International Journal of Aeronautical and Space Sciences

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
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Development of a University-Based Simplified H2O2/PE Hybrid Sounding Rocket at KAIST

  • Huh, Jeongmoo (Department of Aerospace Engineering, Korea Advanced Institute of Science and Technology) ;
  • Ahn, Byeonguk (Department of Aerospace Engineering, Korea Advanced Institute of Science and Technology) ;
  • Kim, Youngil (Department of Aerospace Engineering, Korea Advanced Institute of Science and Technology) ;
  • Song, Hyunki (Space Solutions Co., Ltd.) ;
  • Yoon, Hosung (Space Solutions Co., Ltd.) ;
  • Kwon, Sejin (Department of Aerospace Engineering, Korea Advanced Institute of Science and Technology)
  • Received : 2017.03.22
  • Accepted : 2017.09.14
  • Published : 2017.09.30
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Abstract

This paper reports development process of a university-based sounding rocket using simplified hybrid rocket propulsion system for low-altitude flight application. A hybrid propulsion system was tried to be designed with as few components as possible for more economical, simpler and safer propulsion system, which is essential for the small scale sounding rocket operation as a CanSat carrier. Using blow-down feeding system and catalytic ignition as combustion starter, 250 N class hybrid rocket system was composed of three components: a composite tank, valves, and a thruster. With a composite tank filled with both hydrogen peroxide($H_2O_2$) as an oxidizer and nitrogen gas($N_2$) as a pressurant, the feeding pressure was operated in blowdown mode during thruster operation. The $MnO_2/Al_2O_3$ catalyst was fabricated for propellant decomposition, and ground test of propulsion system showed the almost theoretical temperature of decomposed $H_2O_2$ at the catalyst reactor, indicating sufficient catalyst efficiency for propellant decomposition. Auto-ignition of the high density polyethylene(HDPE) fuel grain successfully occurred by the decomposed $H_2O_2$ product without additional installation of any ignition devices. Performance test result was well matched with numerical internal ballistics conducted prior to the experimental propulsion system ground test. A sounding rocket using the developed hybrid rocket was designed, fabricated, flight simulated and launch tested. Six degree-of-freedom trajectory estimation code was developed and the comparison result between expected and experimental trajectory validated the accuracy of the developed trajectory estimation code. The fabricated sounding rocket was successfully launched showing the effectiveness of the simplified hybrid rocket propulsion system.

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References

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