基于光纤和柔性传感器的固体火箭发动机结构监测技术研究  

Research on structural monitoring technology of solid rocket motor based on optical fiber and flexible sensor

作　　者：李双江 刘向阳[1] 章喆 张晋尚 郭浩然 LI Shuangjiang;LIU Xiangyang;ZHANG Zhe;ZHANG Jinshang;GUO Haoran(School of Astronautics,Beijing Institute of Technology,Beijing100081,China;Southwest Institute of Technology and Engineering,Chongqing400039,China)

机构地区：[1]北京理工大学宇航学院,北京100081 [2]西南技术工程研究所,重庆400039

出　　处：《固体火箭技术》2024年第4期511-518,共8页Journal of Solid Rocket Technology

摘　　要：结构监测对于固体火箭发动机的结构可靠性有着重要意义。发动机界面的温度、应变和应力以及内孔表面的应变均是结构监测的重要参数。利用惰性推进剂圆管发动机,通过在衬层/推进剂和绝热层/衬层两个界面布设FBG光纤传感器和内腔粘贴柔性应变传感器实现发动机药柱结构监测,并通过温度循环载荷试验获得界面温度、轴向应变、环向应变和主应力以及内孔环向应变等数据,验证了结构监测技术的有效性和适用性。试验结果表明,两个界面的温度和轴向应变较为一致;绝热层/衬层界面的环向应变一致性明显优于衬层/推进剂界面,其原因在于传感器在前者中更易定位;基于直角应变花方式测得的界面主应力幅值约为0.007 4 MPa;2个柔性应变传感器测得的内孔环向应变较为一致,幅值分别为13.4%和13.8%,可用于大应变监测。研究结果可为发动机结构监测系统研制和导弹系统的可靠性提供技术参考。Structural monitoring is of great significance for the structural reliability of solid rocket motors.Temperature,strain and stress of motor interface as well as strain on the inner hole surface belongs to important parameters for structural monitoring.The circular tube motor with inert propellant was used to monitor the motor interface structure by laying FBG optical fiber sensors and sticking flexible strain sensors in the inner cavity at the two interfaces of liner/propellant and insulation/liner,and the data of inter⁃face temperature,axial strain,hoop strain and principal stress,as well as inner hole hoop strain were obtained through temperature cycle loading test,which verifies effectiveness and applicability of the structural monitoring technology.The test results show that temperature and axial strain of the two interfaces are relatively consistent.The hoop strain consistency of the insulation/liner inter⁃face is significantly better than that of the liner/propellant interface,because the sensor is easier to be fixed in the former.The am⁃plitude of the interfacial principal stress measured by the right⁃angle strain rosette is about 0.0074 MPa,and the circumferential strain of the inner bore measured by the two flexible strain sensors is relatively consistent,with amplitudes of 13.4%and 13.8%,respectively,which can be used for large strain monitoring.The research results can provide technical references for the develop⁃ment of motor structure monitoring systems and the reliability of missile systems.

关 键 词：固体火箭发动机 结构监测 FBG传感器 柔性应变传感器 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]