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惯性交感    
相关语句
  inertia coupling
    The Influence of the Inertia Coupling on the Stability and Control of the Helicopter and the Response of Helicopter to Gust
    直升机惯性交感对稳定性、操纵性和离散突风响应的影响
短句来源
    THE INFLUENCE OF THE INERTIA COUPLING ON THE STABILITY AND CONTROL OF THE HELICOPTER AND THE RESPONSE OF HELICOPTER GUST
    直升机惯性交感对操稳特性和突风响应的影响
短句来源
    The influence of the inertia coupling on the stability and control of the helicopter and the response of helicopter to dispersed gust are investigated.
    本文研究直升机惯性交感对稳定性和操纵性的影响,亦研究了对直升机在离散突风中响应的影响。
短句来源
    The influence of the inertia coupling on the stability and control of the helicopter and the response of helicopter to dispersed gust are investigated in this paper.
    本文研究直升机惯性交感对操稳以及对在突风中响应的影响.
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  inertia coupling
In the resulting equations of motion the flexible body mass matrix is constant and diagonal while the full nonlinear deformations and the inertia coupling description are still preserved.
      


The influence of the inertia coupling on the stability and control of the helicopter and the response of helicopter to dispersed gust are investigated. An articulated rotor with a blade hinge offset and with an elastic restraint about the flap hinge is used as the rotary wing dynamic model. The nonuniform distribution of induced velocity on the rotor disk derived from the generalized vortex theory is taken into account. The model of the dispersed gust is a sine-squared one according to the demand of the specification.A...

The influence of the inertia coupling on the stability and control of the helicopter and the response of helicopter to dispersed gust are investigated. An articulated rotor with a blade hinge offset and with an elastic restraint about the flap hinge is used as the rotary wing dynamic model. The nonuniform distribution of induced velocity on the rotor disk derived from the generalized vortex theory is taken into account. The model of the dispersed gust is a sine-squared one according to the demand of the specification.A sample calculation of a typical helicopter has been made. Having compared the states whether the inertia coupling is considered or not, the detailed calculation and analysis of the stability, control and the response of helicopter to dispersed gust are given.

本文研究直升机惯性交感对稳定性和操纵性的影响,亦研究了对直升机在离散突风中响应的影响。旋翼动力学模型采用水平铰外伸量和桨叶根部有弹性约束的结构模型。诱导速度在桨盘处的分布采用广义涡流理论所导的公式。离散突风模型为规范所要求的正弦平方型。 本文以某典型直升机为算例,比较了计及惯性交感与否的稳操特性和突风响应。

The influence of the inertia coupling on the stability and control of the helicopter and the response of helicopter to dispersed gust are investigated in this paper. An articulated rotor with a blade hinge offset and with an elastic restraint about the flap hinge are used as the rotary wing dynamic model. The nonuniform distribution of induced velocity on the rotor disk derived from the generalized vortex theory is taken into account. The model of the dispersed gust is the sine-squared according to the demand...

The influence of the inertia coupling on the stability and control of the helicopter and the response of helicopter to dispersed gust are investigated in this paper. An articulated rotor with a blade hinge offset and with an elastic restraint about the flap hinge are used as the rotary wing dynamic model. The nonuniform distribution of induced velocity on the rotor disk derived from the generalized vortex theory is taken into account. The model of the dispersed gust is the sine-squared according to the demand of the specification. A sample calculation of a typical helicopter has been made. Considering the inertia coupling and not and comparing the two states, the detail calculation and analysis of the stability, control and the response of helicopter to dispersed gust are given.

本文研究直升机惯性交感对操稳以及对在突风中响应的影响.旋翼动力学模型采用水平铰外伸和根部弹性约束,诱导速度在桨盘处的分布采用广义涡流理论所导的公式,突风模型为飞行品质规范所要求的正弦平方型.最后以某典型机为算例,比较了计及惯性交感与否的操稳特性和突风响应的影响.

Using six-degree-of-freedom equations and three routines model offlight control system,based on the check of time history,this paper studies thecharacteristics of deep-stall and spin at high angle-of-attack of the fighter F-16. Themechanisms of spin entry and recovery have been explored.

采用六自由度全量运动方程和三通道飞行控制系统模型,使用时域动态响应的方法,研究了F—16飞机在大迎角下飞行的深失速特性和尾旋特性,并对尾旋进入和改出的机理进行了探讨。通过分析研究可得出结论:F-16飞机具有深失速特性,若进入深失速后,可用先拉杆后推杆操纵方法改出;F-16飞机进入尾旋的主要原因是航向自转和偏航、滚转气动交感;在改出尾旋过程中,方向舵操纵力矩、航向静不稳定力矩、偏航惯性交感力矩对制止偏航转动有重要作用;引入迎角/过载限制器、方向舵脚蹬限制器、滚转速率指令限制器及自动抗偏离/尾旋模块,这些能使飞机具有良好的大迎角飞行特性。

 
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