人工脱粘结构界面脱粘原位高频振动监检测方法  

In-situ high-frequency vibration monitoring method for interface debonding of stress release boot

作　　者：叶子航 张守诚[1] 肖黎[1] 屈文忠[1] 沙宝林 YE Zihang;ZHANG Shoucheng;XIAO Li;QU Wenzhong;SHA Baolin(Department of Engineering Mechanics,Wuhan University,Wuhan 430072,China;The 41st Institute of the Fourth Academy of CASC,Xi'an 710025,China)

机构地区：[1]武汉大学工程力学系,武汉430072 [2]中国航天科技集团有限公司四院四十一所,西安710025

出　　处：《固体火箭技术》2022年第3期453-459,共7页Journal of Solid Rocket Technology

基　　金：国家自然科学基金项目(51975581)。

摘　　要：针对固体发动机人工脱粘结构的界面脱粘原位监检测问题,以人工脱粘结构的绝热层/药柱界面模型试件为研究对象,基于结构表面黏贴布置的压电晶片高频局部振动方法,进行了绝热层/药柱界面脱粘实验研究,得出了不同损伤工况下的高频局部振动响应曲线,并利用均方根偏差值对不同工况下的界面脱粘损伤进行了定量分析,发现量化指标随着脱粘区域面积的增大而增大。此外,研究了温度对高频局部振动方法的影响,并结合温度补偿算法进行了温变工况下的界面脱粘损伤监检测实验。结果表明,该高频局部振动方法可有效识别人工脱粘结构的界面脱粘损伤状态,为固体发动机人工脱粘结构界面状态的原位监检测工程实际应用提供了一种新的思路和技术支撑。Aiming at the in-situ monitoring of interface debonding of stress release boot in solid rocket motor,the specimen of insulator/propellant interface model of stress release boot was taken as the research object.Based on the high-frequency local vibra-tion method of piezoelectric wafers attached to the structure surface,the experiment of insulator/propellant grain interface debonding was carried out,and the high-frequency local vibration response curves under different damage conditions were obtained.The root mean square deviation was used to quantitatively analyze the interface debonding damage under different working conditions.It is found that the quantitative index increase with the increase of debonding area.In addition,the influence of temperature on the high-frequency local vibration method was studied.Combined with the temperature compensation algorithm,the monitoring experiment of interface debonding damage under the condition of temperature variation was conducted.The experimental results demonstrate that the high-frequency local vibration method can effectively identify the interface debonding damage state of the stress release boot,which provides a new idea and technical support for the practical in-situ monitoring of stress release boot in solid rocket motor.

关 键 词：人工脱粘结构试件 界面脱粘 压电晶片 高频局部振动 温度补偿 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]