摘要
确定固体火箭发动机工作时的真实燃速是发动机研制中的难题,而利用超声波测量是目前比较可行的方案。综述了利用超声波测量动态燃速和大尺寸发动机燃速的相关技术,并针对低频超声波开展了钢壳体/推进剂组合件的静态试验和钢壳体固体发动机热试车试验验证。通过综述和试验验证指出采用低频超声波是测量大尺寸固体发动机燃速的最可行的方案,提出进一步的研究方向是优化探头布置方案,并给出超声数据处理的建议。
Measuring the true burning rate of a solid rocket motor(SRM)is a challenging problem in SRM research and development.Ultrasonic measurement has been proven to be a feasible solution.This study provides an overview of the related technologies for measuring dynamic and large-scale motor burning rates using ultrasonic technology.Static tests of steel shell/propellant assembly and high-temperature verification tests of the steel shell solid motor are carried out using low-frequency ultrasonic technology.After review and experimental verification,it is determined that low-frequency ultrasonic is the most feasible approach for measuring the burning rate of large-scale SRM.A further research direction is to optimize the probe layout.The study also provides suggestions for ultrasonic data processing.
作者
孙得川
贤光
SUN Dechuan;XIAN Guang(School of Aeronautics and Astronautics,Dalian University of Technology,Dalian 116024,Liaoning,China;The 41st Research Institute of No.6 Academy,China Aerospace Science&Industry Corporation,Hohhot 010010,Inner Mongolia,China)
出处
《兵工学报》
EI
CAS
CSCD
北大核心
2023年第4期1097-1106,共10页
Acta Armamentarii
基金
国防科技工业局支持项目(2020年)。
关键词
超声波
燃速
固体火箭发动机
大尺寸
ultrasonic
burning rate
solid rocket motor
large scale
