空间伸展结构变形与振动分布式光纤监测研究  

Research on spatial deployable structure deformation and vibration monitoring with distributed optical fiber

作　　者：何凯 曾捷[1] 林秋红[2] 龚晓静 康健[1] He Kai;Zeng Jie;Lin Qiuhong;Gong Xiaojing;Kang Jian(State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics ＆ Astronautics Nanfing 210016, China;General Office of China Academy of Space Technology, Beijing 100094, China;Institute Clement ADER UMR CNRS 5312（ INSA/UPS/1SAE/Mines Albi） ） , University De Toulouse, Toulouse 31000, France)

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]中国空间技术研究院总体部,北京100094 [3]法国图卢兹大学法国国家科学研究中心Clement ADER航空结构实验室(UMR CNRS 5312),图卢兹31000

出　　处：《仪器仪表学报》2018年第2期56-65,共10页Chinese Journal of Scientific Instrument

基　　金：国家自然科学基金-联合基金(U1537102);航空科学基金(20152852036);上海航天科技创新基金(SAST2015062);中央高校基本科研业务费专项资金(NS2016004);机械结构力学及控制国家重点实验室开放课题(MCMS-0516K01);江苏高校优势学科建设工程基金(PAPD)项目资助

摘　　要：空间伸展结构是一种最基本的可展开折叠单元,广泛应用于大型展开天线、太阳帆板以及空间机械臂等航天领域,针对此类结构服役状态的智能辨识对于目前开展高轨深空探测研究具有重要意义。为此,提出一种基于准分布式光纤传感器的空间伸展结构变形与振动实时监测技术。借助MSC.Patran/Nastran有限元分析方法,数值模拟得到碳纤维复合材料柔性空间伸展结构在不同载荷作用下的应变、位移响应规律以及振动模态特征。分别研究了基于曲率和弧长信息曲线重构的结构变形反演算法,光纤光栅中心波长偏移量与振动特征关系解析模型,计算得到空间伸展结构沿展开方向不同位置的坐标信息。在此基础上,通过在柔性复合材料伸展结构展向布设离散光纤光栅传感器,实时采集应变分布与变化信息,进而推导相应位置曲率特征,实现不同加载模式下的伸展结构形态重构,变形反演相对误差约为2.5%。此外,借助准分布式光纤传感器不仅可以得到伸展结构对应的变形实时响应曲线,同时还能够获取其前三阶固有模态和振型特征,所测频率与仿真结果吻合度较好,平均误差约为0.67%。研究结果表明,所提方法具有非视觉测量、实时性好以及多种功能复用等优点,能够为未来及时准确获取空间伸展结构姿态,实现空间形态自适应调节与在轨振动主动控制提供有力保障。Spatial deployable structure is one of the most basic deployable folding elements. It is widely used in large deployable antenna,solar array and space manipulator and other aerospace areas. At present,intelligent identification of the service state of such structures is of great significance for the development of high orbit deep space exploration. Therefore,a real-time monitoring technique for deformation and vibration of space deployable structure based on quasi-distributed optical fiber sensor is proposed in this paper. With the MSC. Patran/Nastran finite element analysis method,the strain,displacement response regularity and vibration modal characteristics of the flexible deployable structure based on carbon fiber composite under different loads are obtained by numerical simulation. The inversion algorithm of structural deformation based on curvature and arc length information curve reconstruction is studied. The analytical model of relationship between center wavelength offset and vibration characteristics of fiber gratings are formulated respectively. The coordinate information of space deployable structure in different positions along the stretch direction is achieved. On the basis,a series of discrete fiber Bragg grating sensors are deployed along stretch direction of the flexible composite deployable structure. The strain distribution and variation information are acquired in real time. The curvature characteristics of the corresponding position are deduced to realize the morphological reconstruction of the deployable structure under different loading modes. The relative error of deformation inversion is approximate 2. 5%. In addition,the real time deformation response curves corresponding to the deployable structure can beobtained with the quasi-distributed optical fiber sensor. Its first three order natural modal and vibration characteristics are also measured and the frequencies are consistent with the simulation results. The average error is approximate 0. 67%. The experimental results show that the

关 键 词：柔性复合材料伸展结构 光纤传感器 形态反演算法 变形监测 振动监测 

分 类 号：TN913.7[电子电信—通信与信息系统] TP212[电子电信—信息与通信工程]