Journal of Thermal Analysis and Calorimetry

, Volume 107, Issue 1, pp 135–140 | Cite as

The pressure effect study on the burning rate of ammonium nitrate-HTPB-based propellant with the influence catalysts



The burning rate of AN–HTPB-based propellant catalysed with chromium salt has been studied using conventional strand burner under the various pressure range, i.e. from atmospheric pressure to 6.897 MPa and verified with Piobert law, i.e. r = aP n . At atmospheric pressure, the burning rate AN–HTPB propellant was being accelerated with the chromium-based catalysts used. In case of lead chromate-catalysed system, burning rate was observed 2.655 times higher than burning rate (r = 0.200 mm s−1) of virgin AN–HTPB propellant sample. However, the Copper chromate-catalysed propellant burned with slower rate (r = 0.160 mm s−1) than the virgin AN–HTPB propellant sample. The burning rate of all catalysed propellant samples are found to be the pressure sensitive and accelerated higher with rise of pressure. The highest burning rate (r = 2.422 mm s−1) was recorded with ammonium dichromate and lowest (r = 1.40 mm s−1) with lead chromate-catalysed propellant sample with the rise of pressure up to 6.897 MPa at different pressures. A linear relationship was observed between the burning rate and pressure rise which followed the Piobert law, i.e. r = aP n . The pressure index (n) values of AN–HTPB-based samples were calculated higher when catalysed with ammonium dichromate, Copper Chromate, Cr2O3, Potassium dichromate (n = 0.525, 0.555, 0.429, and 0.408 respectively) and lower (n = 0.226) with lead chromate compared to virgin sample (n = 0.405). Higher value indicates the positive effect on accelerating the burning rate with catalyst at higher pressure ranges.


