升力

本文采用神经网络预测控制的方法对抬升力进行控制。

This article predicts the nerve network control method to elevating force to control .

论文以中国高速电气化铁路接触网常用接触线和受电弓动态抬升力试验数据为例，估算出接触线疲劳寿命。

The paper has used experimental data extracted from the catenaries and dynamic elevating force of pantograph which were used in Chinese high-speed electrified railways as an example .

基于B样条的螺旋桨升力面设计

Propeller design by lifting surface theory based on B-spline

平板有升力绕流的latticeBoltzmann模拟

Numerical Simulation of Flat Plate Flow with Lift via Lattice Boltzmann Method

应用DES（detachededdysimulation）方法数值模拟了3种不同失速类型的翼型的升力特性。

Detached - Eddy Simulation ( DES ) is applied to three airfoils with different stall types .

二维Rankine体升力受邻近壁面干扰的简化算法

Simplified algorithm for wall effect on the lift of 2D Rankine oval

根据P－M理论，计算了五种三翼面飞机和试验模型的诱导阻力因子、升阻比以及翼面升力比等。

On the basis of P-M theory , the calculations are made for the induced drag factor , the ratio of lift to drag , and the ratio of lift in surfaces on five kinds of three-surface planes and test models .

在波浪场中，利用PIV装置进行水平输油管线升力及其周围流场的同步测量。

The synchronistical measurement for marine pipeline lifting force and surrounding current field in wave field was carried out by introducing a PIV system method .

在一定的条件下，Gurney襟翼可以明显增加翼型的升力系数但不过多增加阻力系数。

Under some condition , Gurney flap can increase lift coefficient and lift drag ratio of the airfoil .

通过CFD模拟发现，具有后加载造型、相对厚度大于40%的翼型压力面出现明显分离，造成翼型小攻角失速、升力系数下降。

Turbulent separation occurs on pressure surface at small attack angles for the airfoils which relative thickness more than 40 % , making airfoil stall at small attack angles and the lift coefficient decrease .

结果显示，当Re大于80时，圆柱所受曳力和升力开始振荡。计算所得的脱落频率（Sr）与前人的结果吻合良好。

The results show that the drag and lift forces oscillate for Reynolds numbers greater than 80 . The calculated Strouhal number , a parameter characterizing the oscillations , agrees well with established results .

论文针对零航速小展弦比鳍型引起的非线性升力特性，研究适用于常规减摇模式的鲁棒自适应神经元控制律，分析其Lyapunov稳定性。

For solution of the nonlinear lift characteristic induced by the low aspect ratio , a robust adaptive neuron control law adequate for the conventional anti-roll mode is developed , and its Lyapunov stability is proved .

但大颗粒与壁面碰撞后，必须连同考虑颗粒旋转及Magnus升力的作用。

But for the larger particles and those collided with wall surface in particular , particle rotation and action of Magnus lift force must be considered altogether .

仿真实验表明基于Singh算法的直接力控制器能解除无人机在飞行过程中某些模态运动之间的交叉耦合，并能精确实现纯直接力、俯仰指向等3种模式的直接升力控制。

This implies that the DFC controller can decouple the movement modes and can accurately calculate the 3 modes of the direct lift control such as direct lift and pitch pointing .

最终发现：即使在设计泵与母型泵性能相差较大的情况下，经过CFD改进升力法设计的轴流泵达到预期目标，满足性能需求。

Finally we found that , the performance of the axial-pump using the improved lifting design method based on CFD can attain the prospective goal , even there exists great difference of performances between the parent pump and the designed one .

介绍了超临界CO2流体热力学特性和管内的换热特性，指出了影响换热的主要因素有热流密度、浮升力、压力、管径、流量、润滑油等。

This paper introduces the thermodynamics properties and heat transfer in-tube flow of supercritical carbon dioxide , and points out that the main factors to influence heat transfer are heat flux , buoyancy , pressure , tube diameter , mass flow rate and lubricant .

采用升力面涡格法对系列大毂径MAU型螺旋桨进行敞水性能计算，运用理论算法扩充了MAU型螺旋桨图谱。

The open water characteristics of a series of large hub-diameter Ratio MAU propellers are calculated by using lift-surface method to expand the chart of MAU-series propeller .

