融合导波监测的搭接结构裂纹扩展寿命孪生预测  

Digital Twins Prediction of Crack Growth Life for the Lap Joint Structure Combined with Guided Wave Monitoring Data

作　　者：陈健[1] 孟义兴 袁慎芳[1] 徐秋慧 王卉[1] CHEN Jian;MENG Yixing;YUAN Shenfang;XU Qiuhui;WANG Hui(College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016)

机构地区：[1]南京航空航天大学航空学院,南京210016

出　　处：《机械工程学报》2024年第16期34-42,共9页Journal of Mechanical Engineering

基　　金：国家自然科学基金创新群体(51921003);国家自然科学基金青年(52205160);国家自然科学基金面上(52275153);江苏省自然科学基金青年(BK20220874);江苏高校优势学科建设工程资助项目。

摘　　要：飞行器的高性能和长寿命需求对传统结构设计维护方法的变革提出了迫切要求。在数字孪生的理论思想下,提出一种飞行器搭接结构裂纹扩展寿命的在线预测方法,首先利用裂纹扩展准则和有限元模型建立搭接结构的数字孪生体及其代理模型,在结构服役过程中采用主动导波监测方法对物理实体搭接结构的裂纹长度进行监测,进一步通过贝叶斯滤波方法对搭接结构裂纹扩展准则参数进行修正,在此基础上结合数字孪生代理模型开展结构疲劳裂纹扩展寿命预测。通过蒙皮搭接结构的疲劳试验对方法进行验证,裂纹长度诊断结果的方均根误差为0.8 mm,在8万个载荷循环后裂纹扩展寿命预测结果的最大误差小于5%,表明了方法的有效性。Requirements for the high performance and long service life of aircraft lead to the urgent need for a revolution against traditional structural design and maintenance strategies.In the theoretical framework of the digital twin,an online prediction method of crack growth life for the lap joint structure of aircraft is proposed.The digital twin of the physical structure and its surrogate model is established using the a priori crack growth rule and the finite element model.During the service of the structure,the active guided wave monitoring method is used to monitor the cracks of the actual lap joint structure online.Further,parameters of the crack growth rule of the lap joint structure are corrected by using Bayesian filtering,which is combined in the digital twin for predicting its fatigue crack growth life.The proposed method is validated on the fatigue test of lap joint structures in the aircraft skin.The root means square of the diagnosed crack length is 0.8 mm and the relative error of the predicted fatigue crack growth life is 5%after 80000 loading cycles,showing the effectiveness of the method.

关 键 词：搭接结构 裂纹扩展寿命预测 数字孪生 导波结构健康监测 贝叶斯滤波 

分 类 号：V215[航空宇航科学与技术—航空宇航推进理论与工程]