Experimental Study of Fuel Regression Rate in a HTPB/N2O Hybrid Rocket Motor

Document Type : Article

Authors

1 Senior Researcher, Space Transportation Research Institute, Iranian Space Research Center, Tehran, Iran

2 Department of Aerospace Engineering, Sharif University of Technology, Azadi Street, Tehran, Iran

Abstract

The performance of a HTPB/N2O hybrid motor was experimentally investigated. A hybrid motor was designed and manufactured in a laboratory with the purpose of studying the effects of various parameters on the motor’s performance, including fuel regression rate and specific impulse. A series of tests were conducted to find a correlation between the fuel regression rate and the oxidizer’s mass flux. The effects of chamber’s pressure on the regression rate as well as other performance parameters were investigated. While the burning rate did not change dramatically, both the efficiency and ISP of the motor were increased. The local fuel regression rate and the fuel port were also calculated. In addition, instantaneous regression rate was calculated using a special technique.

Keywords

Main Subjects


References
1. Rezaei, H. and Soltani, M.R. An analytical and experimental study of a hybrid rocket motor", Proc IMechE Part G: J Aerospace Engineering, 228(13), pp.
2475-2486 (2014). 2. Doran, E., Dyer, J., Dunn, Z., et al. Nitrous oxide hybrid rocket motor fuel regression rate characterization",
AIAA Paper, pp. 2007-5352 (2007).
3. Connel, T.L., Santi, S.A., Risha, G.A. et al. Experiment and semi-empirical modeling of lab-scale hybrid rocket performance", AIAA Paper, pp. 2009-
5086 (2009). 4. http://www.scaled.com/projects/tierone/ 5. Cavalleri, R.J. and Loehr, R.D. Hybrid rocket propulsion
performance prediction", AIAA Paper, pp. 2005- 3548 (2005).
6. Zilliac, G. and Karabeyoglu, M.A. Hybrid rocket fuel regression rate data and modeling", AIAA Paper, pp.
2006-4504 (2006).
7. Yen-Sen, C., Lian, Y.Y., Yang, L. and Wu, B. Combustion
modeling and analysis of hybrid rocket motor
internal ballistics", AIAA Paper, pp. 2012-3749 (2012).
8. Kim, J., Kim, S., Kim, J. and Moon, H. Experimental
investigations of the tapered fuel regression rate of
a hybrid rocket motor", AIAA Paper, pp. 2010-7119
(2010).
9. Risha, G.A., Evans, B.J., Boyer, E., Wehrman, R.B.
and Kuo, K.K. Nano-sized aluminum and boronbased
solid fuel characterization in a hybrid rocket
engine", AIAA Paper, pp. 2003-4593 (2003).
10. Aoki, A. and Fukuchi, A. Development of low cost
fuels for hybrid rocket engine", AIAA Paper, pp. 2010-
6638 (2010).
11. Estey, P., Altman, D. and Mc Farlane, J. An evaluation
of scaling e ects for hybrid rocket motors", AIAA-
91-2517 (1991).
12. Karabeyoglu, A., Zilliac, G., Cantwell, B.J., DeZilwa,
S. and Castellucci, P. Scale-up tests of high regression
rate paran-based hybrid rocket fuels", Journal of
Propulsion and Power, 20(6), pp. 1037-1045 (2004).
13. George, P., Krishnan, S., Varkey, P.M., Ravindran,
M. and Ramachandran, L. Fuel regression
rate in hydroxyl-terminated-poly butadiene/gaseousoxygen
hybrid rocket motors", Journal of Propulsion
and Power, 17(1) (2001).
14. Gomes, S.R., Rocco Junior, L., Rocco, J.A.F.F. and
Iha, K. Gaseous oxygen injection e ects in hybrid
labscale rocket motor operations", AIAA Paper, pp.
2010-6545 (2010).
15. Potapkin, A.V. and Lee, T.S. Experimental study
of thrust performance of a hybrid rocket motor with
various methods of oxidizer injection", Combustion,
Explosion, and Shock Waves, 40(4), pp. 386-392
(2004).
16. Peretz, A., Einav, O., Hashmonay, B., Birnholz, A. and
Sobe, Z. Development of a laboratory-scale system for
hybrid rocket motor testing", Journal of Propulsion
and Power, 27(1), pp. 190-196 (2011).
17. Lohner, K., Dyer, J., Doran, E., Dunn, Z. and Zilliac,
G. Fuel regression rate characterization using a laboratory
scale nitrous oxide hybrid propulsion system",
AIAA Paper, pp. 2006-4671 (2006).
18. Shan, F., Hou, L. and Piao, Y. Combustion performance
and scale e ect from N2O/HTPB hybrid
rocket motor simulations", Acta Astronautica Journal,
2013(85), pp. 1-11 (2013).
19. Swami, R.D. and Gany, A. Analysis and testing of
similarity and scale e ects in hybrid rocket motors",
Acta Astronautica, 2003(52), pp. 619-628 (2003).
20. Beckwith, T.G., Maraugoni, R.D. and Lienhard,
V.J.H., Mechanical Measurements, 5th Ed. Cambridge,
MA: Addison-Wesley Publishing Company (1993).
21. Sutton, G.P. and Biblarz, O., Rocket Propulsion Elements,
7th Ed, John Wiley & Sons (2001).
22. Carmicino, C. and Sorge, A.R. In
uence of a conical
axial injector on hybrid rocket performance", Journal
of Propulsion and Power, 22(5), pp. 984-995 (2006).
23. Farbar, E., Louwers, J. and Kaya, T. Investigation of
metalized and non metalized hydroxyl terminated poly
butadiene/hydrogen peroxide hybrid rockets", Journal
of Propulsion and Power, 23(2), pp. 476-486 (2007).
24. Frederick, R.A. and Whitehead, J.J. Predicting hybrid
propellant regression rate using response surfaces",
Journal of Propulsion and Power, 25(3), pp.
815-818 (2009).
25. Patnala, S., Chattaraj, T. and Joshi, P.C. Combustion
studies on paran wax in gaseous oxygen and
nitrous oxide", ARPN Journal of Engineering and
Applied Sciences, 7(7), pp. 806-811 (2012).
H. Rezaei et al./Scientia Iranica, Transactions B: Mechanical Engineering 25 (2018) 253{265 265