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俯仰     
相关语句
  pitch
    Supersonic/Hypersonic Pitch Oscillating Derivatives of Two Dimensional Flat Plate at Arbitrary Angles of Attack
    任意迎角二维平板的超声速和高超声速俯仰振动导数
短句来源
    A STUDY OF RELATIONSHIPS BETWEEN FIGHTER PITCH TRANaENT AGILITY AND FLYING QUALITIES
    战斗机俯仰瞬态敏捷性与飞行品质关系研究
短句来源
    Prediction of Pilot Induced Oscillations in Pitch Tracking Task for Modern Aircraft
    现代飞机俯仰跟踪时诱发振荡预测分析
短句来源
    The Study of Carrier Rocket Pitch Program Control System
    运载火箭俯仰程序控制系统的模拟研究
短句来源
    Signal Reconfiguration Method for Aircraft's Pitch Angular Rate
    飞机俯仰速率信号重构方法研究
短句来源
更多       
  pitching
    PITCHING DERIVATIVES OF WING IN SUPERSONIC AND HYPERSONIC STREAM——METHOD FOR LOCAL FLOW PISTON THEORY
    超声速和高超声速机翼俯仰导数——当地流活塞理论解法
短句来源
    Gust Load Calculation of Canard Airplanes with Pitching
    考虑俯仰时鸭式布局飞机突风载荷系数计算
短句来源
    Experimental Investigation on Unsteady Aerodynamic Characteristics of Rapidly Pitching Delta Wings
    快速俯仰三角翼的非定常空气动力实验研究
短句来源
    Study of the dynamic stability of a pitching unfinned reentry capsule
    不带稳定翼飞船返回舱俯仰动稳定性研究
短句来源
    The visualization of vortex field of unsteady motion for 2-D airfoil——2 pitching motion and heaving/pitching composite motion
    二维翼型非定常运动的涡流场显示——2俯仰运动和沉浮/俯仰联合运动
短句来源
更多       
  the pitch
    Study on Control and Stability of a Kind of Satellite with Large-angle and Rapid Maneuvering Appendage in the Pitch Plane
    带快速大角度机动附件的卫星在俯仰平面内的运动控制与稳定性研究
短句来源
    3. The normal fuzzy attitude control system of the pitch channel is designed based on rigid model of a launch vehicle, which is used to send satellite A. In order to improve the normal fuzzy controller's performance, no-quantification analytic fuzzy method is adopted; and is validated by simulation.
    3.以现有的运载火箭发射A卫星为背景,针对某一飞行段俯仰通道,进行了采用一般模糊控制方法进行刚体运动模型的姿态控制系统设计和仿真,并与采用经典控制方法设计的系统仿真结果比较,对模糊系统中存在的振荡现象,取消量化取整、采用解析方法对模糊控制器进行改进,仿真结果表明是有效的。
短句来源
    The signals of the pitch moment:M_z and the pitch angleθaresatisfactory.
    力矩 M_z 和俯仰角θ的输出信号是非常满意的,已经为某预研型号提供了(?)
短句来源
    The pitch moment M_z andthe pitch angleθof model are measured by strain gage bridge.
    模型的俯仰力矩 M_z和俯仰角θ值分别用应变电桥测量。
短句来源
    This paper presents mathematical models and control laws in maneuvering flight for simulating the pitch agility of modern high maneuverable fighter.
    建立了现代高机动性能战斗机俯仰敏捷性仿真计算数学模型和机动飞行时的操纵动作,以F-16战斗机为例,计算并讨论了初始飞行状态以及飞行控制系统参数对战斗机俯仰敏捷性的影响。
短句来源
更多       
  a pitching
    Study of the dynamic stability of a pitching unfinned reentry capsule
    不带稳定翼飞船返回舱俯仰动稳定性研究
短句来源
    The starting flows past a pitching oscillation Karmam-Trafftz airfoil with 0.12 relative thickness are investigated by numerical calculations for the unsteady N-S equations at Reynolds number 1 000. The emphasis of this study is put on the relation between the complicated vortex structure and the pressure distribution on the body.
    通过对非定常N-S方程的数值求解,研究了最大厚度为12%的Karman-Trafftz翼型在Re数为1000时的大迎角俯仰振动。 其中着重分析了旋涡结构与表面压强分布的关系。
短句来源
    The frequency of unsteady wall pressure at the optimum measuring pressure point is in agreement with frequency of delta wing model undergoing a pitching oscillation. The time lag phenomenon among optimum measuring pressure points is presented.
    风洞洞壁上最佳测压点非定常压力变化频率与模型正弦俯仰振荡频率一致 ,各最佳测压点间呈现时间延迟现象。
短句来源

