C/C热防护结构高温气流损伤导波监测实验方法  

Experimental method of guided wave monitoring for high temperature airflow damage of C/C thermal protection structures

作　　者：郑辉[1] 邱雷[1] 袁慎芳[1] 杨晓飞[1] 卢绪龙 薛兆鹏 ZHENG Hui;QIU Lei;YUAN Shenfang;YANG Xiaofei;LU Xulong;XUE Zhaopeng(Research Center of Structural Health Monitoring and Prognosis,State Key Lab of Mechanics and Control of Mechanical Structures,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

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,结构健康监测与预测研究中心,南京210016

出　　处：《航空学报》2022年第8期422-434,共13页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(51921003,51975292);江苏省杰出青年基金(BK20211519);机械结构力学及控制国家重点实验室自主课题重点项目(MCMS-I-0521K01);中央高校基本科研业务费专项资金(1001-XAC21022);江苏高校优势学科建设工程资助。

摘　　要：热防护结构(TPS)的健康监测对高超声速飞行器的安全服役和高效运维至关重要。导波结构健康监测(SHM)方法具有灵敏度高、通过压电传感器组网可实现大面积区域监测等优点,是一种很有前景的高超声速飞行器结构健康监测方法,但目前国内外针对高超声速飞行器TPS导波监测方法的相关研究很少,其中TPS高温气流损伤实验和监测方面的研究更少。针对该问题,提出了基于导波的高超声速飞行器TPS真实损伤监测实验方法,以碳/碳(C/C)复合材料TPS为具体研究对象,通过大于1800℃的氧-乙炔高温气流烧蚀TPS施加真实损伤,开展了导波在TPS上的传播特性研究,从损伤前后导波信号和特征参数的对比以及损伤程度的表征等方面分析了损伤对导波的影响。结果表明,损伤产生后TPS上导波幅值和波速发生明显变化,通过对导波信号在损伤前后的变化程度进行量化,可以反映出TPS损伤程度,验证了导波监测方法对TPS损伤及其扩展的监测是可行的,为进一步开展高超声速飞行器TPS导波监测理论和方法的研究提供了一种实验方法和依据。The health monitoring of Thermal Protection Structures(TPS)is essential for the safe service and efficient maintenance of hypersonic vehicles.The guided wave based Structural Health Monitoring(SHM)method is a promising method for SHM of hypersonic vehicles,due to its advantages,such as high sensitivity and large monitoring area based on piezoelectric sensor network.However,there are few relevant researches on guided wave monitoring methods for hypersonic vehicles TPS at home and abroad,especially on the experimental and monitoring method for the high-temperature airflow damage on TPS.To solve this problem,an experimental method based on guided waves for the real damage monitoring of hypersonic vehicles TPS is proposed.Through taking the carbon/carbon(C/C)composite TPS as the research object and applying real damage onto it via a high-temperature oxygen-acetylene gas flow above 1800℃,the propagation characteristics of guided wave on TPS are studied.The influence of damage on guided waves is analyzed in terms of the comparison of the signal and characteristic parameters of guided waves before and after damage and the characterization of the damage degree.The results show that the amplitude and propagation velocity of the guided wave change significantly after the damage occurred.By quantifying the change of the guide wave signals before and after damage,the damage degree of TPS can be good indicated,which verifies that the guided wave monitoring method is feasible for monitoring TPS damage and its expansion,providing an experimental method and basis for further research on the guided wave monitoring theory and method of hypersonic vehicles TPS.

关 键 词：高超声速飞行器 热防护结构 碳/碳 结构健康监测 导波 氧-乙炔烧蚀 

分 类 号：V417.3[航空宇航科学与技术—航空宇航推进理论与工程] V448.25[理学—物理] TB553[理学—声学]