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Preliminary Study of a Turbopump Pyro Starter  

Hong, Moon-Geun (한국항공우주연구원 발사체미래기술연구실)
Lee, Soo-Yong (한국항공우주연구원 발사체미래기술연구실)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.12, no.2, 2008 , pp. 74-80 More about this Journal
Abstract
The feasibility study into the development of turbine spinners, which start up the turbo-pump, has been carried out and the design requirements and parameters ranges have been presented. Turbine spinners use the solid propellant as such composite propellant based AN compound with high energy plasticizers, coolants, and phase stabilizer which relieves a sensible volume change due to the phase transformation of AN near room temperature. Propellants which have a homing rate of $0.2{\sim}0.3\;mm/s$ and pressure exponent ranged from 0.3 to 0.6, showed stable burn-out in the standard motor tests. Both the magnitude of ignition energy and its thermal transfer mechanism have been proved to have a tangible effect on the ignition of the pyre starter, and the results of this study showed that a flame temperature of 1400K would be quite adequate to get a stable ignition for the AN composite propellant.
Keywords
Pyro Starter; Turbine Spinner; AN; Composite Propellant;
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  • Reference
1 Huzel, D. K. and Huang, D. H., Modern Engineering for Design of Liquid-Propellant Rocket Engines, AIAA, 1992
2 한국항공우주연구소, 과학로켓트 추진기관 개발연구(III), 과학기술처, 1993
3 Davenas, A., Solid Rocket Propulsion Technology, Pergamon Press Ltd., 1993
4 홍문근, 점화기 및 터보펌프 시동기 관련 기술협의, KARI-TICS-OD-2003-231, 2003
5 홍문근 한상엽, KSLV 터보펌프 시동기 개발현황 및 향후계획, KARI-PCG-TM-2005, 2005
6 Junli-li, and E., and Yalong-xu, "Some recent investigation in solid propellant technology for gas generator," AIAA 90-2335, 1990
7 Hensel, C., Mattstedt, T. B., Oechslein, W., Vermeulen, E., and de Wilde, M., "Ignition system concept for new cryogenic upper stage engine of Ariane 5," AIAA 99-2474, 1999
8 棚次 亙弘, 成尾 芳博, 秋葉鐐二郞 倉谷 健治, "液水/液酸 Engine Turbine Spinner 開發" 宇宙科學硏究所 特輯 第6号, 1983, pp.145-154
9 한국항공우주연구원, 소형위성발사체(KSLV-I) 개발사업(1), 과학기술부, 2003
10 한국항공우주연구소, 로켓 화학추진제 특성연구, 과학기술처, 1995
11 한국항공우주연구원, 소형위성발사체(KSLV-I) 개발사업(5), 과학기술부, 2006
12 김정수, 황준식, "HTPB/AN 복합 고체추진제의 조성연구," 한국항공우주학회 춘계학술발표 논문집, 1994
13 Oommen, C., and Jain, S. R., "Ammonium nitrate: a promising rocket propellant oxidizer," Journal of Hazardous Materials A67, 1992, pp.253-281