Key Technology for Ultrasonic Measurement of Burning Rate in Large-scale Solid Rocket Motors

Dechuan SUN; Guang XIAN

doi:10.12382/bgxb.2021.0805

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Key Technology for Ultrasonic Measurement of Burning Rate in Large-scale Solid Rocket Motors

更新时间：2025-08-18

- Key Technology for Ultrasonic Measurement of Burning Rate in Large-scale Solid Rocket Motors
- Acta Armamentarii Vol. 44, Issue 4, Pages: 1097-1106(2023)
- 作者机构：
  
  1. 大连理工大学航空航天学院, 辽宁大连 116024
  2. 中国航天科工集团第六研究院41所, 内蒙古呼和浩特 010010
- 作者简介：
- 基金信息：
- DOI：10.12382/bgxb.2021.0805
  CLC：
- Received：26 November 2021，
  
  Published Online：25 July 2023，
  
  Published：28 April 2023
- 稿件说明：
移动端阅览
Dechuan SUN, Guang XIAN. Key Technology for Ultrasonic Measurement of Burning Rate in Large-scale Solid Rocket Motors[J]. Acta Armamentarii, 2023, 44(4): 1097-1106.
DOI：

Dechuan SUN, Guang XIAN. Key Technology for Ultrasonic Measurement of Burning Rate in Large-scale Solid Rocket Motors[J]. Acta Armamentarii, 2023, 44(4): 1097-1106. DOI： 10.12382/bgxb.2021.0805.

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。

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.

关键词

Keywords

references

刘宗魁 , 汪太琨 , 王鸿丽 , 等 . 固体火箭发动机装药动态燃速辨识方法 [J ] . 舰船科学技术 , 2020 , 42 ( 2 ): 181 - 184 .

LIU Z K , WANG T K , WANG H L , et al. Dynamic burning rate identification of solid rocket motor propellan [J ] . Ship Science and Technology , 2020 , 42 ( 2 ): 181 - 184 . (in Chinese)

周遵宁 , 潘功配 , 丁昆 , 等 . 烟火药性能试验方法第6部分:燃烧速度测定: GJB 5384.6—2005 [S ] . 北京 : 国防科学技术工业委员会 , 2005 .

ZHOU Z N , PAN G P , DING K , et al. Test methods of performance for pyrotechnic composition Part6 : Determination of burning rate-Target-line method: GJB 5384.6—2005 [S ] . Beijing : The Commission of Science, Technology and Industry for National Defense , 2005 . (in Chinese)

李兆忠 , 李葆萱 . 固体推进剂燃速密闭爆发器测试方法 [J ] . 固体火箭技术 , 1993 , 16 ( 1 ): 81 - 85 .

LI Z Z , LI B X . Solid propellant burning rate characteristics measurement in a closed bomb [J ] . Solid Rocket Technology , 1993 , 16 ( 1 ): 81 - 85 . (in Chinese)

刘华强 , 李葆萱 , 王瑜 . 密闭爆发器法固体推进剂燃速测试系统 [J ] . 固体火箭技术 , 2000 , 23 ( 3 ): 75 - 78 .

LIU H Q , LI B X , WANG Y . On burning rate measurement system of solid rocket propellant in a closed burner [J ] . Solid Rocket Technology , 2000 , 23 ( 3 ): 75 - 78 . (in Chinese)

裴庆 , 赵凤起 , 罗阳 , 等 . 固体推进剂燃速测试技术研究进展 [J ] . 火炸药学报 , 2015 , 38 ( 3 ): 9 - 14 , 21. DOI: 10.14077/j.issn.1007-7812.2015.03.002 http://doi.org/10.14077/j.issn.1007-7812.2015.03.002 通过2-氨基吡啶和2,4-二硝基氯苯的缩合和硝化反应,合成了题称化合物,并对缩合反应的机理作了说明。

PEI Q , ZHAO F Q , LUO Y , et al. Research progress in the burning rate measurement technology of solid propellant [J ] . Chinese Journal of Explosives & Propellants , 2015 , 38 ( 3 ): 9 - 14 , 21. (in Chinese)

王凯 , 贺晓芳 , 沈飞 , 等 . 超声波法测试固体火箭发动机燃速 [J ] . 中国测试 , 2017 , 43 ( 8 ): 19 - 23 .

WANG K , HE X F , SHEN F , et al. Burning rate measurement of solid rocket motor by ultrasonic technology [J ] . China Measurement & Test , 2017 , 43 ( 8 ): 19 - 23 . (in Chinese)

BALLEREAU S , FOUIN G , PAWLOWSKI M . Advancements in ultrasound measurement on large-scale solid rocket motors[C]//Proceedings of the 6th International Symposium on Special Topics in Chemical Propulsion:Advancements in Energetic Materials and Chemical Propulsion . Santiago, Chile: Begell House Inc. , 2005 : 476 - 492 .

郑晖 , 林树青 . 超声检测 [M ] . 第2版 . 北京 : 中国劳动社会保障出版社 , 2008 .

