基于光纤光栅传感网络的变形监测研究
发布时间：2018-12-14 15:34
【摘要】：应变、变形、振动监测与控制是航空航天领域的研究基础,是不可或缺的部分。对结构的应变变形准确的监测,是进行航空航天结构参数后续测量的前提。因此本文对复合材料板和机翼结构进行变形重构分析,主要包括以下几个方面:首先,基于应变传递理论,提出一种改进型光纤光栅传感器与复合材料集成方法。并通过理论与试验同时验证改进型光纤光栅的集成方法具有良好的应变监测效果,证明本文讨论的光纤光栅传感器与复合材料的集成方法具有良好的工程实用意义。其次,讨论了一种基于分布式光纤光栅传感网络的应变信息曲率信息转换关系的变形重构方法和基于双重积分方法的变形重构方法。在仿真的基础上,对单边固支环氧板进行了均布加载实验,利用光纤光栅传感器监测数据重构变形位移。再次,在机翼结构模型上设计了4种加载方式,分别表示弯曲与扭转情况。利用光纤光栅传感器测得的波长信息转化为监测点的曲率信息,并利用曲率信息重构不同加载情况下的变形。利用正交方向上的曲率信息拟合机翼结构的变形曲面片重构,并展示了曲面重构过程,最后对变形重构进行了均方根误差分析。利用粘贴于机翼翼面上的加速度传感器大致估计出机翼结构的模态固有频率。之后利用光纤光栅传感器测得的波长信息与激振力之间的频响函数,求出该机翼的模态参数。
[Abstract]:Strain, deformation, vibration monitoring and control are the basic and indispensable part of aerospace research. Accurate monitoring of structural strain deformation is the prerequisite for subsequent measurement of aerospace structure parameters. Therefore, the deformation reconstruction analysis of composite plate and wing structure is carried out in this paper, including the following aspects: firstly, based on the strain transfer theory, an improved method of integrating fiber Bragg grating sensors with composite materials is proposed. At the same time, both theoretical and experimental results show that the improved method has good strain monitoring effect, which proves that the integrated method of fiber Bragg grating sensor and composite material discussed in this paper has good practical significance in engineering. Secondly, a deformation reconstruction method based on the transformation of curvature information of strain information based on distributed fiber Bragg grating sensor network and a deformation reconstruction method based on double integral method are discussed. On the basis of simulation, the uniform loading experiment of single-side clamped epoxy plate was carried out, and the deformation displacement was reconstructed by using fiber Bragg grating sensor. Thirdly, four loading modes are designed on the wing structure model to represent bending and torsion respectively. The wavelength information measured by fiber Bragg grating sensor is converted into the curvature information of monitoring points, and the deformation under different loading conditions is reconstructed by using the curvature information. The curvature information in orthogonal direction is used to fit the deformation surface reconstruction of wing structure, and the process of surface reconstruction is demonstrated. Finally, the root mean square error analysis of deformation reconstruction is carried out. The modal natural frequency of the wing structure is estimated by the acceleration sensor affixed to the wing surface. Then the modal parameters of the wing are obtained by using the frequency response function between the wavelength information and the exciting force measured by the fiber grating sensor.
【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：V216
，
本文编号：2378878
[Abstract]:Strain, deformation, vibration monitoring and control are the basic and indispensable part of aerospace research. Accurate monitoring of structural strain deformation is the prerequisite for subsequent measurement of aerospace structure parameters. Therefore, the deformation reconstruction analysis of composite plate and wing structure is carried out in this paper, including the following aspects: firstly, based on the strain transfer theory, an improved method of integrating fiber Bragg grating sensors with composite materials is proposed. At the same time, both theoretical and experimental results show that the improved method has good strain monitoring effect, which proves that the integrated method of fiber Bragg grating sensor and composite material discussed in this paper has good practical significance in engineering. Secondly, a deformation reconstruction method based on the transformation of curvature information of strain information based on distributed fiber Bragg grating sensor network and a deformation reconstruction method based on double integral method are discussed. On the basis of simulation, the uniform loading experiment of single-side clamped epoxy plate was carried out, and the deformation displacement was reconstructed by using fiber Bragg grating sensor. Thirdly, four loading modes are designed on the wing structure model to represent bending and torsion respectively. The wavelength information measured by fiber Bragg grating sensor is converted into the curvature information of monitoring points, and the deformation under different loading conditions is reconstructed by using the curvature information. The curvature information in orthogonal direction is used to fit the deformation surface reconstruction of wing structure, and the process of surface reconstruction is demonstrated. Finally, the root mean square error analysis of deformation reconstruction is carried out. The modal natural frequency of the wing structure is estimated by the acceleration sensor affixed to the wing surface. Then the modal parameters of the wing are obtained by using the frequency response function between the wavelength information and the exciting force measured by the fiber grating sensor.
【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：V216
，
本文编号：2378878
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