基于振动测量的热防护结构脱粘损伤检测方法
Vibration based debonding damage detection of thermal protection structures
金嘉炜 1张超 1陶翀骢 1张宇鹏 2裘进浩 1季宏丽1
作者信息
- 1. 南京航空航天大学航空航天结构力学及控制全国重点实验室 南京 210016
- 2. 中国航天科工飞航技术研究院 创新研究院 北京 100074
- 折叠
摘要
针对典型飞行器热防护结构脱粘损伤现场快速无损检测的需求,提出了一种基于敲击测量频响函数的脱粘损伤识别方法.首先,利用有限元方法建立了含脱粘损伤的热防护结构有限元模型并进行了振动特性分析,分析了脱粘损伤引起的结构局部刚度下降规律以及频响函数对脱粘损伤的敏感性;其次,确定了脱粘损伤识别的特征频率范围,给出了一个脱粘损伤指标;最后,采用力锤与激光多普勒测振仪对含脱粘的热防护结构进行了测量.实验结果表明,当脱粘面积达到60%时,脱粘损伤指标比健康件增加了1倍以上,当脱粘面积达到80%时,脱粘损伤指标为健康件的5倍以上,验证了所提出的方法能够有效识别出热防护结构的脱粘损伤.
Abstract
Debonding damage identification method based on the frequency response function measurement is proposed to meet the demand for rapid on-site nondestructive inspection of typical aircraft thermal protection structures.Firstly,a finite element model of the thermal protection structure with debonding damage was established using finite element method and vibration characteristic analysis was performed.In addition,the local stiffness reduction caused by debonding damage and the sensitivity of the frequency response function to debonding damage were analyzed.Then,a characteristic frequency range for debonding damage identification was given,and a debonding damage index was defined.Finally,a thermal protection structure with debonding damage was tested by using a force hammer and laser Doppler vibrometer.The experimental results show that when the debonding area reaches 60%,the debonding damage index is more than doubled compared to the healthy parts,and when the debonding area reaches 80%,the debonding damage index is more than five times that of the healthy parts,which verifies that the proposed method in this paper is able to identify the debonding damage of thermal protection structure effectively.
关键词
热防护结构/模态分析/频响函数/脱粘检测Key words
thermal protection structure/modal analysis/frequency response function/debonding detection引用本文复制引用
基金项目
国家自然科学基金(52175141)
国家自然科学基金(52235003)
国家自然科学基金(51921003)
江苏省自然科学基金(BK20220133)
出版年
2024
NETL
NSTL
维普
万方数据