基于超声的标准发动机动态燃速测试技术  

Dynamic burning rate measurement of standard SRM based on ultrasonic technology

作　　者：邱飞 高永刚 张荣 闫磊 QIU Fei;GAO Yonggang;ZHANG Rong;YAN Lei(Xi’an Aerospace Propulsion Testing Technique Institute,Xi’an 710025,China)

机构地区：[1]西安航天动力测控技术研究所,西安710025

出　　处：《固体火箭技术》2024年第1期128-134,共7页Journal of Solid Rocket Technology

摘　　要：以标准发动机的动态燃速测试技术为研究对象,应用超声测厚原理获取固定声速点火条件下的发动机动态燃速、压强数据;分析提出一种基于特征点的动态燃烧信号辨识方法,获取发动机点火过程中推进剂退移厚度与时间变化数据;通过试验的方法建立常温状态不同压强下的声速校准模型,结合测试过程压强数据计算得到发动机点火过程中超声的实时声速,代入前期在固定声速条件下获取的推进剂退移厚度与时间数据中,通过求导获取点火过程中发动机的实时燃速。计算结果表明:基于超声的动态燃速测试方法能够实现整机的动态燃速测试,具有较高的时间分辨精度,其中基于超声的动态燃速测试燃烧时间与传统压强-时间曲线计算得到的燃烧时间误差为0.235%。此外,对比发动机点火后压强-时间与动态燃速-时间曲线发现,发动机建压完成后的动态燃速与压强曲线变化趋势呈一定相似性。Taking the dynamic burning rate technology of standard solid rocket motor(SRM)as the research object,the dynamic burning rate and pressure data of the SRM under the ignition condition of fixed ultrasonic velocity was tested by means of the ultrasonic thickness measurement principle,and through the analysis of these data,a new dynamic combustion signal identification method was proposed,the data of propellant regression thickness and time variation during the motor ignition were obtained.Finally,the ultrasonic velocity calibration model under different pressures at room temperature was established by experimental method,and the real-time ultrasonic velocity in the ignition process of the motor was calculated by combining the pressure data of the test process,which was substituted into the propellant regression thickness and time data obtained under the condition of fixed ultrasonic velocity,and the real-time burning rate of the motor during the ignition process was obtained by derivation.The results show that,the dynamic burning rate test method based on ultrasonic can realize the dynamic burning rate test of the whole motor and has high time resolution accuracy.The error of combustion time calculated by ultrasonic dynamic burning rate test and traditional pressure-time curve is 0.235%.In addition,by comparing the pressure-time and dynamic burning rate-time curves after ignition,it is found that the trend of dynamic burning rate and pressure curves after the motor pressure is similar.

关 键 词：超声测试技术 动态燃速 标准发动机 声速校准 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]