期刊文献+

超声波法测量燃速初探 被引量:6

Burning rate measurement by means of ultrasonic technique
在线阅读 下载PDF
导出
摘要 针对国内首次引进的超声波实时燃速测量系统编写了测试软件,用水作为被测试对象,进行了退移速率测量,分析了超声波测量燃速的主要影响因素。结果表明,测量精度主要受材料中声速的约束,声速会受到材料应力(压强)和温度的影响。该软件可以用于厚度、材料内声速和实时燃速测量。 Based on SFT4001H card, a burning rate measurement software was compiled. Water was chosen as the test object. Regression rate of the water surface was measured by the software. And the main factors that affect the regression rate measurement were analyzed. The results show that measuring accuracy is mainly restrained sound velocity in the material, moreover the sound velocity in the materials depends on stress of material ( pressure ) and temperature. The software can be used to measure thickness, sound velocity in the materials, and real-time regression rate.
出处 《固体火箭技术》 EI CAS CSCD 北大核心 2007年第4期362-364,共3页 Journal of Solid Rocket Technology
基金 国家自然科学基金(50406023)资助 高校博士点基金(20030699023)资助
关键词 超声波 燃速 实时测量 ultrasonic wave burning rate real-time measurement
  • 相关文献

参考文献2

  • 1Franck Cauty.The ultrasound waves:a measurement tool for energetic material characterization[R].AIAA 2004-4057.
  • 2SOFRATEST.SFT4001H PCI dynamically linked library for windows XP[M].Version 2.4.

同被引文献21

  • 1张劲民,王志强,袁华.超声波燃速测试技术在固体推进剂研制中的应用[J].火炸药学报,2006,29(3):9-12. 被引量:9
  • 2孙得川,杜新,汪亮.PE燃料热解过程对H_2O_2-PE固液发动机点火的影响[J].固体火箭技术,2006,29(5):346-349. 被引量:7
  • 3江英武,刘艳林.复合固体推进剂的薄层燃烧试验与热分析[J].含能材料,1996,4(1):24-32. 被引量:1
  • 4Greg Zilliac, Arif Karabeyoglu M. Hybrid rocket fuel regression rate data and modeling[ R]. AIAA 2006-4504.
  • 5Chiaverini Martin J, Harting George C, Yeu-cherng Lu, et al. Pyrolysis behavior of hybrid rocket solid fuels under rapid heating conditions [ R ]. AIAA 97-3078.
  • 6Antonis Antonioul, Akyuzlu Kazim M. A physics based comprehensive mathematical model to predict motor performanee in hybrid rocket propulsion systems [ R ]. AIAA 2005-3541.
  • 7Cauty F, Demarais J C. Ultrasonic Measurements of the Uncured Solid Propellants Burning Rate[C]// Proceedings of the 21th International Congress of ICT. Karlsruhe: ICT, 1990 : 110.
  • 8Frederick R J, Traineau J C, Marthe Popo. Review of Ultrasonic Technique for Steady State Burning Rate Measurements[J]. American Institute of Aeronautics and Astronautics, 2000 : 34.
  • 9Frank Cauty et al. Determination of Solid Propellant Burning Rate Sensitivity to the Initial Temperature by the Ultrasonic Method [J]. International Journal of Energetic Materials and Chemical Propulsion, 1994 (3) : 642.
  • 10Sinclair A N, Jastrzebski M, Safavi-Ardebili V. Ultrasonic Evaluation of Weak Liner/propellant Bonding in A Rocket Motor[C]. 6th World Conference on NDT, Montreal, Canada Aug 30-Sep 3,2004.

引证文献6

二级引证文献25

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部