• 无人直升机操纵响应特性研究关键有准确旋翼诱导速度模型

    The key to investigate control response characteristics of unmanned helicopter is to determine the correct induced velocity model.

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  • 本文旋翼广义经典涡流理论出发,通过环量对诱导速度的贡献简化处理,推导旋翼诱导速度阶分布。

    In this paper, firstly, relations of first two harmonic induced velocities to the lower and same-order harmonic circulations are obtained from the generalized classical vortex theory of the rotor.

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  • 旋翼桨盘诱导速度分布采用自前向后直线增大形式。

    The distribution of induced velocity at the rotor is assumed linearly variable over the disk.

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  • 应用自由尾迹方法旋翼配平模型建立一个悬停和前飞状态旋翼导弹发射线上诱导速度计算模型。

    Based on the rotor free-wake model and the rotor trim model, an analytical method is developed for the prediction of helicopter rotor induced velocities on missile trajectory.

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  • 本文中作者考虑了各种因素推导出铰接式刚性旋翼动力学广义方程这些因素诱导速度的二阶谐量与挥午系数的二阶谐量;

    In this paper, the general dynamic equations of the hinged stiff rotor blades are derived for a lot of factors, such as the second-harmonic of induced velocity;

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  • 旋翼直升机建模关键详细讨论了与其相关气动力模型、 诱导速度模型挥舞运动模型的建模方法

    Main rotor is the key part of helicopter modeling, the associated modeling methods of aerofoil aerodynamic loads, rotor inflow dynamics and blade flap motion are discussed in detail.

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  • 本文简化自由涡模型研究旋翼近场尾涡系机身影响畸变及其产生的诱导速度交化。

    The effect of helicopter fuselage on its rotor is studied using a simplified free-wake model.

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  • 机身影响下,旋翼尾涡形状发生畸变从而改变桨盘处诱导速度分布

    The results show that the rotor near-wake is distorted because of the flow field of the fuselage, resulting in large variation on the induced velocity distribution at the rotor plane.

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  • 本文简化自由模型模拟旋翼尾涡系,用一简单涡模拟地面涡,对低速飞行时旋翼尾涡系的畸变及其引起诱导速度变化作了研究

    The vortex wake and its induced velocity of a helicopter rotor operating near the ground at low forward speeds have been studied using a simplified free wake-ground vortex model.

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  • 旋翼尾流作用通过自由尾流分析求解局部诱导下洗速度修正翼型

    Rotor wake effects are modeled in the form of a correction applied to the angle of attack along the blades. This correction is obtained by computing the local induced downwash with free wake analysis.

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  • 建立了旋翼升力线模型广义尾迹模型,计算角迹涡线诱导速度时,采用了快速收效方法

    Both lift line model and generalized wake model are founded in this paper. A method is given for calculating induced velocities by a wake vortex line which results in a rapid convergence.

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  • 建立了旋翼升力线模型广义尾迹模型,计算角迹涡线诱导速度时,采用了快速收效方法

    Both lift line model and generalized wake model are founded in this paper. A method is given for calculating induced velocities by a wake vortex line which results in a rapid convergence.

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