超声波测量大尺寸固体火箭发动机燃速的关键技术

doi:10.12382/bgxb.2021.0805

摘要/Abstract

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。

关键词: 超声波, 燃速, 固体火箭发动机

Abstract:

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.

Key words: ultrasonic, burning rate, solid rocket motor

孙得川, 贤光. 超声波测量大尺寸固体火箭发动机燃速的关键技术[J]. 兵工学报, 2023, 44(4): 1097-1106.

SUN Dechuan, XIAN Guang. Key Technology for Ultrasonic Measurement of Burning Rate in Large-scale Solid Rocket Motors[J]. Acta Armamentarii, 2023, 44(4): 1097-1106.

图/表 19

图1 超声波在发动机中的传播[9]

Fig.1 Propagation of ultrasonic waves in a solid rocket motor[9]

图2 测试推进剂燃速的模型发动机剖面图[12]

Fig.2 Cross-section of the combustion chamber with a sample holder[12]

图3 缩比无喷管发动机中的侵蚀燃烧[17]

Fig.3 Erosive burning in a subscale nozzleless rocket-motor[17]

图4 某推进剂中声速随温度的变化

Fig.4 Variation of sound speed with temperature in a propellant

图5 某固体燃料在不同压强条件下所对应的声速[18]

Fig.5 Sound speed of a solid fuel under different pressure conditions[18]

图6 固液发动机试验中超声波测定的退移速率[13]

Fig.6 The regression rate from ultrasonic measurement in a hybrid rocket motor test[13]

图7 ONERA的大尺寸发动机超声燃速测量[19]

Fig.7 Measured ultrasonic burning rate for ONERA’s large-size motor[19]

图8 装药燃面的回波图像[19]

Fig.8 Echo of the grain’s burning surface[19]

图9 传统方案和大厚度方案的比较[20]

Fig.9 Comparison between classical and high-thickness measurement approaches[20]

图10 推进剂的超声特性研究(1—强度,2—中心频率)[21]

Fig.10 Investigation of ultrasonic characteristics of the propellant (1-intensity, 2-central frequency)[21]

图11 测量系统示意图[21]

Fig.11 Block diagram of the measurement system[21]

图12 肉厚变化[21]

Fig.12 Time history of assumed web thicknesses[21]

图13 试件

Fig.13 Test piece

图14 不同频率超声波的药柱表面回波

Fig.14 Echo of the grain surface with different ultrasonic frequencies

图15 直径400mm钢壳体发动机试车的超声波测试数据

Fig.15 Ultrasonic test data of the 400mm-diameter engine with steel shell

图16 超声传播时间[19]

Fig.16 Ultrasonic propagation time[19]

图17 一种时均处理前后的回波[9]

Fig.17 An echo wave before and after time average processing[9]

图18 ODC效果[22]

Fig.18 ODC effects[22]

图19 测量的回波[16]

Fig.19 Measured return waveform[16]

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