ZHENG H , LIN S Q . Ultrasonic testing [M ] . 2nd Edition . Beijing : China Labor and Social Security Press , 2008 . (in Chinese)

孙得川 , 权恩 , 曹梦成 . 超声波实时测量技术在固体火箭发动机中的应用 [J ] . 兵工学报 , 2016 ( 11 ): 1969 - 1975 . DOI: 10.3969/j.issn.1000-1093.2016.11.001 http://doi.org/10.3969/j.issn.1000-1093.2016.11.001 利用超声波对固体推进剂燃速进行实时测量是先进的燃速测量方法之一。针对超声波技术在固体火箭发动机试车中的应用，对典型固体火箭发动机材料进行测试研究，获得了发动机材料的超声波信号特征。将超声波探头直接安装在发动机壳体外侧部位，测量了固体推进剂在常压燃烧时的厚度变化。针对动态燃速测试，提出了超声波数据处理方法，对固体装药在常压燃烧下的回波进行处理，获得了装药的厚度变化过程和燃速，并分析了燃面附近温度分布对燃速测量的影响。结果表明：用超声波测量金属壳体固体发动机的燃速必须在壳体上开窗使超声波透过壳体和绝热层界面，而对复合材料壳体发动机可将超声波探头直接安装在壳体外侧;燃烧引起的装药表面温度变化对测量的影响可以忽略；该数据处理方法可以有效获得装药厚度变化。

SUN D C , QUAN E , CAO M C . Application of ultrasonic real-time measurement technology in solid rocket motor [J ] . Acta Armamentarii , 2016 ( 11 ): 1969 - 1975 . (in Chinese)

罗天佑 . 超声波测量固体推进剂燃速的应用研究 [D ] . 大连 : 大连理工大学 , 2020 .

LUO T Y . Research on the application of ultrasonic in the measurement of solid rocket motor burning rate [D ] . Dalian : Dalian University of Technology , 2020 . (in Chinese)

FREDERICK J R , TRAINEAU J C , POPO M . Review of ultrasonic technique for steady state burning rate measurements[C]//Proceedings of the 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit . Huntsville, AL, US:AIAA , 2000 .

KOHGA M , FREDERICK R A , MOSER M D . Ultrasonic properties of propellant ingredients[C]//Proceedings of the 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit . Indianapolis, IN, US:AIAA , 2002 .

SERIN N , CHIAVERINI M , HARTING G , et al. Pressure correction of ultrasonic regression rate measurements of a hybrid slab motor[C]//Proceedings of the 35th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit . Los Angeles, CA, US:AIAA , 1999 .

孙得川 , 万宏强 . 固体推进剂燃速的超声波测量 [J ] . 西安工业大学学报 , 2011 ( 1 ): 40 - 43 , 52.

SUN D C , WAN H Q . Ultrasonic technique for burning rate measurement of solid propellant [J ] . Journal of Xi’an Technological University , 2011 ( 1 ): 40 - 43 , 52. (in Chinese)

孙得川 , 张研 , 王贺 , 等 . 固液火箭发动机中燃料热解速率的测量与分析 [J ] . 推进技术 , 2010 ( 1 ): 74 - 77 .

SUN D C , ZHANG Y , WANG H , et al. Regression rate measurement and analysis for solid fuel in hybrid rocket motor [J ] . Propulsion Technology , 2010 ( 1 ): 74 - 77 . (in Chinese)

FURFARO J A . Erosive burning study utilizing ultrasonic measurement techniques[C]//Proceedings of the 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit . Huntsville, AL, US:AIAA , 2003 .

CAUTY F . The ultrasound waves: a measurement tool for energetic material characterization[C]//Proceedings of the 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit . Fort Lauderdale, FL, US:AIAA , 2004 .

孙得川 , 罗天佑 . 超声波法测燃速时压强修正系数的确定[C]//第二届中国空天推进技术论坛 . 西宁 : 中国工程院, 中国航天科技集团 , 2019 : 22 - 25 .

SUN D C , LUO T Y . Determination of pressure correction coefficient when measuring burning rate by ultrasonic method[C]//Proceedings of the second China Aerospace Propulsion Technology Forum . Xining : Chinese Academy of Engineering, China Aerospace Science and Technology Corporation, 2019 : 22 - 25 . (in Chinese)

LEFRER R . Ultrasonic measurement applied to ground tests of solid propellant rocket motor[C]//Proceedings of the 35th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit . Los Angeles, CA, US:AIAA 1999 .

COULOUMY J , COLEMARD F , DUCOS G . Great-depth ultrasound measurement on large-scale solid rocket motors [J ] . International Journal of Energetic Materials and Chemical Propulsion , 2009 , 8 ( 2 ): 133 - 145 . DOI: 10.1615/IntJEnergeticMaterialsChemProp.v8.i2 http://doi.org/10.1615/IntJEnergeticMaterialsChemProp.v8.i2 http://www.begellhouse.com/journals/17bbb47e377ce023,48beaa036f7be895.html http://www.begellhouse.com/journals/17bbb47e377ce023,48beaa036f7be895.html

KURABAYASHI H , SATO A , YAMASHITA K , et al. Ultrasonic measurements of burning rates in full-size rocket motors [J ] . Progress in Propulsion Physics , 2011 , 2 : 135 - 148 .

HASEGAWA K , HORI K . Novel burning rate measurement technique for solid propellant by means of ultrasonics [J ] . Combustion, Explosion, and Shock Waves , 2010 , 46 ( 2 ): 188 - 195 . DOI: 10.1007/s10573-010-0029-1 http://doi.org/10.1007/s10573-010-0029-1 http://link.springer.com/10.1007/s10573-010-0029-1 http://link.springer.com/10.1007/s10573-010-0029-1

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