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Burning Rate Study of PSAN-HTPB Based Solid Rocket Propellants


Affiliations
1 Department of Aeronautical Engineering, Bhubaneswar Engineering College, Bhubaneswar, Odisha, India
     

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Composite propellants based on Ammonium Perchlorate (AP) as oxidizer are in major role in solid rocket. However, because of their high toxic exhaust, it is not suggested for global environmental pollution issue. Therefore, researchers want to replace AP based propellants with clean exhaust propellant. Ammonium Nitrate (AN) has the properties which can satisfy the present environmental need in the field of propellant. However, the disadvantage for the application of AN-as solid propellant oxidizer is its dimensional instability in different temperature ranges due to phase transformation which causes change of volume and porosity of the propellant grain. This was be resolved by the use of Phase Stabilized Ammonium Nitrate (PSAN) for propellant processing. Synthesized mixed metal oxides were used to enhance burning rate. These propellant samples were then tested for measuring burn rate in a Crawford High Pressure Strand Burner and thermal degradation studies carried out Simultaneously in Thermal Analyzer (STA). It is observed that the thermal decomposition and burn rate of the propellant is maximum by adding anyone of the mixed metal oxide catalyst among 3 different catalysts. In this research the different samples are formulated to test and get results. It has been observed that only two propellants burnt properly as compared to other propellants taken for the analysis.

Keywords

Burn Rate, Catalytic Combustion, Preparation of Catalyst, Preparation of PSAN, Solid Propellants, Thermal Decomposition.
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  • M. W. Beckstead, R. L. Derr, and C. F. Price, “A model of composite solid propellant combustion based on multiple flames,” AIAA Journal, vol. 8, no. 12, pp. 2200-2207, 1970.

  • M. Pandey, and S. Jha, “Pressure effect study on burning rate of AN-HTPB propellant,” Academic Journal, vol. 107, Jan. 2012.

  • J. C. Handley, and W. C. Strahle, “Behaviour of several catalysts in the combustion of solid propellant sandwiches,” AIAA Journal, vol. 13, no. 1, pp. 5-6, 1975.

  • C. W. Fong, and B. L. Hamshere, “The mechanism of burning rate catalysis in composite HTPB-AP propellant combustion,” Combustion and Flame Journal, vol. 65, no. 1, pp. 61-69, 1986.

  • C. W. Fong, and B. L. Hamshere, “The mechanism of burning rate catalysis in composite propellants by transition-metal complexes,” Combustion and Flame Journal, vol. 65, no. 1, pp. 71-78, 1986.

  • T. Valdes-Solis, G. Marban, and A. B. Fuertes, “Nanosized catalysts for the production of hydrogen by methanol steam reforming,” Catalysis Today Journal, vol. 116, no. 3, pp. 354-360, 2006.

  • L. Patron, V. Pocol, O. Carp, E. Modrogan, and M. Brezeanu, “New synthetic route in obtaining copper chromite (I): Hydrolysis of some soluble salts,” Materials Research Bulletin, vol. 36, no. 7-8, pp. 1269-1276, 2001.

  • A. M. Kawamoto, L. C. Pardini, and L. C. Rezende, “Synthesis of copper chromite catalyst,” Aerospace Science and Technology Journal, vol. 8, no. 7, pp. 591-598, 2004.

  • S. Methew, K. Krishnan, and K. N. Ninan, “Effect of energetic material on thermal decomposition of PSAN - An eco-friendly oxidizer,” Defense Science Journal, vol. 49, no. 1, pp. 65-69, Jan. 1999.

  • L. T. Deluca, L. Galfetti, F. Maggi, G. Colombo, A. Bandera, S. Cerri, and P. Donega, “Burning of metallized composite solid rocket propellants: Toward nanometric fuel size,” 2nd International Symposium on Propulsion for Space Transportation, At Heraklion, Crete, Greece, 5-8 May 2008.

  • E. W. Price, R. K. Sigman, S. R. Chakravarthy, and P. D. Paulsen, “Hot stage microscope studies of decomposition of propellant ingredients,” Proceedings of the 30th JANNAF Combustion Meeting, II, JANNAF, pp. 289-296, Nov. 1993.


Abstract Views: 443

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  • Burning Rate Study of PSAN-HTPB Based Solid Rocket Propellants

Abstract Views: 443  |  PDF Views: 6

Authors

Rajan Lakra
Department of Aeronautical Engineering, Bhubaneswar Engineering College, Bhubaneswar, Odisha, India
Swagat Prasad Das
Department of Aeronautical Engineering, Bhubaneswar Engineering College, Bhubaneswar, Odisha, India
S. K. Samal
Department of Aeronautical Engineering, Bhubaneswar Engineering College, Bhubaneswar, Odisha, India

Abstract


Composite propellants based on Ammonium Perchlorate (AP) as oxidizer are in major role in solid rocket. However, because of their high toxic exhaust, it is not suggested for global environmental pollution issue. Therefore, researchers want to replace AP based propellants with clean exhaust propellant. Ammonium Nitrate (AN) has the properties which can satisfy the present environmental need in the field of propellant. However, the disadvantage for the application of AN-as solid propellant oxidizer is its dimensional instability in different temperature ranges due to phase transformation which causes change of volume and porosity of the propellant grain. This was be resolved by the use of Phase Stabilized Ammonium Nitrate (PSAN) for propellant processing. Synthesized mixed metal oxides were used to enhance burning rate. These propellant samples were then tested for measuring burn rate in a Crawford High Pressure Strand Burner and thermal degradation studies carried out Simultaneously in Thermal Analyzer (STA). It is observed that the thermal decomposition and burn rate of the propellant is maximum by adding anyone of the mixed metal oxide catalyst among 3 different catalysts. In this research the different samples are formulated to test and get results. It has been observed that only two propellants burnt properly as compared to other propellants taken for the analysis.

Keywords


Burn Rate, Catalytic Combustion, Preparation of Catalyst, Preparation of PSAN, Solid Propellants, Thermal Decomposition.

References