Temperature decoupling large range fiber Bragg grating strain sensor

被引：0
|
作者：
Yan G. [1 ,2 ]
Lu J.-Z. [1 ,2 ]
Zhang K.-Y. [1 ,2 ]
Meng F.-Y. [1 ,2 ]
Zhu L.-Q. [1 ,2 ]
机构：
[1] Instrument Science and Optoelectronic Engineering, Beijing Information Science and Technology University, Beijing
[2] Beijing Laboratory of Optical Fiber Sensing and System, Beijing Information Science and Technology University, Beijing
来源：
Jilin Daxue Xuebao (Gongxueban)/Journal of Jilin University (Engineering and Technology Edition) | 2019年 / 49卷 / 05期
关键词：
Aircraft load spectrum; Fiber grating; Strain sensor; Technology of instrument and meter; Temperature decoupling;
D O I：
10.13229/j.cnki.jdxbgxb20180842
中图分类号：
学科分类号：
摘要：
In the test of aircraft load parameters, some structures will produce large strain concentration points. In order to solve the problem of large-scale strain monitoring of aircraft structure,a temperature-sensitized, strain-reducing fiber grating large-range strain sensor is proposed. The fiber Bragg grating sensing theory is analyzed, and a new sensor base structure is designed and analyzed by finite element method. The temperature-calibration, temperature repeatability, and strain calibration tests were performed on the packaged sensor. The results show that in the environment of 10~60 °C, the packaged fiber grating strain sensor has a temperature sensitivity of 44.959 pm/°C, which is 4.5 times stronger than bare fiber and has a linearity of 0.999. The central wavelength change at the same temperature is ±4 pm. Under the condition of 0~2000 με, the strain sensitivity is 0.79 pm/με, which is 1.52 times lower than that of bare fiber, the linearity is 0.999, and the repeatability of multiple strain cycles is ±5 pm. The packaged sensor has good sensitivity and consistency, meets the accurate measurement of the aircraft's large-scale strain, and has a promising future in the monitoring of aircraft strain concentration structure. © 2019, Jilin University Press. All right reserved.
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页码：1682 / 1688
页数：6
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