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叶间减
相关语句
  inter-blade
     Parametric Analysis of Inter-Blade Lag Dampers of Helicopter Rotor
     直升机旋翼叶间减摆器的参数影响分析
短句来源
     Study on Aeromechanical Stability of a Helicopter with Inter-blade Dampers
     带叶间减摆器直升机气动机械稳定性研究
短句来源
     In 1990s, Eurocopter began to use the inter-blade dampers in EC155 which means to put every damper between two adjacent blades.
     上个世纪90年代,欧直公司开始在EC155上使用叶间减摆器,减摆器不是布置在桨叶和桨毂之间,而是布置在相邻两片桨叶之间。
短句来源
     An analytical model is presented for nonlinear helicopter rotor/fuselage coupled dynamics with inter-blade lag dampers. Along with the damper linear properties, numerical simulation and time-domain technology are applied in predictions of rotor/fuselage coupled dynamic instabilities and damper loads in forward flight.
     建立了带叶间减摆器的直升机旋翼/机体耦合非线性动力学分析模型,针对具有线性特性的叶间减摆器,采用数值模拟及时域方法分析了直升机前飞状态下旋翼/机体耦合动稳定性及减摆器载荷,并就减摆器布局、几何参数对系统动稳定性及减摆器载荷的影响进行了分析。
短句来源
  “叶间减”译为未确定词的双语例句
     CHANGES OF COUPLED ROTOR-BODY STABILITY FOR A LEAD-LAG DAMPER BETWEEN BLADES FAILURE
     叶间减摆器失效时旋翼/机体耦合稳定性的变化
短句来源
  相似匹配句对
     Parametric Analysis of Inter-Blade Lag Dampers of Helicopter Rotor
     直升机旋翼摆器的参数影响分析
短句来源
     Study on Aeromechanical Stability of a Helicopter with Inter-blade Dampers
     带摆器直升机气动机械稳定性研究
短句来源
     CHANGES OF COUPLED ROTOR-BODY STABILITY FOR A LEAD-LAG DAMPER BETWEEN BLADES FAILURE
     摆器失效时旋翼/机体耦合稳定性的变化
短句来源
     (2)Irregular thickenning of inter lobar pleura;
     (2)胸膜不均匀增厚;
短句来源
     There were 2 cases of mixed types (epithelial and mesenchymal components).
     上皮混合型 2例。
短句来源
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  inter-blade
Clocking effect in a two-stage compressor with different inter-blade-row gaps
      
The capabilities of the developed approach are demonstrated by the example of computing the flow in the inter-blade channel of a low-velocity compressor.
      
Each disturbance is characterized by its own frequency and inter-blade phase angle and can be approximated by the Fourier series.
      
The core sequence repeat, YVTD in b strand 2, forms crucial inter-blade contacts.
      


In this paper the stability of coupled rotor-body for a lead-lag damper failure is calculated by taking a helicopter with a rotor of 5 blades and dampers mounted between blades as an example. Comparison of the changes in lead-lag frequency, damping and modes of rotor has been made for the damper working and failure. The change characterisitcs and mechanism of ground and air resonance brought from the damper failure are analyzed. A design method is suggested to avoid or eliminate probable ground resonance .

本文以5片桨叶的叶间减摆器旋翼直升机为例,计算了一个减摆器失效时旋翼与机体耦合稳定性,比较了失效与不失效时旋翼摆振频率、阻尼和振型的变化,分析了由此引起的“地面共振”和“空中共振”的变化特点及其变化机理,提出了避免或消除失效可能导致“地面共振”的设计方法。

An analytical model is presented for nonlinear helicopter rotor/fuselage coupled dynamics with inter-blade lag dampers. Along with the damper linear properties, numerical simulation and time-domain technology are applied in predictions of rotor/fuselage coupled dynamic instabilities and damper loads in forward flight. Effects of the damper configurations and structural parameters on the system dynamic instabilities and the damper loads are studied, and significant effects of the damper kinematic couplings are...

An analytical model is presented for nonlinear helicopter rotor/fuselage coupled dynamics with inter-blade lag dampers. Along with the damper linear properties, numerical simulation and time-domain technology are applied in predictions of rotor/fuselage coupled dynamic instabilities and damper loads in forward flight. Effects of the damper configurations and structural parameters on the system dynamic instabilities and the damper loads are studied, and significant effects of the damper kinematic couplings are observed. Advantages of kinematic couplings can be utilized by cautiously selecting the damper attachment offset and its build-in angles with rotor hub plane. Compared with a baseline model (which has no damper attachment offset), analytical results show that the regressive lag mode damping can be increased about 50%, simultaneously, the damper steady cyclic load amplitude has about 60% decrement for a notional model.

建立了带叶间减摆器的直升机旋翼/机体耦合非线性动力学分析模型,针对具有线性特性的叶间减摆器,采用数值模拟及时域方法分析了直升机前飞状态下旋翼/机体耦合动稳定性及减摆器载荷,并就减摆器布局、几何参数对系统动稳定性及减摆器载荷的影响进行了分析。研究发现,"叶间"布局引起的几何耦合对减摆器载荷及系统的动稳定性有很大的影响,合理选择减摆器安装支臂的长度及其与桨毂平面之间的夹角,可以有效地利用几何耦合的因素。与基本模型相比,它能使系统的模态阻尼提高50%以上,而同时使减摆器的定常循环载荷的幅值下降60%左右。

 
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