Application of ultrasonic real-time measurement technology in solid rocket motor

被引：0
|
作者：
Sun D.-C. [1 ]
Quan E. [2 ]
Cao M.-C. [1 ]
机构：
[1] State Key Laboratory of Structural Analysis for Industrial Equipment, School of Aeronautics and Astronautics, Dalian University of Technology, Dalian, 116024, Liaoning
[2] The Institute of Xi'an Aerospace Solid Propulsion Technology, Xi'an, 710025, Shaanxi
来源：
Binggong Xuebao/Acta Armamentarii | 2016年 / 37卷 / 11期
关键词：
Burning rate; Data processing; Ordnance science and technology; Solid rocket motor; Temperature; Ultrasonic;
D O I：
10.3969/j.issn.1000-1093.2016.11.001
中图分类号：
学科分类号：
摘要：
Ultrasonic measurement of burning rate is an advanced technique. For application of ultrasonic measurement in solid rocket motor test, some typical materials used in solid rocket motor (SRM) are measured by ultrasonic technique, and their ultrasonic signal signatures were obtained. The real-time thickness variation of solid propellant at ordinary pressure is measured by an ultrasonic transducer mounted on the outside of the motor shell. A data processing method is proposed to manipulate the echo wave for real-time measurement of burning rate. The proposed method was successfully used in a hot fire test in which the propellant burns at ordinary pressure. The variation in thickness of propellant and its burning rate at ordinary pressure was obtained. The influence of temperature distribution near burning surface on burning rate test is analyzed. The results show that for motor with metal shell, a window must be made on the metal shell to let enough ultrasonic wave energy penetrate the interface between shell and isolator, and for composite shell motor the probe can be mounted outside the shell directly. The influence of temperature variation near burning face caused by combustion on measurement is negligible. The proposed data processing method can be used effectively to obtain the variation of grain thickness. © 2016, Editorial Board of Acta Armamentarii. All right reserved.
引用
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页码：1969 / 1975
页数：6
相关论文
共 14 条
  • [1] Cauty F., Demarais J.C., Ultrasonic measurements of the uncured solid propellants burning rate, Proceedings of the 21th International Congress of ICT, pp. 110-114, (1990)
  • [2] Frederick R.J., Traineau J.C., Popo M., Review of ultrasonic technique for steady state burning rate measurements, 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, (2000)
  • [3] Demarais J.C.I., Cauty F., Erades C., Determination of solid propellant burning rate sensitivity to the initial temperature by the ultrasonic method, International Journal of Energetic Materials and Chemical Propulsion, 3, 1-6, pp. 642-653, (1994)
  • [4] Murphy J.J., Krier H., Ultrasound measurements of solid propellant burning rates: theory and application, AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, (1998)
  • [5] Sinclair A.N., Jastrzebski M., Safavi-Ardebili V., Ultrasonic evaluation of weak liner/propellant bonding in a rocket motor, 16th World Conference on NDT, (2004)
  • [6] McLean C.H., Deininger W.D., Marotta B.M., Et al., Green propellant infusion mission program overview, status, and flight operations, 51st AIAA/SAE/ASEE Joint Propulsion Conference, (2015)
  • [7] Redden J.J., SLS booster development, 51st AIAA/SAE/ASEE Joint Propulsion Conference, (2015)
  • [8] Anthoine J., Jezequel P., Prevost M., Et al., Variable fuel grains Burn velocities to reduce solid-rocket-motor pressure oscillations, Journal of Propulsion and Power, 31, 1, pp. 342-351, (2015)
  • [9] Jones D.A., Mascaro M.D., Lineberry D.M., Et al., An advanced digital cross correlation method for solid propellant burning rate determination, 51st AIAA/SAE/ASEE Joint Propulsion Conference, (2015)
  • [10] Zhang J.-M., Wang Z.-Q., Yuan H., Application of ultrasonic measurement for burning rate in solid propellant development, Chinese Journal of Explosives and Propellants, 29, 3, pp. 9-12, (2006)
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