 

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  pitch
Based on the principle of formation of conjugate tooth contour, the equations of the cam's pitch curve are derived.
      
The continuity and symmetry of the cam's pitch curve are also analyzed.
      
The satellite passes chosen for the detailed analysis and modeling lay approximately along the cusp/cleft band from afternoon till prenoon MLT sectors, thus emphasizing the pitch-angle dispersion role with respect to the dispersion due to convection.
      
Some conclusions about the regime of pitch-angular diffusion into the loss cone are made.
      
It is assumed that in such a cascade each i-th system (group) of profiles has its own pitch ti (i=1, 2,?, s) and constant phase shift αi of the oscillations between neighboring profiles.
      
更多          
  pitching
Hydrodynamic problem of the pitching of a catamaran on shallow water
      
The problem of calculating the pitching of multihull vessels, which are widely used in world shipping, has been inadequately developed.
      
In the present paper, the method of [4] is used to solve the hydrodynamic problem of the pitching of a catamaran.
      
The linear problem of inviscid incompressible flow around a high-aspect-ratio wing at an angle of attack and in the presence of steady pitching and rolling rotation is considered.
      
Many-loop hysteresis of the pitching characteristics of an airplane model with a high-aspect-ratio straight wing at Re = 0.33 × 106 is studied.
      
更多          
  the pitch
The satellite passes chosen for the detailed analysis and modeling lay approximately along the cusp/cleft band from afternoon till prenoon MLT sectors, thus emphasizing the pitch-angle dispersion role with respect to the dispersion due to convection.
      
The pitch moment coefficient related to the angular velocity of vibration is determined.
      
A pitch extraction method is considered that employs a decision function whose maximum is greater than the possible spurious maxima of the analyzed signal on the pitch period.
      
We use data on open star clusters (OSCs) from the Homogeneous Catalog of OSC Parameters to determine some of the parameters of the spiral structure of our Galaxy: the pitch angle of the spiral arms
      
An increase in the magnetic field strength is shown to have no significant effect on the pitch-angle distribution of the accelerated particles in the solar chromosphere.
      
更多          
  a pitching
Visualization of flow around a pitching airfoil with a rotating nose demonstrates the technically interesting concept of dynamic separation without dynamic stall.
      
PIV-measurements of the flow above a pitching airfoil were conducted in a transonic wind tunnel.
      
A high-speed phase-locked interferometry system has been designed and developed for real-time measurements of dynamic stall flow over a pitching airfoil.
      
A high-speed phase-locked interferometry system has been designed and developed for real-time measurements of dynamic stall flow over a pitching airfoil.
      
At a pitching rate of 76 million cells per g of mash an ethanol yield of 20.4% (v/v) was obtained.
      
更多          
  其他


This paper presents a numerical solution of unsteady supersonic flows for sideslipping wings by means of the characteristic lines network method of unsteady supersonic sources distributed on the wing plane. This paper provides the oscillating mode of undulatory, pitching and rolling harmonic oscillations of the wings with sideslip angles and the methods to calculate its lift, moment coefficient and dynamic stability derivatives (including cross-coupling derivatives). The dynamic stability derivatives of a typical...

