航天器板状部件在轨热应变FBG测量方法研究  

Research on In-Orbit Thermal Strain FBG Measurement Method of Spacecraft Plate Components

作　　者：程晓迪 辛朝军 皮姝 刘子璇 

机构地区：[1]航天工程大学宇航科学与技术系,北京

出　　处：《国际航空航天科学》2023年第2期58-67,共10页Journal of Aerospace Science and Technology

摘　　要：以SAR卫星天线为代表的航天器板状部件在航天领域应用广泛,在轨环境导致的该类型部件热应变对航天器测量精度的影响不容忽视。为补偿在轨热应变导致的航天器测量误差,提出了一种基于光纤光栅传感网络的板状部件在轨热应变测量方法,在阐述测量原理的基础上,利用ABAQUS进行了热应变仿真分析,进而设计了基于光纤光栅传感网络的在轨热应变测量系统,开展了测量实验。结果表明,文章提出的方法测量相对误差小于5%,可实现航天器板状部件在轨热应变的高精度测量。The plate-shaped components of spacecraft represented by SAR satellite antennas are widely used in the aerospace field. The influence of thermal strain of this type of components caused by on-orbit environment on the measurement accuracy of spacecraft cannot be ignored. In order to compensate for the measurement error of spacecraft caused by on-orbit thermal strain, an on-orbit thermal strain measurement method of plate components based on fiber grating sensing network is proposed. On the basis of expounding the measurement principle, the thermal strain simulation analysis is carried out by using ABAQUS, and then the on-orbit thermal strain measurement system based on fiber grating sensing network is designed, and the measurement experiment is carried out. The results show that the relative error of the proposed method is less than 5%, which can realize the high-precision measurement of on-orbit thermal strain of spacecraft plate components.

关 键 词：板状部件 光纤光栅传感器 实验设计 热应变测量 

分 类 号：TN9[电子电信—信息与通信工程]