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   飞机着陆 的翻译结果: 查询用时:0.582秒
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飞机着陆
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  aircraft landing
     Lastly, according to the mathematic model and feature of aircraft landing, pitching fuzzy controller and pitching fuzzy-PID controller are designed.
     最后,根据飞机着陆阶段的特点和数学模型,分别设计纵向通道的模糊控制器和模糊-PID控制器,利用MATLAB工具对设计的控制器进行了仿真。
短句来源
     Algorithm for Scheduling Aircraft Landing Based on Minimum Cost
     基于最小成本的飞机着陆规划算法
短句来源
     Application of adaptive fuzzy decoupled control for aircraft landing
     自组织模糊解耦控制在飞机着陆中的应用
短句来源
     Design and Implementation of Algorithm on Scheduling Aircraft Landing
     飞机着陆调度排序算法的设计与实现
短句来源
     The paper presents aircraft landing response analysis.
     本文就某型飞机着陆时的结构振动响应作了初步分析。
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  aircraft landing time
     The paper presents an algorithm of scheduling aircraft landing time based on branch and bound(ASAL). Experiments show the proposed method is good at solving the problem of scheduling aircraft landing time.
     该文提出了基于分枝定界的飞机着陆调度排序算法——ASAL,实验证明通过该算法能够很好地解决飞机着陆调度优化问题。
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  “飞机着陆”译为未确定词的双语例句
     Design of a Robust H_∞ Controller for Automatic Landing System of an Aircraft
     飞机着陆系统的一种鲁棒H_∞控制器设计
短句来源
     A PREDICTION FOR LANDING FLYING QUALITIES OF AIRCRAFT USING LOOP SEPARATION PARAMETER METHOD
     采用回路分离参数法预测飞机着陆品质
短句来源
     Present and Development of the Plane Landing System
     飞机着陆系统的现状与发展
短句来源
     Input-output nonlinear equation was processed with feedback linearization of differential geometry in airplane automatic landing control system.
     飞机着陆自动跟踪控制系统,采用微分几何反馈线性化处理非线性方程输入/输出反馈。
短句来源
     THE PROBLEMS OF RANDOM OPTIMAL CONTROLIN AIRPLANE LANDING GUIDANCE
     飞机着陆导引中的随机最优控制问题
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  aircraft landing
Application of generalised neural network for aircraft landing control system
      
We present the basic ideas underlying bond graphs and illustrate the approach by modelling an aircraft landing gear system.
      
Enhanced vision for adverse weather aircraft landing
      
Millimeter-wave short range radar systems have unique advantages in surface navigation applications, such as military vehicle mobility, aircraft landing assistance, and automotive collision avoidance.
      
The problem of the feedback control of an aircraft landing in the presence of windshear is considered.
      
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Force measurements of a whole aircraft model with a delta wing and spanwise blowing were carried out and flow visualization of its semi-span model were conducted in the FL-8 and FL-5 wind tunnels. Several techniques, such as oil flow, water fog, helium bubble, fluorescent minitu-fts, were employed in the flow visualization.The comparative test investigations of two blowing techniques, i.e. the flap spanwise blowing and the blown flap, were completed with the identical model in the same wind tunnel.It is found...

Force measurements of a whole aircraft model with a delta wing and spanwise blowing were carried out and flow visualization of its semi-span model were conducted in the FL-8 and FL-5 wind tunnels. Several techniques, such as oil flow, water fog, helium bubble, fluorescent minitu-fts, were employed in the flow visualization.The comparative test investigations of two blowing techniques, i.e. the flap spanwise blowing and the blown flap, were completed with the identical model in the same wind tunnel.It is found that the flap shoulder vortex is generated over the flap instead of the jet vortex when the spanwise blowing is applied to a flap with large deflection angles. Furthermore, the flap shoulder vortex locates always ahead of the jet. Its vorticity originates from flap shoulder separation. Axial velocity of the vortex is provided by entrainment effect of the jet. It is also shown that the lift augmentation caused by the flap span-wise blowing should not be attributed merely to the boundary layer control and is mainly due to the vortex control.Lift increments originated from the flap spanwise blowing consist of two parts: one acts on the flap, another on the wing. The lift increments which approach to those of the blown flap are obtained at a small jet momentum coefficient(about 0.012) which can be provided by recent engines through selecting optimum configurations and parameters of nozzle. Therefore, it is possible to improve landing performance of aircraft markedly. For the first time a two-branch nozzle is applied, in result the flow over the whole surface of the flap is ameliorated.

本文分析了在FL-8和FL-5风洞完成的一个三角翼飞机模型展向吹气全模测力和机翼半模流态实验中的襟翼展向吹气的气动效果,并且与同一模型在同一风洞中所得到的吹气襟翼结果进行了比较。 明确了在大偏度襟翼上展向吹气,产生的集中涡是“肩线涡”,而不是“喷气涡”。指出涡控制是襟翼展向吹气增升的重要原因,而不应单纯归结为边界层控制问题。通过对喷嘴形状和参数的优选,实现了用当前发动机实际能提供的小的吹气动量系数(约0.012)取得与吹气襟翼相近的升力增量。从而有可能显著地改善飞机的着陆性能。首次采用了“两叉喷嘴”,使整个襟翼面的流动获得改善。由于这项技术结构简单、重量轻、不占用机翼内部空间、生存力强,因此可望成为飞机设计中一种可供选用的动力增升方案。

In this paper, we analyse the effect of the natural characteristics of aircraft such as aerodynamic characteristics engine performance and general configuration on landing approach speed of aircraft. The method for determining the minimal landing approach speed is given. Take example by a supersonic fighter aircraft, the minimal landing approach speed is choosed,

本文分析了飞机固有特性,诸如气动力特性、发动机特性和总体布局等对飞机着陆进场速度的影响,给出了确定最小着陆进场速度的方法,并以一架超音速歼击机为例,选择了它的最小着陆进场速度。

The bounce kinematics of aircraft arresting-hook and arresting gear dynamics produced by strain of nylon or wire rope system is discussed and analysed. The first is bounce kinematics produced by hook motion through a smooth runway or a runway with obstructions following touch-down from a sinking approach; the second is boun-e kinematics during landing with three wheels. The later part of this paper discusses, respectively, arresting gear dynamics of centerline engagement condition and off-center engagement condition...

The bounce kinematics of aircraft arresting-hook and arresting gear dynamics produced by strain of nylon or wire rope system is discussed and analysed. The first is bounce kinematics produced by hook motion through a smooth runway or a runway with obstructions following touch-down from a sinking approach; the second is boun-e kinematics during landing with three wheels. The later part of this paper discusses, respectively, arresting gear dynamics of centerline engagement condition and off-center engagement condition for nylon or wire rope system, and provides an example to describe their effects of arresting gear dynamics for various arresting cable lengths.

本文对拦阻着陆中出现的拦阻钩振动和拦阻动载两大重要问题作了阐明和分析。重点研究和推演了飞机地面滑行中拦阻钩的二类振动运动学及其微分方程特性;钩的阻尼振动轨迹特性;阻尼器参数选择。 在拦索应变动载的研究中阐明了飞机对中拦阻、偏心拦阻、使用不同拦索材料的应变动载特性,并进行了实例计算分析,证实了飞机拦阻的拦索应变动载大小与地面拦阻装置的配置、拦索材料、飞机着陆的偏心程度等有密切关系。

 
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