规控制面变化的飞机本体平衡曲线，揭示了其固有的在大迎角下的开环运动特性。

Bifurcation Analysis and Catastrophe Theory Method ( BACTM ) was applied to a nonlinear dynamics model of an inherently static unsteady aircraft to calculate the equilibrium curve while regular control surfaces deflected .

大迎角非对称载荷的减缓和控制

The alleviation and control of the asymmetry load at high angle-of-attack

细长尖头旋成体大迎角非对称涡系结构

Asymmetric vortex structure of slender revolution at high angles of attack

大迎角涡流的同步迭代算法

Synchronous iterative method for computation of vortex flows at high angles-of-attack

大迎角非线性飞行动力学（一）

Nonlinear flight dynamics at high angle of attack ( 1 )

先进战斗机大迎角运动特性分析和试验

High Angles of Attack Character Analysis and Test for an Advanced Fighter

超声速大迎角分离流中三种湍流模型的比较研究

Comparison of three turbulence models in supersonic high-attack-angle separated flows

大迎角粘性复杂流场的数值模拟

The Numerical Simulations of Complex Viscosity Flowfield under Large Angle

小展弦比飞机的大迎角涡流计算

Simulation of Vortex Flows over Low Aspect Ratio aircraft at Large angle

飞机大迎角机动飞行控制律研究

Control law study of aircraft maneuvers at high attack angle

尾撑大迎角试验技术研究

Study on high angle of attack test technique of rear sting supports