Burning rate Catalytic effect Pressure effect AN–HTPB propellant Pressure index 


  1. 1.
    Hamilton BK. Method for making a propellant having a relatively low burn rate exponent and high gas yield for use in a vehicle inflator, US Patent 6315930, Nov 2001.Google Scholar
  2. 2.
    Batchelder GW. Solid composite, smokeless, slow burning, low flame propellant, UP Patent 2974026, March 1997.Google Scholar
  3. 3.
    Jones JL. Smokeless slow burning cast propellant—ammonium nitrate, catalyst, methyl acrylate copolymer, US Patent 4112,849, Sept 1978.Google Scholar
  4. 4.
    Simoes P, Pedroso L, Portugal A, Plaksin I, Campos J. New propellant component part II. Study of a PSAN/DNAM/HTPB based formulation. Propellant Explos Pyrotech. 2001;26(6):278–83.CrossRefGoogle Scholar
  5. 5.
    Arakawa Y, Kohga M. Combustion characteristics of ammonium nitrate based composite solid propellant: effect of mean diameter of ammonium nitrate. Kayaku Gakkaishi. 1997;58(2):76–82.Google Scholar
  6. 6.
    Arakawa Y, Kohga M. Ammonium nitrate based composite solid propellant 2: effects of addition of surfactants on viscosity of uncured propellant. Kayaku Gakkaishi. 1997;58(2):83–8.Google Scholar
  7. 7.
    Kuwahara T, Matsno S. Burning rate characteristics and ignition characteristics of ammonium nitrate/ammonium perchlorate composite propellants. Kayaku Gakkaishi. 1995;56(3):135–40.Google Scholar
  8. 8.
    Kato K, Goro N. Burning rate characteristics of GAP/AN propellant. Kayaku Gakkaishi. 1995;56(3):130–4.Google Scholar
  9. 9.
    Hagihara Y. Effects of chromium and cobalt compounds on burning rate of AN/HTPB composite propellant. Kogyo Kayaku (Sci Technol Energ Mater). 1991;52(6):390–395.Google Scholar
  10. 10.
    Kempa PB, Herrmann M, Engel W. Dilatometric measurement of phase stabilized ammonium nitrate (CuPSAN) performed by X-ray Diffraction. In: 29th international annual conference ICT, on energetic materials, 1998, p. 73.1–73.11.Google Scholar
  11. 11.
    Brewster MQ, Sheridan TA, Ishihara A. Ammonium nitrate–magnesium propellant combustion and heat transfer mechanisms. J Propuls Power. 1992;18(4):760–9.CrossRefGoogle Scholar
  12. 12.
    Murata H, Azuma Y, Tohara T, Simoda M, Yamaya T, Hori K, Saito T. Effect of magnalium (Mg–Al Alloy) on combustion characteristics of ammonium nitrate based solid propellant. Kayaku Gakkaishi. 2000;61(2):58–66.Google Scholar
  13. 13.
    Backstead MV, Derr RL, Price CF. A model of composite solid propellant combustion based on multiple flame. AIAA J. 1970;8(12):2200–7.CrossRefGoogle Scholar
  14. 14.
    Hermance CF. A model of composite propellant combustion including surface heterogeneity and heat generation. AIAA J. 1966;4(9):1629–37.CrossRefGoogle Scholar
  15. 15.
    Fenn JB. A Phalanx flame model for the combustion of composite solid propellants. Combust Flame. 1968;12(3):201–16.CrossRefGoogle Scholar
  16. 16.
    Andersen WH, Bills KW, Mishuck E, Moe G, Schultz RD. A model describing combustion of solid composite propellants containing ammonium nitrate. Combust Flame. 1959;3:301–17.CrossRefGoogle Scholar
  17. 17.
    Chaiken RF. A thermal layer mechanism of combustion of solid composite propellants. Combust Flame. 1959;3:285–300.CrossRefGoogle Scholar
  18. 18.
    Chaiken RF, Anderson WH. The role of binder in composite propellant combustion. Solid propellant rocket research, progress in astronautics and rocketry Vol. I. New York: Academic Press; 1960. p. 227–47.Google Scholar
  19. 19.
    Carvalheira P, Campos J. A combustion model for AN/HTPB-IPDI composite solid propellant. In: Proceeding of international conference on energetic materials-technology, manufacturing and processing, Institut Chemische Technologie, Germany, 1996, p. 12.1–12.21.Google Scholar
  20. 20.
    Kondrikov BN, Annikov VE, Egorshev VU, DeLuca L, Bronzi C. Combustion of ammonium nitrate-based compositions, metal-containing and water impregnated compounds. J Propuls Power. 1999;15(6):763–71.CrossRefGoogle Scholar
  21. 21.
    Sarner SF. Propellant chemistry. New York: Reinhold Publishing Corporation; 1966.Google Scholar
  22. 22.
    Kadiresh PN, Sridhar BTN. Experimental study on ballistic behaviour of an aluminised AP/HTPB propellant during accelerated aging. J Therm Anal Calorim. 2010;100(1):331–5.CrossRefGoogle Scholar
  23. 23.
    Yi J-H, Zhao F-Q, Ren Y-H, Wang B-Z, Zhou C, et al. BTATz-CMDB propellants, high-pressure thermal properties and their correlation with burning rates. J Therm Anal Calorim. 2011;104(3):1029–36.CrossRefGoogle Scholar
  24. 24.
    Munjal NL, Joshi PC, Shrivastava BP. Burning rate studies of HTPB-AP composite solid propellants. National convention on Indian space programme for 2000 & beyond a prospective, BIT Mesra, India, Dec 1998, p. 197–215.Google Scholar
  25. 25.
    Rastogi RP, Syal V. Pressure dependence of catalysed and inhibited burning rate of composite solid propelants. Indian J Chem. 1989; 28A:452–7.Google Scholar
  26. 26.
    Varma M, Pandey M. Thermal decomposition studies on catalysed ammonium nitrate. In: Proceeding, HEMCE 2000, of the 3rd international convention on high energy materials, VSSC Trivendrum, India, 6–8 Dec, 2000, p. 182–188.Google Scholar

Copyright information

© Akadémiai Kiadó, Budapest, Hungary 2011

Authors and Affiliations

  • M. Pandey
    • 1
  • S. Jha
    • 1
  • R. Kumar
    • 2
  • S. Mishra
    • 2
  • R. R. Jha
    • 2
  1. 1.Sikkim Manipal Institute of TechnologyMajitarIndia
  2. 2.Department of ChemistryRanchi UniversityRanchiIndia

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