上海交通大学曾应用升力面理论涡格法和无升力体面元法，探索了POD推进器的定常水动力性能预报理论方法。

In Shanghai Jiaotong University , a numerical method has been established to predicate the steady performance of POD propulsion , which the propeller blades are calculated by a vortex lattice method and the pod including its strut by a boundary element method for non-lifting bodies .

洛克希德·马丁公司正在研制的低成本、新一代、多用途联合攻击战斗机F-35飞机的推进系统由F135发动机/F136发动机和轴驱动的升力风扇等部件构成。

The propulsion system of Lockheed Martin low-cost multi-role next-generation F-35 Joint Strike Fighter consist of the F135 / F136 engines and common propulsion system components .

对于管内径为0.27mm的微细圆管，当进口Re高于104时，浮升力的影响可以忽略，对流换热系数的变化完全由物性的变化尤其是cp的变化导致。

For the tube with the diameter of 0.27 mm , when the inlet flow Re exceeds 104 , the experimental result indicates that has not influence . The variation of convection heat transfer coefficient is attributed to the variation of thermal properties , especially the variation of cp.

为了探索适用于长航时飞行器的翼型设计思想、方法和技术，进行了新型高升力及失速特性缓和的BUAAK1BUAAK2翼型的设计研究。

Design research of high lift , mild stall airfoils ( BUAA K1 / BUAA K2 ) was conducted in order to investigate their design strategy , methods and technology for a long endurance aircraft .

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 .

通过二维Rankine体、三维扁卵形体、三维回转体的近壁面干扰计算，解释了试验中观察到的钝体升力效应、随间距减小产生的吸力下降现象以及阻力变化等。

Through the interacting computations of 2D Rankine oval , 3D flat ovoid and 3D ovoid near wall , some special characteristics observed in experiments are explained , e.g. the lifting effect of blunt-end body , suction-drop phenomena and variation of drag .

IPSA模型对每一相求解N-S方程，并考虑水-气体两相间的相间相互作用，包括相间阻力、相间升力、相间压力和虚质量力。

The IPSA model solves the Navier-Stokes equations of each phase with the interphase interactions between two phases of water and air , including the interphase drag forces , interphase lift forces , interphase pressure and virtual mass forces .

本文应用有限基本解法（涡格法）及联合流场概念，计算出CK-1机带翼梢小翼的升力系数及诱导阻力系数。

The lift coefficient and induced drag coeffcient of the CK-1 wing with winglets are calculated in . this paper by the vortex-lattice method and the concept of united flowfield being used .

应用现代螺旋桨升力面元方法计算冲压空气涡轮的气动性能，叶片采用单层涡模型，尾涡采用与Goldstein假设一致的刚性尾涡，将螺旋马蹄尾涡视为开口涡环以便于编程。

The modern propeller lifting surface method has been applied to calculating the performance of Ram Air Turbine , and a single layer vortex model is adapted to the blade , the wake is modeled to rigid cylinder wake coincided with Goldstein hypothesis .

应用Murman-Cole的有限差分法，求解具有纵向大扰动而横向小扰动的跨音速轴对称速势方程，由此计算旋转体跨音速零升力时的压力分布和波阻力，以及激波位置。

A transonic axisymmetrical potential equation with large disturbance in the free stream direction and small disturbance in the transverse direction is solved by using the Murman-Cole schemes of finite differences .

绝热两相流的数值模拟结果表明颗粒在壁面的跟随性随粒径的增大而下降，近壁区Saffman升力的存在对两相流动的轴向速度影响不大，但对颗粒的浓度分布有一定的影响。

The numerical simulating results of the gas-particle two-phase flow in duct show that the velocity difference of the gas and particle in the near-wall region would increase as the diameter of the particle enlarge .

数值模拟了流场的变化特征，分析了各种攻角下，具有方形截面的高层建筑的升力系数、抗力系数和Strouhal数。

The present discrete vortex model combined with singularity method can be easily applied to a building with complicated shape . The characteristics of wind field are numerically simulated , the lift and drag coefficients and Strouhal numbers are analyzed for several angles of attack .

升力式再入飞行器的神经网络自适应逆控制系统设计

Neural Network and Adaptive Inversion for Lifting Re-entry Flight Control Design