International Scientific Journal


In rocketry application, now-a-days instead of monopropellants slowly composite propellants are introduced. Burning rate of a solid state composite propellant depends on many factors like oxidizer-binder ratio, oxidizer particle size and distribution, particle size and its distribution, pressure, temperature, etc. Several researchers had taken the mass varied composite propellant. In that, the ammonium perchlorate mainly varied from 85 to 90%. This paper deals with the oxidizer rich propellant by allowing small variation of fuel cum binder ranging from 2%, 4%, 6%, and 8% by mass. Since the percent of the binder is very less compared to the oxidizer, the mixture remains in a powder form. The powder samples are used to make a pressed pellet. Experiments were conducted in closed window bomb set-up at pressures of 2, 3.5, and 7 MN/m2. The burning rates are calculated from the combustion photography (images) taken by a high-speed camera. These images were processed frame by frame in MATLAB, detecting the edges in the images of the frames. The burning rate is obtained as the slope of the linear fit from MATLAB and observed that the burn rate increases with the mass variation of constituents present in solid state composite propellant. The result indicates a remarkable increase in burn rate of 26.66%, 20%, 16.66%, and 3.33% for Mix 1, 2, 3, 4 compared with Mix 5 at 7 MN/m2. The percentage variations in burn rate between Mix 1 and Mix 5 at 2, 3.5, and 7 MN/m2 are 25.833%, 32.322%, and 26.185%, respectively.
PAPER REVISED: 2016-08-19
PAPER ACCEPTED: 2016-08-25
CITATION EXPORT: view in browser or download as text file
THERMAL SCIENCE YEAR 2016, VOLUME 20, ISSUE Supplement 4, PAGES [S1119 - S1125]
  1. ***, Course Notes on Propellants and Explosive Technology, Indian Institute of Technology, Madras, Chennai, India, 1998
  2. Price, E. W., et al., The Details of Combustion of Ammonium Perchlorate Propellants: Leading Edge Flame Detachment, Combustion Science and Technology, 138 (1998), 1-6, pp. 63-83
  3. Hightower, J. D., Price, E. W., Combustion of Ammonium Perchlorate, 11th International Symposium on Combustion, Berkeley, Cal., USA, 1966, Proceedings, The Combustion Institute, Pittsburgh, Penn., USA, 1967, pp. 463-472
  4. Kishore, K., Sunitha,M. R., Effect of Oxidizer Particle Size on Burning Rate and Thermal Decomposition of Composite Solid Propellants, Defence Science Journal, 32 (1982), 3, pp. 251-257
  5. Bastress, E. K., Modification of Burning Rates of Ammonium Perchlorate Solid Propellants by Particle Size Control, Ph. D. thesis, Princeton University, Princeton, N. J., USA, 1961
  6. Chakravarthy, S. R., et al., Binder Melt Flow Effects in the Combustion of AP-HC Composite Solid Propellants, AIAA paper 95-2710, 1995
  7. Banerjee, S., Chakravarthy, S. R., Ammonium Perchlorate-Based Composite Solid Propellant Formulations with Plateau Burning Rate Trends, Combustion Explosion and Shock Waves, 43 (2007), 4, pp. 435-441
  8. Chakravarthy, S. R., et al., Mechanism of Burning Rate Enhancement of Composite Solid Propellants by Ferric Oxide, Journal of Propulsion and Power, 13 (1997), 4, pp. 471-480
  9. Jayaraman, K., et al., Production Characterization, and Combustion of Nano-Aluminium and its Effects in Solid Propellant Combustion, Ph. D. thesis, Indian Institute of Technology, Madras, Chennai, India, 2008
  10. ***, MATLAB software
  11. Chakravarthy, S. R., et al., Plateau Burning Behavior of Ammonium Perchlorate Sandwiches and Propellants at Elevated Pressures, Journal of Propulsion and Power, 19 (2003), 1, pp. 56-65
  12. Price, E. W., et al., Pressure Dependence of Burning Rate of Ammonium Perchlorate-Hydrocarbon Binder Solid Propellants, AIAA paper 97-3106, 1997
  13. Summerfield, M., et al., Burning Mechanism of Ammonium Perchlorate Propellants, Solid Propellant Rocket Research, ARS Progress in Astronautics and Rocketry, Academic Press, New York, USA, 1960, 1, pp. 141-182
  14. Atwood, A. I., et al., Burning Rate of Solid Propellant Ingredients, Part 1: Pressure and Initial Temperature Effects, Journal of Propulsion and Power, 15 (1999), 6, pp. 740-747

© 2024 Society of Thermal Engineers of Serbia. Published by the Vinča Institute of Nuclear Sciences, National Institute of the Republic of Serbia, Belgrade, Serbia. This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution-NonCommercial-NoDerivs 4.0 International licence