将一个二元颤振主动抑制系统视为由若干个滞后环节组成的控制系统。
FAS system can be considered as a control system comprising a number of hysteresis elements.
本文编制了可用于分析带有颤振主动抑制系统的机翼的根轨迹法程序。
A flutter analysis based on root locus method is programmed. It can be applied to a wing equipped with an active flutter suppression system.
本文采用谐波平衡法，定量地解释了机翼颤振主动抑制风洞试验中出现的极限环现象。
The phenomena "limit cycle" occurred in wind tunnel test for active flutter suppression of a wing model are numerically explained using Harmonic Balance Method.
风洞试验结果说明，采用颤振主动抑制控制系统后，机翼的颤振临界速度可提高37%。
The results of the wind tunnel test show the flutter critical speed of the wing model increases by 37% after the implementation of AFS system.
实验结果表明：改变反馈控制的增益和相位角两个变量，能影响主动颤振抑制系统的稳定性。
The test results show that a change in two parameters-the gain and the phase Angle of the feedback control-will have an effect on the stability of the active flutter suppression system.
最后，提出了为实现主动颤振抑制必须解决的一些问题。
At the end of this paper are some problems which must be solved for the realization of active flutter suppression.
本文简要地阐述了具有后缘控制面的二元机翼模型主动颤振抑制低速风洞试验的全过程。
This paper gives a brief description of the whole process of the low-speed wind tunnel test for active flutter suppression of a two-dimensional wing model with trailing edge control surface.
本文简要地阐述了具有后缘控制面的二元机翼模型主动颤振抑制低速风洞试验的全过程。
This paper gives a brief description of the whole process of the low-speed wind tunnel test for active flutter suppression of a two-dimensional wing model with trailing edge control surface.
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