Testing of Paraffin-based Hybrid Rocket Fuel using Gaseous Oxygen Oxidiser

Yash Pal; J. Baskar; S. Murugesan

doi:10.14429/dsj.62.2346

Yash Pal Hindustan University, Chennai
J. Baskar Hindustan University, Chennai
S. Murugesan Hindustan University, Chennai

DOI: https://doi.org/10.14429/dsj.62.2346

Keywords: Hybrid rocket, regression rate, injection pressure, helical grain, star grain

Abstract

A series of paraffin-based hybrid rocket fuel has been studied experimentally in a laboratory-scale motor. To enhance the regression rate of paraffin solid fuel, three types of grain configurations: Cylindrical, star, and helical grain configurations of paraffin wax have been developed and tested with gaseous oxygen. The helical fuel grain presented best performance among all the test ports. About 40.2 per cent and 20.6 per cent regression rates are increased by burning paraffin fuel with helical and star grain configuration respectively, as compared to cylindrical grain configuration at Gox=0.0191 g/mm2s. The regression rates were significantly influenced by the oxygen injection pressure varied between 344.7 kPa and 620.5 kPa. Furthermore, the experimentally obtained exponents of oxidizer mass flux for all three grain configurations have been found to be significantly different from those of the classical hybrid system. Finally, thrust-time traces for all three grain configurations were also studied. The result shown no significant increase or decrease in the amplitude of the thrust oscillations.

Defence Science Journal, 2012, 62(5), pp.277-283, DOI:http://dx.doi.org/10.14429/dsj.62.2346

Author Biographies

Yash Pal, Hindustan University, Chennai

Mr Yash Pal obtained his master degree in Aeronautical Engineering in 2011with a thesis on analysis of regression rate of PVC hybrid fuel in hybrid rocket combustion. Presently, he is working as Assistant Professor in Department of Aeronautical Engineering at Hindustan University. His area of research includes Hybrid rocket combustion.

J. Baskar, Hindustan University, Chennai

Mr Baskar. J is an undergraduate student at Department of Aeronautical Engineering at Hindustan University. His area of interest is in the field of hybrid rocket propulsion.

S. Murugesan, Hindustan University, Chennai

Mr S. Murugesan obtained his BE from University of Madras in 1970. Earlier he was working for Indian Space Research Organisation in the field of solid propulsion. Presently, he is working as Associate Professor at Department of Aeronautical Engineering at Hindustan University. His scientific activity is focused on solid rocket motor performance and high regression rate hybrid rocket fuels.

References

Karabeyoglu, M.A.; Cantwell, B.J. & Altman, D. Development and testing of paraffin-based hybrid rocket fuels. In the 37th AIAA/ASME/SAE/ASEE Joint propulsion Conference, Salt Lake City, Utah, 8-11 July, 2001. AIAA 2001-4503.

Carmicino, C. & Sorge, A.R. Role of injection in hybrid rockets regression rate behaviour. J. Propul. Power, 2005, 21(4), 606-12.

George, P.; Krishnan, S.; Varkey, P.M.; Ravindran, M. & Lalitha, R. Fuel regression rate in hydroxyl terminated polybutadiene/gaseous-oxygen hybrid rocket motors. J. Propul. Power, 2001, 17(1), 35-42.

Kim, S.; Lee, J.; Kim, G.; Cho, J.; Moon, H.; Sung, H.; Kim, J. & Park, S. Combustion characteristics of the cylindrical multi-port grain for hybrid rocket motor. In the 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2-5 August 2009, Denver, Colorado.

Shin, K.H.; Lee, C. & Yu, Y.H. The experiments for the enhancement of regression rate of hybrid rocket fuel. J. Mechanical Sci. Technol., 2005, 19(10), 1939-949.

Lee, C.J.; Lee, J.W.; Byun, B.W. & Lee, S.T. Effect of induced swirl flow on regression rate of hybrid rocket fuel by helical grain configuration. In the European Conference for Aerospace Sciences (EUCASS), 4-7 July, 2005, Moscow. pp. 68-76.

Santos, L.M.C.; Almeida, L.A.R.; Fraga, A.M. & Veras, C.A.G. Experimental investigation of a paraffinbased hybrid rocket. J. Engenharia Térmica (Thermal Engineering), 2006, 5(1), 08-12.

Smooth, C.T. & Price, C.P. Regression rate mechanism of non-metalized hybrid fuel system. AIAA Journal, 1965, 3(8), 1408-413.

Wilkinson, R.; Hart, K.; Day, R. & Coxhill, I. Proof-of-concept testing of a sustained vortex-flow configuration for hybrid rocket motors. In the 46thAIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 25-28 July 2010, Nashville, TN. AIAA 2010-6782.