International Journal of Aeronautical and Space Sciences

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
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Development and Verification Test of a Bi-propellant Thruster Using Hydrogen Peroxide and Kerosene

  • Yu, I Sang (Department of Aerospace Engineering, Chungnam National University) ;
  • Kim, Tae Woan (Department of Aerospace Engineering, Chungnam National University) ;
  • Ko, Young Sung (Department of Aerospace Engineering, Chungnam National University) ;
  • Jeon, Jun Su (Engine Test and Evaluation Team, Korea Aerospace Research Institute) ;
  • Kim, Sun Jin (Department of Fire Safety Engineering, Chungnam State University)
  • Received : 2016.04.05
  • Accepted : 2017.06.08
  • Published : 2017.06.30
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Abstract

This paper describes development procedure and verification test results of a bi-propellant thruster using hydrogen peroxide and kerosene. The design thrust of the thruster is about 500 N and six swirl type coaxial injectors were used. The passage type manifolds were employed for the injector head to reduce the response time. The passage was designed to minimize stagnation points and recirculation region to ensure uniform flow distribution and sufficient cooling performance through flow analysis using Fluent. A catalytic igniter using hydrogen peroxide was installed at the center of the injector head. The propellant feeding and spray characteristics were confirmed by hydraulic tests. Combustion tests were performed on design and off-design points to analyze combustion characteristics under various mixture ratio conditions. The combustion test results show that combustion efficiency was over 95 % and chamber pressure fluctuation were less than 1.5 % under all test conditions.

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References

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