直升机横航向动力学模型频域辨识方法研究  

作　　者：陈力 

机构地区：[1]中国飞行试验研究院,西安710089

出　　处：《科技创新与应用》2023年第2期72-75,共4页Technology Innovation and Application

摘　　要：该文针对直升机横航向耦合强、试飞数据高频噪声大的特点,建立适用于直升机横航向飞行动力学模型的频域辨识方法。利用线性调频Z变换、多输入多输出系统频率响应计算和相干系数加权等方法,提高了频率响应计算精度。通过状态子空间方法、输出误差方法辨识横航向动力学模型中的未知参数。利用某型直升机的飞行试验数据对该文方法进行验证,并与商用软件CIFER的辨识结果进行对比,结果表明两者的辨识结果具有相当精度,模型输出都能很好拟合试飞数据,具有良好的工程应用价值。In this paper,a frequency domain identification method for helicopter lateral directional flight dynamics model is established according to the characteristics of strong coupling of helicopter lateral directional and high frequency noise of flight test data.The accuracy of frequency response calculation is improved by using linear frequency modulation Z transform,multi input multi output system frequency response calculation,and coherence coefficient weighting.The unknown parameters in the lateral directional dynamic model are identified by the state subspace method and the output error method.The method in this paper is verified by flight test data of a certain type of helicopter,and the identification results are compared with those of commercial software CIFER.The results show that the identification results of the two software have considerable accuracy,the model output can well fit the flight test data,and have good engineering application value.

关 键 词：直升机 相干系数 频率响应 状态子空间 输出误差 

分 类 号：V217[航空宇航科学与技术—航空宇航推进理论与工程]