IJMIE

Regression Rate Study of PVC/HTPB Hybrid Rocket Fuels

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Abstract

In the present study an effort is made to investigate the local regression rate, average regression rate through the effect of oxidizer injection pressure. For experimental investigation a lab scale ballistic test motor is designed and number of static test firing are carried out at different gaseous oxidizer injection pressure. The injection pressure is varied from 150psi to 420psi and a Swirl Injector and a conventional Shower Head Injector are used for the oxidizer injection from oxidizer chamber to fuel grain port. The local regression rate is obtained from the unburnt fuel web thickness after 10.5 second of test firing. Further, the investigation of regression rate of PVC and HTPB solid fuels are depended on mass flux of oxidizer as the regression rate shown a decreasing trend from head end to nozzle end. From the present analysis, it can be summarized that for PVC solid fuel regression rate is completely dependent on swirl injection of oxidizer, as well as the oxidizer injection pressure.

Recommended Citation

[1] Bartel, H. R, and Rannie, W. D., “Solid Fuel combustion as
Applied to Ramjets”, Progress Report 3-12, Jet Propulsion
Laboratory, California Institute of Technology, USA, 1946.
[2] Marxmann, G. A, Wooldridge, C.E., and Muzzy, R.J.,
“Fundamentals of Hybrid Boundary Layer Combustion”,
Progress in Aeronautics and Astronautics, Vol. 15, AIAA, New
York, 1964, pp. 485-522.
[3] Estey,P. N., Altman, D., and McFarlane, J. S., “An Evaluation
of Scaling Effects for Hybrid Rocket Motors,” AIAA Paper 91-
2517, June 1991.
[4] Smooth, C. T., and Price, C. P., “Regression Rate Mechanism
of Non -Metalized Hybrid Fuel System”, AIAA Journal, Vol. 3,
No. 8, 1965, pp. 1408-1413.
[5] Karabeyoglu, M. A., Cantwell, B. J. and Altman, D.,
“Development and Testing of Paraffin based hybrid Rocket
fuels,” AIAA paper 2001- 4503, 2001, pp. 632-638.
[6] Lee, C., Lee, J. W., and Byun, D. Y., “Transient Analysis of
Hybrid Rocket Combustion by the Zeldovich-Novozhilov
Method,” KSME International Journal, Vol. 17, No. 10, 2003, pp.
1572-1582.
[7] Houser, T. J., and Peck, M. V., “Research in Hybrid
Combustion”, Progress in Aeronautics and Astronautics, Vol. 15,
1964, pp. 559-581