无人直升机操纵响应特性研究的关键是有准确的旋翼诱导速度模型。
The key to investigate control response characteristics of unmanned helicopter is to determine the correct induced velocity model.
本文从旋翼的广义经典涡流理论出发，通过环量对诱导速度的贡献的简化处理，推导出旋翼诱导速度的二阶分布。
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.
旋翼桨盘处的诱导速度分布采用自前向后直线增大的形式。
The distribution of induced velocity at the rotor is assumed linearly variable over the disk.
应用自由尾迹方法和旋翼配平模型，建立了一个悬停和前飞状态旋翼在导弹发射线上的诱导速度计算模型。
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.
在本文中作者考虑了各种因素，推导出铰接式刚性旋翼的动力学广义方程。这些因素是：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;
主旋翼是直升机建模的关键，详细讨论了与其相关的翼型气动力模型、 诱导速度模型和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.
本文用简化的自由涡模型研究旋翼近场尾涡系在机身影响下的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.
在机身影响下，旋翼近场尾涡形状发生畸变，从而改变桨盘处的诱导速度分布。
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.
本文用一简化自由涡模型模拟旋翼尾涡系，用一简单涡模拟地面涡，对近地低速飞行时旋翼尾涡系的畸变及其引起的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.
旋翼尾流的作用通过自由尾流分析来求解局部的诱导下洗速度以修正翼型攻角。
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.
建立了旋翼升力线模型和广义尾迹模型，在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.
建立了旋翼升力线模型和广义尾迹模型，在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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