卫星镜头结构光纤光栅温度传感器研究

Research on fiber Bragg grating temperature sensor of satellite lens structure

为了解决卫星星敏感器光学镜头结构在轨温度监测问题,提出一种弧形基底封装的光纤光栅温度传感器。分析了星敏镜头结构特征与光纤光栅温度传感原理,采用飞秒激光刻写的光纤光栅作为敏感元件,设计了可贴合于星敏镜头结构特征的弧形封装基底,完成了光纤光栅温度传感器封装,并对传感器进行了拉伸测试、温度标定及温度重复性测试,并已应用于实际工程中。结果表明:弧形封装结构形式的光纤光栅温度传感器线性度可达 0 998,温度灵敏度达到 8 54pm/℃,同一温度下中心波长变化量在 2pm以内,且受弧形基底封装结构变形产生的应变影响小。卫星在轨温度监测,光纤光栅传感与电子式传感相差±3℃。可以实现星敏镜头结构的温度测量功能,在星敏感器结构在轨温度测温中具有应用前景。

In order to solve the in-orbit temperature monitoring problem of the optical lens structure of the satellite star sensor,an arc-shaped substrate-packaged fiber grating temperature sensor was proposed.The structural characteristics of the star-sensitive lens and the principle of fiber grating temperature sensing were analyzed.The fiber grating written by femtosecond laser,was used as the sensing element,and an arc-shaped package substrate suitable for the structural features of the star-sensitive lens was designed.The FBG temperature sensor package was completed.The sensor had been tested by tensile test,temperature calibration,and temperature repeatability test,and had been applied in practical engineering.The results showed that the linearity of the FBG temperature sensor with arc-shaped package structure was 0.998,the temperature sensitivity was 8.54 pm/℃,and the change of the center wavelength was less 2 pm at the same temperature,and the strain that caused by deformation of the arc-shaped package structure had little influence on fiber gratings.Satellite on-orbit temperature monitoring showed that the temperature difference between the FBG sensor and electronic sensor was±3 ℃.It can realize the temperature measurement function of the star-sensitive lens structure,and had application prospects in orbit temperature measurement of the star sensor structure.