The invention relates to a wing low-speed impact positioning method based on a distributed fiber bragg grating sensing network, and belongs to the technical field of sensing application of optical fiber sensors. Simulating and selecting a proper positioning index by using an inverse finite element method; according to the area of the structure, fiber grating sensors are laid along a wing and connected with a wavelength demodulator, and an initial signal of an impact event is collected through a computer and then processed; impact signals at different heights are obtained through the impact experiment platform, and the arrival time of the impact signals collected by the sensor is obtained. The signal processing flow comprises the following steps of: firstly, decomposing an impact signal through a variational mode decomposition algorithm aiming at the noise interference and wave aliasing problems of the impact signal, then selecting a reconstructed signal component through time-frequency domain matching and analysis of an original signal and each mode component, calculating an envelope line by utilizing a Hilbert algorithm to obtain signal arrival time, and finally, calculating the signal arrival time by utilizing the Hilbert algorithm. And finally, reconstructing the distribution condition of a strain field and a deformation field when an impact event occurs through an inverse finite element method to realize impact positioning. The purpose of wing structure health monitoring is achieved through the fiber bragg grating sensing network.
本发明涉及一种基于分布式光纤光栅传感网络的机翼低速冲击定位方法,属于光纤传感器的传感应用技术领域,在该方法过程中首先建立机翼结构的三维模型;利用逆有限元法仿真选取合适的定位指标;根据结构的面积大小,将光纤光栅传感器沿机翼铺设并分别与波长解调仪连接,通过计算机采集到冲击事件的初始信号后进行处理;通过冲击实验平台获取不同高度的冲击信号得到传感器采集到的冲击信号到达时间。信号处理流程首先针对冲击信号的噪声干扰和波混叠问题,通过变分模态分解算法对冲击信号进行分解,然后通过原始信号和各模态分量的时频域匹配与分析选择重构信号分量,利用希尔伯特算法计算包络线得到信号到达时间,最后通过逆有限元法重构出冲击事件发生时的应变场与变形场的分布情况实现冲击定位。它通过光纤光栅传感网络实现了机翼结构健康监测的目的。
Aircraft wing impact positioning method based on fiber grating sensor
一种基于光纤光栅传感器的飞机机翼冲击定位方法
03.01.2025
Patent
Elektronische Ressource
Chinesisch
IPC: | G01H MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES , Messen von mechanischen Schwingungen oder Ultraschall-, Schall- oder Infraschallwellen / B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen / G06F ELECTRIC DIGITAL DATA PROCESSING , Elektrische digitale Datenverarbeitung |
Aircraft wing deformation monitoring method based on fiber bragg grating sensing network
Europäisches Patentamt | 2023
|Impact Localization on a Composite Wing Using Fiber Bragg Grating Sensors
British Library Conference Proceedings | 2010
|Aircraft wing machining, maintaining and positioning device
Europäisches Patentamt | 2021
|AIRCRAFT WING AND FIBER METAL LAMINATE FORMING PART OF SUCH AN AIRCRAFT WING
Europäisches Patentamt | 2018
|Aircraft wing and fiber metal laminate forming part of such an aircraft wing
Europäisches Patentamt | 2017
|