本文根据机轮摆振的点接触理论，导出了为克服摆振所需线性阻尼的计算公式。
In this paper the formula of requisite linear damping for overcoming shimmy is derived according to the point contact theory of wheel shimmy.
在讨论输入和阻尼机理的基础上，提出了用振幅大小和起振门槛值作为衡量摆振大小和抗御摆振能力的衡量指标。
Based on the mechanism of input and damping, it is suggested that the vibration amplitude and threshold be taken as a criterion for evaluation vibration strength and anti-vibration ability.
分析了直升机从悬停到小速度前飞时，定常垂直气流的非均匀分布对直升机平衡操纵以及对系统摆振后退型模态阻尼的影响。
The influences of nonuniform vertical flow on helicopter trim controls and regressive lag modal damping levels were analyzed in hovering and forward flight.
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