纵向平面的英文

• fore and aft plane
• fore and aftpiston
• fore-and-aft piston
• fore-and-aft plane
• longitudinal plane

• "纵向"英文翻译    direction; machine direction ...
• "平面"英文翻译    plane; two dimensions; flat ...
• "纵向平面波" 英文翻译 :    longitudinal plane waves
• "纵向平衡" 英文翻译 :    balance in pitch; longitudinal balance; longitudinal equilibrium
• "纵向平铺" 英文翻译 :    tile vertical
• "侧向平面" 英文翻译 :    lateral plane
• "定向平面" 英文翻译 :    orientation flat
• "法向平面" 英文翻译 :    normal plane
• "方向平面" 英文翻译 :    direction plane
• "非迷向平面" 英文翻译 :    non isotropic plane
• "横向平面" 英文翻译 :    transverse plane
• "径向平面" 英文翻译 :    radial plane
• "迷向平面" 英文翻译 :    minimal plane
• "有向平面" 英文翻译 :    oriented plane
• "在“径向平面”" 英文翻译 :    radial plane
• "轴向平面" 英文翻译 :    axial plane
• "纵向平铺窗口" 英文翻译 :    tile vertically
• "齿轮轴向平面" 英文翻译 :    gear axial plane
• "刀盘轴向平面" 英文翻译 :    cutter axial plane
• "中心侧向平面" 英文翻译 :    central lateral plane
• "纵向平等见横向平等与纵向平等" 英文翻译 :    v=p*q/m=gnp/mvertical equity
• "横向平等与纵向平等" 英文翻译 :    horizontal equity vsvertical equityy; horizontal equity vs．vertical equity
• "纵向平移断裂作用" 英文翻译 :    longitudinal strike-slip faulting
• "横向平等与纵向平等横向平等指的是" 英文翻译 :    horizontal equity vs.vertical equity; horizontal equity vsvertical equityy
• "定向平面对准器" 英文翻译 :    orientation flat aligner/flat orientor

• Thus the flight dynamic characteristics and control features in the conversion mode are the key technologies in the whole tilt rotor design
  过渡模式飞机的气动布局改变主要体现在纵向平面内,所以本文主要研究过渡模式下飞机纵向通道的动力学特性和控制系统设计。
• The central contents in this paper is : first , the reference frame is defined and the movement equation and the transfer function of the body are proposed in portrait plane . so the module of the center of mass stabilization loop is proposed
  本文研究的主要内容是：第一，定义了坐标系，并在导弹的纵向平面内推导了弹体的运动方程和传递函数，确定了质心稳定回路的模型。
• To solve the problems caused by the varieties of the missile dynamics with the difference of flight height , velocity and attitude angle in modeling the missile , in this thesis , the theory of variable structure model reference adaptive control is used to design a pitch channel autopilot based on a longitudinal missile model , the status equation using the measurable parameters of load and angular rate is established , and the methodology to choosing the reference model is discussed also , and the performance of the controller is analyzed by means of simulation
  为了解决拦截弹气动参数随飞行高度、速度、姿态的不同，变化范围大，控制系统难以准确建模的困难，基于纵向平面拦截弹模型，采用模型参考变结构控制理论设计了俯仰通道姿控复合控制系统，以可测量变量过载和角速度作为状态量建立了系统的状态方程，讨论了参考模型的选择方法，并对系统的性能作了仿真分析。