This paper presents a numerical solution of unsteady supersonic flows for sideslipping wings by means of the characteristic lines network method of unsteady supersonic sources distributed on the wing plane. This paper provides the oscillating mode of undulatory, pitching and rolling harmonic oscillations of the wings with sideslip angles and the methods to calculate its lift, moment coefficient and dynamic stability derivatives (including cross-coupling derivatives). The dynamic stability derivatives of a typical wing with sideslip angle equal to zero were worked out both by analytical formula in conformity with the conventional quasi-stationary theory and by the present method, and were compared and examined. The results show that the present method is satisfactory.

本文利用分布在机翼平面上的非定常超音速点源的特征线网格法给出非定常超音速侧滑机翼的数值解。本文给出侧滑机翼作沉浮、俯仰、滚转谐振时的振型以及计算升力、力矩和动导数(包括交叉导数)的计算方法。按本文用非定常理论数值解对典型的无侧滑机翼计算出的动导数与常用的按准定常理论解析公式计算结果进行比较和鉴定,结果表明本文方法是令人满意的。

This paper analyzes the problem of large pitch angle oscillation of a R.P.V.in a flight test,provides a new and quite simple physical simulation method,repeats the oscillation phenomenon in the air successfully,finds out the reasons of failure and presents the improvements.Through several flight tests and applications,it is proved that the conclusions are correct and the improvements are effectual.

本文对无人机在一次研究性试飞中发生的俯仰角大幅度振荡问题作了分析,并提出了一种新的比较简便的实物模拟方法,成功地复现了空中故障现象,找出了失误的原因,提出了改进的措施。经过多次试飞和使用证明,所得的结论是正确的,改进是有效的。

A new type of inertial navigation system combining customary platform type with strap-down one is put forward. In this system the azimuth rate platform without azimuth stabilized loop, coordinate-resolver and azimuth syn chronzer is adopted. The azimuth angles of platform and vehicle will be obtained by an integrator from azimuth rate signals measured by an azimuth gyroscope supported on a horizontal gimbal. This type of inertial navigation system is suitable for vehicles without large-pitching maneuver, such...

A new type of inertial navigation system combining customary platform type with strap-down one is put forward. In this system the azimuth rate platform without azimuth stabilized loop, coordinate-resolver and azimuth syn chronzer is adopted. The azimuth angles of platform and vehicle will be obtained by an integrator from azimuth rate signals measured by an azimuth gyroscope supported on a horizontal gimbal. This type of inertial navigation system is suitable for vehicles without large-pitching maneuver, such as transports, aerodynamic and ballistic missiles.Operational principles of the azimuth rate platform, mechanization equations, distinguishing features of initial alignment, and calibration and compensation for drifts of gyroscopes are discussed in this paper. Error propagation characteristics caused by various error sources for navigation positioning, velocity and attitude are simulated on a digital computer. Simplicity in platform structure, small volume and weight, high reliability, possibility of calibration and compensation for drifts of the azimuth gyroscope are the distinctive advantages of this inertial navigation system.Moreover, by using a specific optical system referring to given azimuth angles of land marks and geographical latitudes, it is possible to accomplish not only fast alignment, but also calibration and compensation of horizontal gyroscope.

本文提出一种把平台式和捷联式惯导系统结合在一起的新的惯性导航系统。在该系统中使用的速率方位平台没有方位稳定回路、方位坐标分解器及同步器。平台和运载器的方位角是根据由水平环架支承的方位速率陀螺讯号借助积分运算得到的。这种惯导系统适用于运输机、飞航式及弹道式导弹等不作大角度俯仰机动的运载器。文中叙述了方位速率平台的工作原理、力学编排方程、初始对准的特点以及陀螺漂移的标定和补偿;同时对各主要误差源所引起的姿态、速度和导航定位误差的传播特性进行了模拟计算。在结论中指出:平台的结构简单、体积小、重量轻、可靠性好、可对方位陀螺的漂移进行标定和补偿是其独特优点。另外,如果利用专门的光学系统,配合已知地标的方位角和纬度,不仅能够实现快速对准,而且还可进行水平陀螺的标定和补偿。

 
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