Volume 31 Issue 12
Dec.  2016
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Article Navigation >  Journal of Aerospace Power  > 2016  >  31(12): 2996-3003
LI Bo, YU Xin-yu, XIE Kan, GUO Chang-chao, WEI Zhi-jun, WANG Ning-fei. Thrust vectoring features about fluidic throat for solid rocket motor[J]. Journal of Aerospace Power, 2016, 31(12): 2996-3003. doi: 10.13224/j.cnki.jasp.2016.12.023
Citation: LI Bo, YU Xin-yu, XIE Kan, GUO Chang-chao, WEI Zhi-jun, WANG Ning-fei. Thrust vectoring features about fluidic throat for solid rocket motor[J]. Journal of Aerospace Power, 2016, 31(12): 2996-3003. doi: 10.13224/j.cnki.jasp.2016.12.023
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Thrust vectoring features about fluidic throat for solid rocket motor

doi: 10.13224/j.cnki.jasp.2016.12.023

  • 1. School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China;

  • 2. Beijing Aerospace Propulsion Institute, China Aerospace Science and Technology Corporation, Beijing 100076, China

  • Received Date: 2015-03-19
  • Publish Date: 2016-12-28
    Abstract
  • A cold-flow experiment and numerical simulation research were performed on the fluidic throat using water as working fluid. The general rules of the fluidic throat for solid rocket motor were studied, including the injection styles choke performance, the thrust angle and the thrust performance of the fluidic throat under different conditions of secondary flow injection styles and secondary flow ratio. Numerical simulations were in good agreement with experimental results. Results show that, the choke performance is related to the point, angle and flow ratio of secondary injection. Meanwhile, the choke performance will be better with the increase of the flow ratio of the secondary flow and main flow. Secondary injection of the nozzle throat can effectively regulate the effective throat area which contributes to the thrust magnitude. When the flow ratio is 0.4, the maximum effective throat area ratio is 0.8. Secondary injection at the divergent section can regulate the thrust direction effectively. When the flow ratio is 0.4, the maximum thrust angle is 20°. The phase difference of the throat injection and divergent section injection is used for reducing the interference from throat and divergent segment.

     

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