高速飞行器飞行模态辨识技术及验证研究

Application and Verification of the High Speed Aircraft’s Operational Mode Identification

针对高速飞行器飞行模态辨识技术可行性及未来发展问题,本文介绍了高速飞行器飞行模态辨识技术及验证研究情况。其中工作模态辨识搭载的飞行试验平台最高飞行马赫数为6。通过地面试验研究和飞行器结构特点,确定了遥测系统测点最优布置方案,通过遥测系统进行了若干通道的低频振动响应测量。提出了基于时域缩放的飞行模态滑动跟踪方法,对飞行器飞行过程中的低阶模态进行了锁定和跟踪。通过研究,验证了飞行模态辨识方法和测量系统的可行性,为后续进一步研究飞行模态天地差异以及发展飞行模态在线辨识技术奠定了基础。

To verify the technology of the high speed aircraft’s operational mode identification and put forward the development trend in the Future,the application and verification of the hypersonic aircraft’s operational mode identification is presented.The observations of operational mode identification are onboard flight test platform,whose fast velocity is 6Ma.The influence of the measure information on the operational mode identification of the aircraft is investigated by ground test,where the best measuring points distributing is determined,and the low-frequency vibration of several channels is acquired.The sliding tracking method of the operational mode is put forward,which can lock and track the low order modes of the aircraft during the flying.It is found that the method of the operational mode identification and the measurement scheme are verified.The result reinforces the study of operational mode’s difference between flight and ground testing,and the development of the on-line operational mode identification.