摘要
颤振模态参数辨识是飞机颤振飞行试验中的一个重要环节。为实现颤振飞行试验过程中飞机结构的实时和准实时在线分析,提高随机子空间模态参数辨识自动化程度,针对飞机颤振飞行试验激励力不足、测量点有限、常存在谐波分量的特点,在随机子空间法的基础上结合扩展模态置信度准则和扩展峰度系数检查法,通过不同模态间频率、阻尼比和振型定义的距离聚类方式,提出了一种适用于颤振飞行试验的模态参数自动辨识方法。最后结合仿真数据和飞行试验实测数据验证了该方法的有效性。
Flutter modal parameter identification is an important part of aircraft flutter flight test.In order to realize the real-time and quasi-real-time online analysis of the aircraft structure during the flutter flight test and improve the automation degree of modal parameter identification in stochastic subspace method,an automatic identification method for modal parameters suitable for flutter flight test based on the stochastic subspace with extended modal confidence criterion and extended kurtosis coefficient checking method is proposed.Finally,the effectiveness of the proposed method is verified by the simulation data and flight test data.
作者
刘立坤
闫轲
Liu Likun;Yan Ke(Aircraft Flight Test Technology Institute,Xi’an 710089,China)
出处
《航空科学技术》
2020年第3期53-58,共6页
Aeronautical Science & Technology
关键词
颤振
飞行试验
模态参数
随机子空间法
flutter
flight test
modal parameters
stochastic subspace identification method
