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   equivalent linear damping 在 航空航天科学与工程 分类中 的翻译结果: 查询用时:0.599秒
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equivalent linear damping
相关语句
  等效线性阻尼
    Results demonstrate that the damper axial velocity could be reduced and equivalent linear damping increased through modifications of damper geometric arrangement and reasonable choices of structural parameters.
    通过改进减摆器的安装型式、选择合理的几何参数可以显著降低轴向速度 ,提高等效线性阻尼
短句来源
  等效线性阻尼
    Results demonstrate that the damper axial velocity could be reduced and equivalent linear damping increased through modifications of damper geometric arrangement and reasonable choices of structural parameters.
    通过改进减摆器的安装型式、选择合理的几何参数可以显著降低轴向速度 ,提高等效线性阻尼
短句来源
  等效线性阻尼的
    On Influence of Kinematics to Equivalent Linear Damping of Helicopter Blade Hydraulic Damper
    几何耦合对直升机桨叶液压减摆器等效线性阻尼的影响研究
短句来源
  “equivalent linear damping”译为未确定词的双语例句
    In order to investigate the effect of kinematics and parameters of nonlinear hydraulic damper on equivalent linear damping, a analytical model of helicopter rotor damper, accounting for kinematic couplings, is presented in forward flight.
    为研究几何耦合与设计参数对非线性液压减摆器等效阻尼的影响 ,建立了直升机前飞时 ,计入几何耦合的旋翼液压减摆器的分析模型 ,根据桨叶与减摆器之间的关系和减摆器力 -速度曲线 ,导出了桨叶的摆振运动方程。
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  equivalent linear damping
The transmissibility of a nonlinear viscoelastic isolator is compared with that of a linear isolator using an equivalent linear damping coefficient.
      
Results indicate that equivalent linear damping will be significantly reduced if pitch/flap/lag kinematic coupling introduced for notional model and flight conditions.
      
Fourier series based moving block analysis was applied to calculate equivalent linear damping in terms of transient responses of damper axial velocity.
      
On influence of kinematics to equivalent linear damping of helicopter blade hydraulic damper
      
The equivalent linear damping ratio was measured as a function of vibration amplitude and clamping force.
      
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In order to investigate the effect of kinematics and parameters of nonlinear hydraulic damper on equivalent linear damping, a analytical model of helicopter rotor damper, accounting for kinematic couplings, is presented in forward flight. A blade lead lag differential equation is derived in terms of blade damper relations and damper force velocity curve. Four ordered Runge Kutta numerical method is applied to calculate damper axial velocity in time domain for different cases of kinematic couplings,...

In order to investigate the effect of kinematics and parameters of nonlinear hydraulic damper on equivalent linear damping, a analytical model of helicopter rotor damper, accounting for kinematic couplings, is presented in forward flight. A blade lead lag differential equation is derived in terms of blade damper relations and damper force velocity curve. Four ordered Runge Kutta numerical method is applied to calculate damper axial velocity in time domain for different cases of kinematic couplings, and equivalent linear damping is obtained from energy balance method. The effects of geometric arrangements on the damper axial velocities and the magnitudes of equivalent linear damping are also analyzed. Results demonstrate that the damper axial velocity could be reduced and equivalent linear damping increased through modifications of damper geometric arrangement and reasonable choices of structural parameters.

为研究几何耦合与设计参数对非线性液压减摆器等效阻尼的影响 ,建立了直升机前飞时 ,计入几何耦合的旋翼液压减摆器的分析模型 ,根据桨叶与减摆器之间的关系和减摆器力 -速度曲线 ,导出了桨叶的摆振运动方程。用 4阶龙格 -库塔法对减摆器轴向速度在时域内的响应进行了计算 ;用能量平衡的原理计算了非线性液压减摆器的等效线性阻尼 ;计算并分析了几种典型的几何耦合形式、减摆器的安装形式和设计参数对轴向速度和等效阻尼的影响。结果表明 ,前飞时变距几何耦合将使液压减摆器的有效阻尼大幅度下降 ;通过改进减摆器的安装型式、选择合理的几何参数可以显著降低轴向速度 ,提高等效线性阻尼。

An analytical model of hydraulic damper was presented in forward flight accounting for pitch/flap/lag kinematic coupling and its nonlinear force_velocity curve. The fourth order Runge_Kutta was applied to calculate the damper axial velocity in time domain. Fourier series based moving block analysis was applied to calculate equivalent linear damping in terms of transient responses of damper axial velocity. Results indicate that equivalent linear damping will be significantly reduced if pitch/flap/lag...

An analytical model of hydraulic damper was presented in forward flight accounting for pitch/flap/lag kinematic coupling and its nonlinear force_velocity curve. The fourth order Runge_Kutta was applied to calculate the damper axial velocity in time domain. Fourier series based moving block analysis was applied to calculate equivalent linear damping in terms of transient responses of damper axial velocity. Results indicate that equivalent linear damping will be significantly reduced if pitch/flap/lag kinematic coupling introduced for notional model and flight conditions.

建立了直升机前飞时 ,计入变距 /挥舞 /摆振几何耦合和力_速度非线性关系的液压减摆器分析模型 ;用 4阶龙格_库塔法在时域内计算减摆器的轴向速度 ;根据减摆器轴向速度的瞬态响应成分 ,利用基于富里叶级数的移动矩形窗方法计算了减摆器等效线性阻尼· 结果表明 ,存在变距 /挥舞 /摆振几何耦合的液压减摆器 ,在直升机前飞时其等效线性阻尼将大幅度下降

 
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