助手标题  
全文文献 工具书 数字 学术定义 翻译助手 学术趋势 更多
查询帮助
意见反馈
   操纵 在 航空航天科学与工程 分类中 的翻译结果: 查询用时:0.083秒
图标索引 在分类学科中查询
所有学科
航空航天科学与工程
汽车工业
船舶工业
投资
证券
金融
文艺理论
经济法
中国语言文字
更多类别查询

图标索引 历史查询
 

操纵     
相关语句
  control
    The Analysis of Dynamic Stiffness of Aircraft Control System and Inherent Vibration Characteristics Coupled with Rudder
    飞机操纵系统的动态刚度及其与舵面耦合固有振动特性分析
短句来源
    THE STUDY OF CONTROL LAWS OF SPIN ENTRY RECOVERY FOR THE JJ-6 AIRCRAFT (1)
    JJ-6飞机进入和改出尾旋的操纵规律的研究(一)
短句来源
    THE ANALYSIS OF CONFATIBILlTY FOR CONTROL AUGMENTATION SYSTEM AND MACHINERY CONTROL SYSTEM
    控制增稳系统与机械操纵系统的相容性分析
短句来源
    VARIABLE-STRUCTURE CONTROL OF LIQUID-FILLED SPACECRAFT LARGE-ANGLE MANEUVERS
    充液飞行器大角度操纵变结构控制
短句来源
    INFLUENCE OF CONTROL RATE OF STICK ON PILOT INDUCED OSCILLATION
    操纵速率对驾驶员诱发振荡的影响
短句来源
更多       
  maneuvering
    CONTROL REQUIREMENTS FOR POST STALL MANEUVERING
    过失速机动的操纵要求
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
    As the control law more accurate represents the nonlinear factors that arise in aircraft dynamic model and remedies the degrading of aircraft nonlinear dynamical behavior during maneuvering flight , it offers the potential for providing high levels of handling quality and flight performance in the entire flight envelope of the aircraft.
    由于这组控制规律计及了飞机动力学模型中的非线性因素,能够弥补飞机机动飞行时非线性特性的恶化影响,在整个飞行包线内都能为飞机提供优良的操纵品质和飞行性能。
短句来源
    The results show that the initial conditions have natable effect on fighter functionagility , and improving the performance of engine , reasonably designing and choosing thecontrol system and the control laws in maneuvering flight will be benefit to develop functionagility of fighter.
    结果表明:不同初始飞行状态对飞机功能敏捷性有显著影响,改善和提高发动机性能,合理设计和选取飞机的控制系统和机动飞行中的操纵动作,将有利于发挥飞机敏捷性功能。
短句来源
    From the viewpoint of aircraft design, a topic on control design requirements for post stall maneuvering is tackled.
    从飞机设计的角度分析了过失速机动飞行的操纵要求问题。
短句来源
更多       
  steering
    SURVEY OF STEERING LAWS FOR SINGLE GIMBAL CONTROL MOMENT GYROSCOPE SYSTEMS
    单框架控制力矩陀螺系统操纵律研究综述
短句来源
    Study on Steering Law of Large Spacecraft SGCMG System Based on Fuzzy Decision
    大型航天器SGCMG系统基于模糊决策的操纵律设计研究(英文)
短句来源
    Study on calculative method of aircraft steering turning radius and turning velocity
    飞机地面操纵转弯半径和转弯速度计算方法研究
短句来源
    Dynamic Steering Law Design for Redundant Single Gimbal Control Moment Gyroscopes
    单框架控制力矩陀螺动态操纵律设计
短句来源
    Observer-based steering law design for control moment gyroscopes
    基于非线性观测器的控制力矩陀螺操纵律设计
短句来源
更多       
  maneuver
    THE INFLUENCE OF AIRPLANE CONTROL SYSTEM PROPERTIES ON THE MANEUVER LOADS
    飞机操纵系统特性对机动载荷的影响
短句来源
    Computation of Control Requirements of Unconventional Maneuver
    非常规机动操纵要求的计算
短句来源
    Secondly, two maneuver control models are discussed, and control algorithms of typical maneuvers are implemented based on the models.
    建立了基于驾驶员操纵特点和矢量指向的两种机动控制方法,并利用这两种机动控制方法实现了典型空战机动的控制算法。
短句来源
    1. Based on the analysis of the definition and the study of the estimation methods , the Fighter's Combat Effectiveness model , in which the parameters of maneuver, cannon, missile , detector and others are considered, is established.
    a) 建立了战斗机作战效能计算模型。 在分析和研究作战效能定义、作战效能评估方法的基础上,建立了能反映飞机机动性、火力、目标探测能力、电子战能力、操纵效能、生存力、航程、突防能力、远程武器能力、导航能力、载弹量等因素对飞机作战效能影响的作战效能计算模型。
短句来源
    By means of bifurcation analysis and catastrophe theory methodology,this paper explores the effects of various kinds of control systems of an aircraft in rolling maneuver on occuring jump and limit cycle phenomena,enhancing critical roll rate,extending effective region of control surface,and improving time responses.
    本文用分支和突变理论的方法,着重探讨急滚机动飞行时飞机上的各类控制系统,对突跃和极限环现象的发生,临时滚转速率的提高,舵面可操纵范围的扩大,以及时间响应的改善等方面的影响。
短句来源
更多       

