摘要
为实现对固体火箭发动机装药结构试件界面应力的实时原位监测,提出了一种基于柔性传感器的界面应力测试方法,分别将柔性压阻传感器与柔性电容传感器预先埋入装药结构试件界面中,通过拉伸机进行扯离实验和剪切实验。结合NI虚拟仪器系统和LabVIEW图形化软件搭建装药结构界面应力监测系统,在试件扯离和剪切过程中通过对传感器的输出电阻和电容的实时监测以研究装药结构试件的界面应力变化情况。实验结果表明,随着扯离和剪切实验进行,柔性压阻传感器输出电阻由374.7Ω增大至3705Ω,正应力大小由0.4085 MPa减小至0.0297 MPa;柔性电容传感器输出电容由298 pF减小至296.7 pF。验证了嵌入式柔性传感器监测和表征装药结构试件界面应力的可行性以及装药结构界面应力监测系统的可靠性。
In order to realize the real-time in-situ monitoring of the interface stress of the solid rocket motor charge structure specimen,a flexible-sensor-based interface stress test method was proposed.The flexible piezo resistive sensor and the flexible capacitance sensor were embedded in the interface of the charge structure specimen in advance.The tearing and shearing experiments were carried out by the tensile machine.Combining NI virtual instrument system and LabVIEW graphical software to build the interface stress monitoring system.The interface stress variation of the specimen was studied by real-time monitoring of the output resistance and capacitance of the flexible sensors during tearing and shearing.The experiment results show that with the tearing and shearing experiments,the output resistance of the flexible piezoresistive sensor increases from 374.7Ωto 3705Ω,and the magnitude of the normal stress decreases from 0.4085 MPa to 0.0297 MPa;the output capacitance of the flexible capacitive sensor decreases from 298 pF to 296.7 pF.The feasibility of the embedded flexible sensor to monitor and characterize the interface stress of charge structure and the reliability of the interface stress monitoring system of charge structure are verified.
作者
张松涛
金东晖
屈文忠
肖黎
黄凯
ZHANG Songtao;JIN Donghui;QU Wenzhong;XIAO Li;HUANG Kai(Department of Engineering Mechanics,Wuhan University,Wuhan 430072,China)
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2020年第4期511-517,共7页
Journal of Solid Rocket Technology
基金
国家自然科学基金(51975581)。
作者简介
张松涛(1996-),男,硕士,研究方向为结构健康监测。E-mail:zhangsongtao@whu.edu.cn;通讯作者:肖黎(1975-),女,副教授,研究方向为结构健康监测。E-mail:xiaolily@whu.edu.cn。
