The accuracy of modal parameter estimation plays a crucial role in flutter boundary prediction.
准确估计模态参数在飞机颤振边界的预测中具有重要意义。
Designing of BF-1 rotors depends upon the principle that the total damping is equal to zero at the point near the stall flutter boundary.
文中提出了实验模型的零阻尼设计原则，描述了失速颤振发生的过程。
This paper also presents the experimental results of effects of the blade tip clearance and the airfoil shape on the stall flutter boundary.
此外还给出了两种叶尖间隙和两种叶型对失速颤振影响的实验结果。
It incorporates organically the flight test data and the flutter theory model by the structured singular value theories, to process the flutter boundary estimate.
利用结构奇异值理论将颤振理论模型和试飞数据有机结合起来，进行了颤振边界预测。
Pass to incorporate organically the flight test data and the system model, make use of the structured singular value theories proceed the flutter boundary estimate.
一种新的颤振分析方法——鲁棒颤振裕度法被介绍，它利用结构奇异值理论将系统模型和试飞数据有机结合起来进行颤振边界预测。
The varying tendency of flutter speed can be deduced when the store parameters are asymmetric, according to the results of the original symmetric flutter boundary curves.
该法在原始对称构型的颤振边界曲线已知的情况下，就能推断结构参数不对称时颤振速度的变化趋势。
Furthermore, it performed the parametric analysis in terms of feedback gains and delayed time using the root locus method, thus obtaining the system's flutter stability boundary.
进而采用根轨迹方法就反馈增益和延迟时间进行参数分析，获得系统的颤振稳定性边界。
Furthermore, it performed the parametric analysis in terms of feedback gains and delayed time using the root locus method, thus obtaining the system's flutter stability boundary.
进而采用根轨迹方法就反馈增益和延迟时间进行参数分析，获得系统的颤振稳定性边界。
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