Design and Implementation of Distributed Temperature Monitoring System Based on Fiber Optic Temperature Sensor

In order to realize the spacecraft temperature measurement in space simulation space vacuum heat environment, real-time monitoring of spacecraft structure temperature and spacecraft health status diagnosis, a distributed temperature monitoring system based on fiber temperature sensor is designed. Firstly, the distributed optical fiber temperature monitoring hardware system was built by using the characteristics of the fiber temperature sensor. Secondly, through the modular design, the LabVIEW was used to read the center wavelength value of the fiber grating connected to the fiber grating demodulator in real time. The decoupling algorithm of stress realizes the functions of temperature data acquisition, display and storage. Finally, the distributed temperature monitoring system is tested in high and low temperature under vacuum low temperature environment, and its repeatability is verified. The system test shows that the monitoring system can measure the temperature of the spacecraft structural components in a vacuum low temperature environment, and the system has good repeatability through three tests.