 

查询“操纵”译词为其他词的双语例句

     

    查询“操纵”译词为用户自定义的双语例句

        我想查看译文中含有:的双语例句
    例句
    为了更好的帮助您理解掌握查询词或其译词在地道英语中的实际用法,我们为您准备了出自英文原文的大量英语例句,供您参考。
      control
    Some applications are given to control theory for partial differential equations.
          
    Thus, PPARα/γ dual agonists may provide superior therapy to the current PPARγ-selective agonists, due to the additional lipid control afforded by the PPARα component.
          
    Study subjects were divided into three groups: subjects in group 1 were microalbuminuric diabetic (n = 33), in group 2 subjects were normoalbuminuric diabetic group (n = 32), and group 3 was formed from nondiabetic healthy control subjects (n = 18).
          
    Serum VEGF concentrations were significantly higher in the diabetic groups than in the control group even at the normoalbuminuric stage.
          
    Compound IVc indicated the best antibacterial activity compared with the control drug ampicillin (CAS 69-53-4).
          
    更多          
      maneuvering
    Virtual reality system of manned maneuvering unit taking into consideration the disturbance from an astronaut's limbs
          
    This paper describes a manned maneuvering unit (MMU) virtual reality system.
          
    Analysis of disturbances in a leg of pitch-up maneuvering
          
    A complex model of disturbances for a leg of pitch-up maneuvering by a carrier aircraft in launching a launch vehicle was constructed.
          
    In order to resolve the multisensor multiplied maneuvering target tracking problem, this paper presents a distributed interacted multiple model multisensor joint probabilistic data association algorithm (DIMM-MSJPDA).
          
    更多          
      steering
    Firstly, a new data model is established based on generalized steering vectors and generalized array manifold matrix.
          
    Multi-axle dynamic steering system of truck-howitzer
          
    A two-degree-of-freedom (2-DOF) steering model of multi-axle vehicle was established.
          
    The steering center position, the relationship between the steering angle and the vehicle velocity, and the minimum turn radius were deduced on the basis of the proportional control with a zero sideslip angle.
          
    The microrobot is driven by three electromagnetic micromotors with 2 mm diameter, two of which are for linear movement and the third one for steering.
          
    更多          
      maneuver
    In consideration of the needs of human beings, machinery and computation, the model has been used for structural design combined with relevant knowledge, means, maneuver and strategy.
          
    It is demonstrated that the optimum maneuver assures the maximum absolute value of the reentry angle and the insensitivity of the trajectory of descent with respect to small errors of orientation of the braking engine in the plane of the orbit.
          
    Optimization of the Flight of a Spacecraft with a Solar Sail from the Earth to Mars with a Perturbation Maneuver near Venus
          
    The trajectories of the fastest flight of a spacecraft (SC) with a solar sail from the Earth's sphere of activity to the Martian sphere of activity including the section of a perturbation maneuver near Venus are investigated.
          
    The planetary spheres of activity are assumed to be point-like; i.e., the maneuver section and the initial and final positions of the SC coincide with the corresponding positions of the planets.
          
