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

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。

2·The desingularization smoothing parameter is introduced in calculating the induced velocity on trailing vortex surface.

在诱导速度计算中引入了非奇异光滑参数。

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

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。

4·The nonuniform distribution of induced velocity on the rotor disk derived from the generalized vortex theory is taken into account.

诱导速度在桨盘处的分布采用广义涡流理论所导的公式。

5·The nonuniform distribution of induced velocity on the rotor disk which is derived from the wang's generalized fix vortex theory is taken into account.

诱导速度在桨盘处的分布则采用王氏固定涡系涡流理论所导出的诱导速度非均布公式。

6·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;

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；

7·Experiment results showed that the relation between exciting voltage and induced velocity magnitude was linear, but the influence of supply frequency was not evident.

实验结果表明，等离子体激励作用主要集中在近壁面附近；激励电压与诱导速度近似为线性关系，激励频率对诱导速度的影响不大。

8·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.

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。

9·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.

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。

10·In particular, expressions of flapping coefficients are derived, including the effect of variable induced velocity distribution but in terms of blade parameters and flight parameters only.

特别是在挥舞系数的表达式中，考虑了诱导速度的变化，但直接与桨叶参数和飞行参数有联系。