Browse > Article

Performance Analysis of PE-GOX Hybrid Rocket Motor Part I : Regression Rate Characteristics  

Youn, Chang-Jin (한국항공대학교 항공우주 및 기계공학과)
Song, Na-Young (한국항공대학교 항공우주 및 기계공학과)
Yoo, Woo-Jun (한국항공대학교 항공우주 및 기계공학과)
Jeon, Chang-Soo (한국항공대학교 항공우주 및 기계공학부)
Kim, Jin-Kon (한국항공대학교 항공우주 및 기계공학부)
Sung, Hong-Gae (한국항공대학교 항공우주 및 기계공학부)
Moon, Hee-Jang (한국항공대학교 항공우주 및 기계공학부)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.11, no.2, 2007 , pp. 71-78 More about this Journal
Abstract
An experimental investigation was conducted to clarify the combustion characteristics of Polyethylene-GOX(PE-GOX) hybrid motor using a single-port fuel grain configuration. Data from the experiments were analyzed to evaluate the length-averaged regression rate of PE-GOX propellants. Based on the existing theories, the empirical regression rate formulas provided from Marxman[3,4] and Altman[14] showed good concordance with the PE-GOX experiments. The accuracy of the regression rate was then evaluated and compared with the measured one. As a result, Marxman's model was somewhat more precise than Altman's model in these experiments. Moreover, the consideration of the empirical regression rate showed that O/F ratio has minor variation due to the quasi constant inflow of the fuel during motor firing.
Keywords
Hybrid Rocket; Regression Rate; PE-GOX propellants; Combustion Characteristics; Performance Prediction;
Citations & Related Records
Times Cited By KSCI : 2  (Citation Analysis)
연도 인용수 순위
1 Marxman, G. A. and Gilbert, M., "Turbulent Boundary Layer Combustion in the Hybrid Rocket",Academic Press Inc., 1963, pp. 371-383
2 Chiaverini, M. J., Kuo, K. K., Peretz, A. and Harting, G. C., "Regression-Rate and Heat-Transfer Correlations for Hybrid Rocket Combustion." Journal of propulsion and power, Vol. 17, No. 1, 2001, pp. 99-110   DOI   ScienceOn
3 김수종, 김진곤, 이승철, 유우준, 이정표, "하이브리드 로켓의 L/D 비 변화에 따른 연소특성 연구", 한국추진공학회지, 제 9권, 제 4호, 2005, pp. 31-38
4 우준, 김진곤, 이정표, 김수종, 이승철, 국태승, "Single Port 하이브리드 추진 시스템의 연료에 따른 연소특성 연구", 한국추진공학회 추계학술대회, 2005, pp. 368-372
5 이정표, 김수종, 이승철, 김진곤, "Single Port 하이브리드 로켓에서의 고체연료 질량유속을 고려한 연소특성 연구", 한국추진공학회 춘계학술대회, 2006, pp. 246-250
6 황영춘, 이창진, "스월 유동과 나선형 그레인에 의한 하이브리드 로켓 연료의 연소율 향상", 한국항공우주학회지, 제 34권, 제 4호, 2006, pp. 63-69
7 Lengelle, G., Fourest, B., Godon, J. C. and Guin, C., "Condensed-phase behavior and ablation rate of fuels for hybrid propulsion." AIAA Paper 93-2413, 1993
8 Smoot, L. D. and Price, C. F., "Regression Rates of Metalized Hybrid Fuel Systems." AIAA Journal, Vol. 4, 1965
9 Glassman, I., Combustion, Academic Press, 1996
10 Marxman, G. A., Muzzy, R. and Wooldridge, C., "Fundamentals of hybrid boundary-layer combustion.", Academic Press, 1964, pp. 485-521
11 Peck, M. V. and Houser, T. J., "Research in Hybrid Combustion", Heterogeneous Combustion, 1963, pp. 559-581
12 Humble, R. W., "Spece Propulsion Analysis and Design", McGrawHill, 1995
13 Smoot, L. D. and Price, C. F., "Regression Rates of Nonmetalized Hybrid Fuel Systems." AIAA Journal, Vol. 3, No. 8, 1965   DOI
14 Carmicino, C. and Sorge, A. R., "Role of Injection in Hybrid Rockets Regression Rate Behavior." Journal of propulsion and power, Vol. 21, No. 4, 2005, pp. 606-612   DOI   ScienceOn