复合材料层板光纤冲击判位与载荷历程重构方法

doi:10.19936/j.cnki.2096-8000.20240928.008

复合材料科学与工程 ›› 2024, Vol. 0 ›› Issue (9): 52-56.DOI: 10.19936/j.cnki.2096-8000.20240928.008

复合材料层板光纤冲击判位与载荷历程重构方法

冯振辉¹, 王哲², 曾捷^2*, 陈斌斌², 冯春乐², 周帆³

1.南京晨光集团有限责任公司航天理化分析和无损检测研究所,南京 210006;
2.南京航空航天大学航空学院,南京 210016;
3.中国航天科工集团第三研究院创新研究院,北京 100074

收稿日期:2024-01-29 出版日期:2024-09-28 发布日期:2024-10-18
通讯作者: 曾捷(1976—),男,博士,副教授,硕士生导师,主要从事光纤传感技术及其在航空航天领域应用方面的研究,zj2007@nuaa.edu.cn。
作者简介:冯振辉(1996—),男,硕士,助理工程师,主要从事无损检测技术方面的研究。
基金资助:
国家自然科学基金(52275536);航空科学基金(20220028052002);直升机旋翼动力学国家级重点实验室基金(61422202207);科技部国家重点研发计划(2021YFC2802300);南京航空航天大学大学生创新训练计划(2023CX001058)

A method for optical fiber impact localization and load history reconstruction of composite laminates

FENG Zhenhui¹, WANG Zhe², ZENG Jie^2*, CHEN Binbin², FENG Chunle², ZHOU Fan³

1. Institute of Aerospace Physical and Chemical Analysis and Non Destructive Testing, Nanjing Chenguang Group Co., Ltd., Nanjing 210006, China;
2. College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
3. Innovation & Research Institute, Hiwing Technology Academy of CASIC, Beijing 100074, China

Received:2024-01-29 Online:2024-09-28 Published:2024-10-18

摘要/Abstract

摘要： 针对典型航空航天器复合材料层板冲击载荷识别需求,提出了一种基于光纤Bragg光栅传感器的复合材料层板冲击响应特征辨识方法。基于光纤Bragg光栅传感器离散应变感知信息,发展了基于距离倒数乘方原理的复合材料层板冲击应变响应反演方法。基于冲击响应突变特征并结合极值比较法,辨识出冲击载荷对应的应变响应峰值所在位置。在辨识出冲击位置的基础上,提出采用贝叶斯正则化法对复合材料层板冲击载荷进行重构,有效解决了常规载荷历程重构中脉冲响应矩阵病态性造成的不适定性问题。实验结果显示,冲击点与辨识点坐标之间平均误差约为13.00 mm,重构所得冲击载荷有效作用历程内平均相对误差约为4.21%,载荷峰值辨识相对误差为3.85%。

关键词: 复合材料层板, 光纤Bragg光栅传感器, 冲击载荷位置, 载荷历程重构, 距离倒数乘方, 非负贝叶斯正则化

Abstract: A method for identifying the impact response characteristics of composite laminates based on fiber Bragg grating sensors is proposed for typical aerospace composite laminates. Based on the discrete strain sensing information of fiber Bragg grating sensors, a composite laminate impact strain response inversion method based on the principle of distance reciprocal multiplication has been developed. Based on the sudden change characteristics of the impact response and combined with the extreme value comparison method, identify the position of the strain response peak corresponding to the impact load. On the basis of identifying the impact position, the Bayesian regularization method is proposed to reconstruct the impact load of composite laminates, effectively solving the ill posed problem caused by the ill posed pulse response matrix in conventional load history reconstruction. The experimental results show that the average error between the coordinates of the impact point and the identification point is about 13.00 mm. The average relative error within the effective action history of the reconstructed impact load is about 4.21%, and the relative error for identifying the peak load is 3.85%.

Key words: composite laminates, fiber bragg grating sensor, impact load position, load history reconstruction, the power of the reciprocal of distance, non negative bayesian regularization

中图分类号:

TB332

冯振辉, 王哲, 曾捷, 陈斌斌, 冯春乐, 周帆. 复合材料层板光纤冲击判位与载荷历程重构方法[J]. 复合材料科学与工程, 2024, 0(9): 52-56.

FENG Zhenhui, WANG Zhe, ZENG Jie, CHEN Binbin, FENG Chunle, ZHOU Fan. A method for optical fiber impact localization and load history reconstruction of composite laminates[J]. COMPOSITES SCIENCE AND ENGINEERING, 2024, 0(9): 52-56.

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复合材料层板光纤冲击判位与载荷历程重构方法

A method for optical fiber impact localization and load history reconstruction of composite laminates

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