层状碳纤维复合材料结构热应变光纤传感特性研究  

Study on Thermal Strain Optical Fiber Sensing Characteristics ofLaminated Carbon Composite Structures

作　　者：胡雪雯 张泽敏 郭智 周康鹏 孙广开[1,2] HU Xuewen;ZHANG Zemin;GUO Zhi;ZHOU Kangpeng;SUN Guangkai(Beijing Engineering Research Center of Optoelectronic Information and Instrument,Beijing Information Science&Technology University,Beijing 100016,China;Beijing Information Science&Technology University,School of Instrumentation Science and Optoelectronic Engineering,Beijing 100192,China;Beijing Institute of Space Mechanics&Electricity,Beijing 100094,China;School of Precision Instrument&Electronics Engineering,Tianjin University,Tianjin 300072,China)

机构地区：[1]北京信息科技大学光电信息与仪器北京市工程研究中心,北京100016 [2]北京信息科技大学仪器科学与光电工程学院,北京100192 [3]北京空间机电研究所,北京100094 [4]天津大学精密仪器与光电子工程学院,天津300072

出　　处：《航天器工程》2023年第2期39-47,共9页Spacecraft Engineering

基　　金：国家自然科学基金(51705024)。

摘　　要：针对高分辨率遥感卫星关键载荷复合材料支撑结构热变形光纤在轨监测需求,研究层状复合材料结构热应变光纤光栅传感特性。首先,采用有限元方法分析得出层状复合材料结构在局部热载荷作用下热应变场分布特征;然后,制作层状复合材料结构试件,建立光纤光栅热应变监测实验系统;最后,以同样尺寸的铝合金结构为对比试件,实验分析T700级碳纤维增强复合材料层压板的热应变传感特性。实验数据表明,在30~100℃范围内,碳纤维复合材料结构热应变随温度升高而近似线性增大,但其热应变量明显小于同一温度下铝合金结构热应变;碳纤维复合材料的热应变场呈各向异性分布特征,100℃时其轴向和径向应变的光纤光栅测量值分别为155.8με、181.3με,与仿真计算结果的平均相对误差为1.58%、1.52%。利用光纤光栅传感器能够有效测量碳纤维复合材料结构的热应变,研究结果可为高分辨率遥感卫星层状复合材料结构光纤在轨监测提供参考。The sensing characteristics of thermal strain fiber Bragg grating in layered composite structures are studied to meet the in-orbit monitoring requirements of critical load composite structures of high-resolution remote sensing satellites.Firstly,the finite element method is used to analyze the thermal strain field distribution characteristics of laminated composite structure under local thermal load.Then,the lamellar composite structure specimen is made,and the thermal strain monitoring experimental system of fiber Bragg grating sensors is established.Finally,the thermal strain sensing characteristics of T700 carbon fiber reinforced composite laminate were experimentally analyzed with aluminum alloy structure as the contrast specimen.The experimental data show that the thermal strain of carbon fiber composite structure increases approximately linearly with increasing temperature in the range of 30℃to 100℃,but the thermal strain of carbon fiber composite structure is significantly smaller than that of aluminum alloy structure at the same temperature.The thermal strain field of the carbon fiber composite is anisotropic.At 100℃,the axial and radial strain values of the fiber Bragg grating are 155.8μεand 181.3με,respectively.The average relative errors with the simulation results are 1.58%and 1.52%.The thermal strain of carbon fiber composite structure can be measured effectively by using fiber Bragg grating sensors.The research results can provide a reference for on-orbit monitoring of lamellar composite fiber in high-resolution remote sensing satellites.

关 键 词：层状碳纤维复合材料 有限元仿真 光纤传感 遥感卫星 热应变 

分 类 号：V19[航空宇航科学与技术—人机与环境工程]