Fuel and Combustion

Fuel and Combustion

Investigation of the Effect of Iron Oxide on the Burning Rate Temperature Sensitivity of Solid Composite Propellants

Authors
Navab Fathi
Mohammad Ali Dehnavi
Faculty of Engineering, Imam Hossein University, Tehran, Iran
Abstract
The temperature sensitivity of solid propellant burning rate directly affects the accuracy and performance of the rocket motor. In this study, the effect of additives such as iron oxide (IO) on burning rate temperature sensitivity of solid composite propellants based on HTPB was investigated by burning rate, DTA, density and auto ignition temperature experiments. Also the effect of various coarse to fine ratios of oxidizer ammonium per chlorate on temperature sensitivity was studied. The experimental results showed that the burning rates of these propellants were increased by addition of iron oxide or decreasing coarse to fine ratios of ammonium per chlorate particles. DTA results indicated that decomposition temperatures of AP were decreased by addition of iron oxide. Also the auto ignition temperatures of AP with iron oxide were decreased according to the results of auto ignition temperature test. The results also showed that the burning rate temperature sensitivity of AP/HTPB based propellants was reduced by addition of IO or decreasing coarse to fine ratios of ammonium per chlorate particles. The enhancement of burning surface temperature of AP/HTPB/IO and AP/HTPB with low coarse to fine ratios is responsible for the reduced temperature sensitivity. Very small values of the temperature sensitivity are seen when fine AP particles and IO are mixed together.
Keywords
Composite propellants
Burning rate
Temperature sensitivity
Auto ignition temperature
DTA
1.        P. Thakre and V. Yang, “Solid Propellants,” Encyclopedia of Aerospace Engineering, 1, 2010, pp. 1-10.
2.        M. T. Gaunce and J. R. Osborn, “Temperature Sensitivity Coefficients of Solid Propellant Burning Rate,” Acta Astronautica, 13, 1986, pp. 127-130.
3.        T. T. Nguyen, “Burn Rate Temperature Sensitivity of Solid Rocket Propellants: an Overview of Current Status of Experimental Results,” 22nd Int. Annual Conference of ICT, Karlsruhe, Germany, 1991, pp. 41/1-18.
4.        K. Kishore and K. Sridhara, “Effect of Temperature on the Burning Rate of Solid Propellants: A Review,” J. Propulsion, 2, 1986, pp. 193-194.
5.        J. P. Agrawal, High Energy Materials Propellants, Explosives and Pyrotechnics, WILEY-VCH Verlag GmbH & Co. KGaA, Weinheim, 2010.
6.        V. V. Kulkarni, A. R. Kulkarni, P. A. Phawade and J. P. Agrawal, “A Study on the Effect of Additives on Temperature Sensitivity in Composite Propellants,” Propellants Explos. Pyrotech., 26, 2001, pp. 125-129.
7.        Y. L. Sun, S. F. Li and D. H. Ding, “Effect of Ammonium Oxalate/Strontium Carbonate on the Burning Rate Characteristics of Composite Propellants,” Journal of Thermal Analysis and Calorimetry, 86, 2006, pp. 497-503.
8.        R. E. Hamke, M. T. Gaunce and J. R. Osborn, “The Effect of Pressure Exponent on Temperature Sensitivity,” Acta Astronautica, 15, 1987, pp. 377-382.
9.        N. Kubota and H. Okuhara, “Burning Rate Temperature Sensitivity of HMX Propellants,” J. Propulsion, 5, 1986, pp. 406-410.
10.     N. Kubota and S. Miyazaki, “Temperature Sensitivity of Burning Rate of Ammonium Perchlorate Propellants,”
Propellants Explo. Pyrotech., 12, 1987, pp. 183-187.
11.     N. Kubota and K. Miyata, “Inhibition Reaction of SrCO3 on the Burning Rate of Ammonium Perchlorate Propellants,”
Propellants Explos. Pyrotech., 15, 1990, pp. 127-131.
12.     T. T. Nguyen, “New Insights into the Combustion of AP/HTPB Rocket Propellants: The Catalyst Active Sites and a Combustion Flame Model for the Ferrocene-Catalysed Combustion,” Defense Science & Technology Organization (DSTO), 1996, pp. 679-692.
13.     A. I. Atwood, T. L. Boggs, P. O. Curran, T. P. Parr, D. M. Hanson-Parr, C. F. Price and J. Wiknich, “Burning Rate of Solid Propellant Ingredients, part 2: Determination of Burning Rate Temperature Sensitivity,” Journal of Propulsion and Power, 15, 1999, pp. 748-752.
14.     N. Kubota, K. Uchiyama and N. Hirata, “Combustion Wave Structure of Ammonium Perchlorate Composite Propellants,” J. Propulsion, 2, 1986, pp. 296-300
 
 
 
15.     N. Kubota, Propellants and Explosives: Thermochemical Aspects of Combustion, WILEY-VCH Verlag GmbH & Co. KgaA, Weinheim, 2002.
16.     E. Cohen-Nir, “Temperature Sensitivity of the Burning Rate of Composite Solid Propellants,” Combustion Science and Technology, 9, 1974, pp. 183-194.
17.     N. S. Cohen and D. A. Flanigan, “Mechanisms and Models of Solid-Propellant Burn Rate Temperature Sensitivity: A Review,” AIAA Journal, 23, 1985, pp. 1538-1547.
18.     V. Yang, T. B. Brill and W. Z. Ren, Solid Propellant Chemistry, Combustion, and Motor Interior Ballistics, American Institute of Aeronautics, Reston, Virginia, 2000.
19.     T. D. Manship, “High Burn Rate Solid Composite Propellants,” Master of Science Thesis, Department of Aeronautics and Astronautics, Purdue University, West Lafayette, Indiana, 2010.
20.     K. K. Kuo and M. Summerfield, “Fundamentals of Solid Propellant Combustion,” American Institute of Aeronautics and Astronautics, New York, 1984, pp. 100-120.
21.     K. Kishore and M. R. Sunitha, “Effect of Transition Metal Oxides on Decomposition and Deflagration of Composite Solid Propellant Systems: A Survey,” AIAA Journal, 17, 1979, pp. 1118-1125.
22.     S. S. Joshi, P. R. Patil and V. N. Krishnamurthy, “Thermal Decomposition of Ammonium Perchlorate in the Presence of Nanosized Ferric Oxide,” Defense Science Journal, 58, 2008, pp. 721-727.
23.     S. R. Chacravarthy, E. W. Price and R. K. Sigman, “Mechanism of Burning Rate Enhancement of Composite Solid propellants by Ferric Oxide,” Journal of Propulsion and Power, 13, 4, 1997, pp. 471-480.
24.     K. K. Kuo and M. Summerfield, “Fundamentals of Solid Propellant Combustion,” American Institute of Aeronautics and Astronautics, New York, 1984, pp. 53-106.