复合材料层板OFDR分布式光纤冲击判位方法研究  

OFDR Distributed Optical Fiber Impact Localization Method of Composite Laminate

作　　者：钟照振 曾捷[1] 李艳芬[2] 白瑜芳 黄继伟 綦磊[3] ZHONG Zhaozhen;ZENG Jie;LI Yanfen;BAI Yufang;HUANG Jiwei;QI Lei(State Key Laboratory of Mechanics and Control of Aerospace Structures,Nanjing University of Aeronautics and Astronautics Nanjing,210016,China;Beijing Institute of Structure&Environment Engineering Beijing,100076,China;Beijing Institute of Spacecraft Environment Engineering Beijing,100094,China)

机构地区：[1]南京航空航天大学机械结构力学及控制国家重点实验室,南京210016 [2]北京强度环境研究所,北京100076 [3]北京卫星环境工程研究所,北京100094

出　　处：《振动．测试与诊断》2023年第5期1005-1010,1044,共7页Journal of Vibration,Measurement & Diagnosis

基　　金：南京航空航天大学高校联合创新基金资助项目(CALT201808);航空科学基金资助项目(20185644006);上海航天科技创新基金资助项目(SAST2018-015);江苏省重点研发计划资助项目(BE2018047);直升机旋翼动力学国家级重点实验室基金资助项目(61422202207)。

摘　　要：基于复合材料的航空航天器结构在服役过程中受到外界物体冲击易造成损伤,常规光纤Bragg光栅冲击监测模式需要借助大量试验建立冲击响应样本库,不仅工作量大,还会影响被测结构力学性能,甚至造成预先损伤。为此,提出了一种基于应变幅值非线性加权原理的复合材料层板结构分布式光纤冲击位置辨识方法,通过提取结构应变响应幅值作为特征量,结合无需先验样本的非线性加权原理实现冲击载荷位置辨识。借助有限元数值仿真,模拟得到冲击载荷作用下复合材料层板结构应变响应与分布特征,并根据仿真结果对该辨识方法加以验证。构建了基于高空间分辨率分布式光纤传感器的冲击监测系统,平均定位误差约为8.44 mm。研究表明,所提方法具有便于集成、通用性强以及无需构建样本库等特点,能够为航空航天器结构健康监测、寿命评估和快速维护提供技术支撑。Aerospace vehicle structures based on composite materials are easily damaged by impacts from external objects during service.The conventional fiber Bragg grating impact monitoring mode requires a large number of experiments to establish an impact response sample library,which not only requires a lot of work,but also affects the mechanical properties of the tested structure and even causes pre-damage.For this reason,this paper proposes a method for identifying the impact position of distributed optical fiber based on the principle of nonlinear weighting of strain amplitude.The method extracts the structural strain response amplitude as the characteristic quantity,and combines the principle of nonlinear weighting without prior samples to realize the impact load position identification.With the aid of finite element numerical simulation,the strain response and distribution characteristics of composite laminate structure under impact load are simulated,and the identification method is verified according to the simulation results.An impact monitoring system based on a high spatial resolution distributed optical fiber sensor is constructed,and the average positioning error is about 8.44 mm.Research shows that the method proposed in this paper has the characteristics of easy integration,strong versatility,and no need to build a sample library,and can provide technical support for the structural health monitoring,life evaluation and rapid maintenance of spacecraft.

关 键 词：复合材料层板 分布式光纤传感器 冲击定位 非线性加权 应变响应 

分 类 号：TH741[机械工程—光学工程] V214.8[机械工程—仪器科学与技术] V414.8[机械工程—精密仪器及机械]