Plume velocity characteristics of pintle controlled solid rocket motor based on TDLAS technique

被引：0
|
作者：
Wang R. [1 ]
Song A. [2 ]
Wang L. [3 ,4 ]
Wang D. [1 ]
Li J. [1 ]
Wang N. [1 ]
机构：
[1] School of Aerospace Engineering, Beijing Institute of Technology, Beijing
[2] Beijing System Design Institute of Electro Mechanic Engineering, Beijing
[3] College of Aerospace Engineering, National University of Defense Technology, Changsha
[4] The 41st Institute of the Sixth Academy of China Aerospace Science & Industry Corp, Huhhot
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2023年 / 44卷 / 17期
基金：
中国国家自然科学基金;
关键词：
afterburning reaction; dynamic regulation; pintle controlled solid rocket motor; plume velocity; tunable diode laser absorption spectroscopy (TDLAS);
D O I：
10.7527/S1000-6893.2022.28107
中图分类号：
学科分类号：
摘要：
To investigate the plume velocity characteristics，a numerical simulation model of plume of the pintle controlled solid rocket motor considering afterburning reaction is established，using the finite-rate reaction model and dynamic mesh. The model is combined with Tunable Diode Laser Absorption Spectroscopy（TDLAS）technology to calculate the plume velocity. The transient flow field during the pintle motion is analyzed，and the effects of after-burning reactions and measurement position on velocity measurement investigated. The results show that the transient plume field changes periodically with the reciprocal motion of the pintle. When the pintle tends to close the nozzle，a strong shock wave appears near the nozzle. The downstream plume velocity distribution is more uniform，indicating the reduced influence of the velocity gradient on TDLAS measurement；the afterburning reaction leads to significant changes in the downstream velocity and H2O component distribution of the plume. Along the downstream direction，the influence of afterburning on the oscillation amplitude of the velocity along the TDLAS optical path gradually increases. In practice，to reduce the influence of afterburning and the velocity gradient，the measuring position should be closer to the nozzle to obtain measurement closer to the axis velocity. © 2023 AAAS Press of Chinese Society of Aeronautics and Astronautics. All rights reserved.
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共 28 条
  • [1] ZHANG S, HU B, MENG Y T., Application and de⁃ velopment of controllable solid rocket motor[J], Journal of Solid Rocket Technology, 25, 4, pp. 12-15, (2002)
  • [2] KO H, LEE J., Cold tests and the dynamic characteristics of the pintle type solid rocket motor, (2013)
  • [3] WANG Y L，, HE G Q, LI J, Et al., Experiment on non-coaxial variable thrust pintle solid motor[J], Journal of Solid Rocket Technology, 31, 1, pp. 43-46, (2008)
  • [4] WEI X G，, HE G Q，, LI J，, Et al., Analysis on response of pressure in non-coaxial variable thrust pintle motor[J], Journal of Solid Rocket Technology, 32, 4, pp. 409-412, (2009)
  • [5] WANG J X, WEI Z J, WANG N F., High burning tem⁃ perature experiment on pintle controlled solid motor[J], Journal of Propulsion Technology, 33, 1, pp. 89-92, (2012)
  • [6] SONG A C, WANG N F, LI J W，, Et al., Transient flow characteristics and performance of a solid rocket motor with a pintle valve[J], Chinese Journal of Aeronautics, 33, 12, pp. 3189-3205, (2020)
  • [7] WANG P Y, WANG Z T, WU Z P，, Et al., Optimization design for contour of pintle nozzle for variable thrust solid rocket motor under multiple working conditions[J], Jour⁃ nal of Solid Rocket Technology, 45, 3, pp. 337-342, (2022)
  • [8] MA B Y, LI J W, WANG X Q, Et al., Simulation on dy⁃ namic response characteristics of pintle variable thrust solid rocket motor[J], Journal of Propulsion Technol⁃ ogy, 41, 10, pp. 2161-2172, (2020)
  • [9] YANG Y J, ZHAO F Q，, SUN M，, Et al., Investigations on the exhaust plume velocity characteristics of double-base and CMDB propellants charge based on TDLAS technique[J], Chinese Journal of Explosives & Propel⁃ lants, 39, 3, pp. 70-74, (2016)
  • [10] LI M, SUN M, ZHAO F Q, Et al., Numerical calcula⁃ tion of the exhaust plume characteristic parameters of three typical solid propellants[J], Chinese Journal of Ex⁃ plosives & Propellants, 41, 1, pp. 86-92, (2018)
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