摘要
直升机旋转桨叶的固有频率是影响旋翼动响应以及气弹稳定性的重要因素之一,频率配置是旋翼桨叶设计的重要内容。受旋翼这种旋转系统信号谐波成分多、气动干扰大、信噪比低、模态密集等特点的影响,一直以来,旋转桨叶的固有频率识别都是直升机行业的一个难点,也是型号研制中必须进行测试的内容之一。通过将固定坐标系下的激励位移信号与旋转坐标系下的桨叶响应信号同步采集、激励位移信号坐标系转换、激励响应信号重采样处理等步骤,发展了基于传递函数分析的旋转桨叶固有频率识别方法,并通过试验验证。试验结果表明该方法能综合运用幅频曲线、相频曲线、相干系数等信息识别旋转桨叶固有频率,物理概念清晰,测试结果易于判断、稳定可靠。
The modal frequency of the rotor blade is a key factor of the rotor transient response and aeroelastic stability problem.As we know,because of the complexity of the blade structure and the badly working environment,identification of rotating blade frequency is always a difficulty in helicopter industry,so we have to design a experiment to test the modal frequency.In this paper we developed the new method-rotating blade modal frequency identification based on transfer function.First,we collected the exciting signal and the response signal synchronously.Second,we transferred the exciting signal from fixed system to rotating system.Then,we resampled the exciting signal and the response signal.At last,we used transfer function to obtain the modal frequency.The advantage of this method is that,the concept is very clear and the result is easy to obtained and reliable.
出处
《直升机技术》
2011年第3期1-7,共7页
Helicopter Technique
基金
重点实验室基金(9140C400401070C4007)资助项目
关键词
旋转桨叶
固有频率
传递函数
rotating blade
modal frequency
transfer function
