한국추진공학회지 (Journal of the Korean Society of Propulsion Engineers)
- 제1권2호
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- Pages.58-66
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- 1997
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- 1226-6027(pISSN)
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- 2288-4548(eISSN)
$GO_2$ /HTPB를 사용하는 Hybrid Rocket의 추진제 침투율에 관한 실험적 연구
An Experimental Study on the Regression Rate of the Hybrid Rocket with $GO_2$ /HTPB Propellant Combination
- Kim, S.J. (Chungnam National University, Dept. of Mechanical Engineering) ;
- Han, J.S. (Chungnam National University, Dept. of Mechanical Engineering) ;
- Kim, Y. (Chungnam National University, Dept. of Mechanical Engineering) ;
- Ji, P.S. (Chungnam National University, Dept. of Mechanical Engineering) ;
- Cho, S. (Korea Aerospace Research Institute)
- 발행 : 1997.12.01
초록
본 연구에서는 HTPB를 연료로, 그리고 기체산소를 산화제로 사용하는 실험실용 hybrid rocket을 설계, 제작하여 지상연소실험을 수행함으로서, 산화제 유동율이 연료 grain침투율에 미치는 영향을 실험적으로 규명하였다. 실험 범위내에서 다음과 같은 결론을 얻었다.
To investigate the effect of the oxidizer mass flow rate on the fuel regression rate of the hybrid rocket, a laboratory size rocket was designed and ground fire test were carried out. Oxidizer was gaseous oxygen and HTPB was used as a fuel. Following correlation was obtained from the experiment.
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