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.
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