Browse > Article
http://dx.doi.org/10.6108/KSPE.2016.20.6.054

Fuel Rich Gas O/F Ratio Characteristics of HDPE and Paraffin Fuel in Low Range of the Oxidizer Mass Flux  

Han, Seongjoo (Graduate School of Department of Aerospace & Mechanical Engineering, Korea Aerospace University)
Ryu, Sunghoon (Graduate School of Department of Aerospace & Mechanical Engineering, Korea Aerospace University)
Kim, Jinkon (School of Aerospace & Mechanical Engineering, Korea Aerospace University)
Kang, Teagon (School of Aerospace & Mechanical Engineering, Korea Aerospace University)
Moon, Heejang (School of Aerospace & Mechanical Engineering, Korea Aerospace University)
Kim, Junhyung (Agency for Defense Development)
Ko, Seung Won (Agency for Defense Development)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.20, no.6, 2016 , pp. 54-60 More about this Journal
Abstract
Multi-port HDPE and Paraffin firing tests are conducted for hybrid gas generator application of a ducted rocket in the low oxidizer mass flux range. A fuel rich gas of O/F ratio from 0.3 to 0.8, a typical O/F operating range of a ducted rocket gas generator, have been achieved with paraffin fuel implying that the hybrid system can be a potential candidate. It was also found that an almost constant O/F ratio regime exists under $35kg/m^2s$ of the oxidizer mass flux, opening a possibility for the paraffin fuel toward the VFDR gas generator application.
Keywords
Ducted Rocket; Paraffin; HDPE; Fuel Rich Gas; O/F ratio;
Citations & Related Records
Times Cited By KSCI : 1  (Citation Analysis)
연도 인용수 순위
1 Komornik, D. and Gany, A., "Investigation of a Ducted Rocket with a Hybrid Gas Generator," ISABE-1661, 2013.
2 Kim, G.H., "A Study on Combustion Characteristic of the Cylindrical Multi port grain for hybrid Rocket motor using PE/N2O," Korea Aerospace University Master thesis, 2010.
3 Kim, S.J. and Kwon, O., "Regression Characteristics of the Cylinderical Multiport Grain in Hybrid Rockets," Journal of Propulsion and Power, Vol 29, No.3, pp. 573-581, 2013.   DOI
4 Humble, R.W, Henry, G.N. and Larson, W.J., Space Propulsion Analysis and Design, McGraw-Hill Inc., Columbus, O.H., U.S.A., 1995.
5 Kim, S.J., "A Study on Combustion Characteristics of Hybrid rocket using Liquefying Solid fuel - Gaseous Oxygen," Korea Aerospace University Ph.D thesis, 2010.
6 Karabeyoglu, M.A., Altman, D. and Cantwell, B.J., "Combustion of Liquefying Hybrid Propellants: Part 1, General Theory," Journal of Propulsion and Power, Vol. 18, No. 3, pp. 610-620, 2002.   DOI
7 Ryu, S.H., Han, S.J., Kim, K.H., Kim, J.K., Moon H.J., Kim, J.H. and Ko, S.W., "Experimental Investigation of Gas NItrous Oxide/Paraffin Hybrid Gas Generator for Ducted Rocket", 8th Asian Joint Conference on Propulsion and Power, Takamatsu, Kagawa, Japan, AJCPP 2016-021, Mar. 2016.
8 Lee, D.E. and Lee, C.J., "Fuel-Rich Combustion Characteristic of a Combined Gas Generator," Journal of The Korean Society for Aeronautical and Space Sciences, Vol. 43, No. 7, pp. 593-600, 2015.   DOI
9 Cantwell, B., Karabeyoglu, A. and Altman, D., "Recent Advances in Hybrid Propulsion," International Journal of Energetic Materials and Chemical Propulsion, Vol. 9, No. 4, pp. 305-326, 2010.   DOI