    更多          


    The analysis of the pilot-induced oscillation is carried out in general by usingthe simulated methods or flying tests. For the need of the design calculations, however, the writer through consulting the related references provides twotheoretical methods, i.e. the frequency response and root-locus methods.At first, the equation of the airplane longitudinal motion, the equation of the control system motion with full-power or no-power, and the related transfer functions are given in this paper.And then, based on...

    The analysis of the pilot-induced oscillation is carried out in general by usingthe simulated methods or flying tests. For the need of the design calculations, however, the writer through consulting the related references provides twotheoretical methods, i.e. the frequency response and root-locus methods.At first, the equation of the airplane longitudinal motion, the equation of the control system motion with full-power or no-power, and the related transfer functions are given in this paper.And then, based on the closed-lrop dynamic models of the combination of the airplane and control systems, the frequency response of the elevator deflection to stick force input is calculated and the root-locus is plotted. Thus, the tendency of the pilot-induced oscillation may be analylized.In addition, some simplified criterions of the longitudinal pilot-induced oscillation are presented. Some primary influence factors, especially the effect of bobweight in control systems are discussed.

    驾驶员诱发振荡问题的分析,一般通过模拟试验或飞行试验进行。但为了设计计算的需要,本文参考有关资料,提出两种理论分析方法,即频率法和根轨迹法。 文中首先给出飞机的纵向运动方程、助力及非助力操纵系统方程以及有关传递函数,然后根据飞机与操纵系统组合的闭环动力学模型,计算舵偏角对杆力输入的频率反应或绘制根轨迹曲线,从而可以分析飞机的诱发振荡趋势。 此外,还介绍了几种纵向驾驶员诱发振荡的简化判据。并对主要影响因素,特别是对操纵系统配重的影响进行了讨论。

    In this paper modal characteristics of rotor blades torsional vibration coupled with control system of the helicopter are studied by using the mechanical impedance method. A practical one is here illustrated. The results obtained by these analyses show that the problem of the influence of control system on modal characteristics of the rotor blades torsional vibration is noticeable.

    本文用机械阻抗方法研究与直升机操纵系统耦合的旋翼桨叶扭转振动固有特性,并附一应用实例。分析结果表明:操纵系统对旋翼桨叶扭转振动固有特性的影响是一个值得注意的问题。

    A numerical method is presented for predicting the aerodynamic characteristics of elastic aircraft under quasi-static approximation. This method can be used to evaluate the lift distribution and 11 main longitudinal aerodynamic derivatives of elastic aircraft at subsonic speeds. The aerodynamic calculations are based on the Green's function method. The structure deformation is evaluated by the free structure influence coefficient method. The combination of these methods can provide an efficient, general and...

    A numerical method is presented for predicting the aerodynamic characteristics of elastic aircraft under quasi-static approximation. This method can be used to evaluate the lift distribution and 11 main longitudinal aerodynamic derivatives of elastic aircraft at subsonic speeds. The aerodynamic calculations are based on the Green's function method. The structure deformation is evaluated by the free structure influence coefficient method. The combination of these methods can provide an efficient, general and flexible aerodynamic tool for design of elastic aircraft.Several numerical examples are given and some dynamical problems of elastic aircraft are also discussed in this paper. The derivatives evaluated in this paper can be directly adopted in analysis of stability and control of elastic aircraft.

    本文介绍一种准静弹性飞机气动特性的数值计算方法。可以用它来计算亚音速时弹性飞机的升力分布及11个主要的纵向气动导数。 文中附有算例,并对准静弹性飞机动态特性方面的一些问题进行了分析和讨论。 本文所得的导数可直接用于弹性飞机操纵性与稳定性的分析。

     
    << 更多相关文摘    
    图标索引 相关查询

     


     
    CNKI小工具
    在英文学术搜索中查有关操纵的内容
    在知识搜索中查有关操纵的内容
    在数字搜索中查有关操纵的内容
    在概念知识元中查有关操纵的内容
    在学术趋势中查有关操纵的内容
     
     

    CNKI主页设CNKI翻译助手为主页 | 收藏CNKI翻译助手 | 广告服务 | 英文学术搜索
    版权图标  2008 CNKI-中国知网
    京ICP证040431号 互联网出版许可证 新出网证(京)字008号
    北京市公安局海淀分局 备案号:110 1081725
    版权图标 2008中国知网(cnki) 中国学术期刊(光盘版)电子杂志社