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TG studies of a composite solid rocket propellant based on HTPB-binder

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Abstract

Thermal decomposition kinetics of solid rocket propellants based on hydroxyl-terminated polybutadiene-HTPB binder was studied by applying the Arrhenius and Flynn-Wall-Ozawa's methods. The thermal decomposition data of the propellant samples were analyzed by thermogravimetric analysis (TG/DTG) at different heating rates in the temperature range of 300-1200 K. TG curves showed that the thermal degradation occurred in three main stages regardless of the plasticizer (DOA) raw material, the partial HTPB/IPDI binder and the total ammonium perchlorate decompositions. The kinetic parameters E a (activation energy) and A (pre-exponential factor) and the compensation parameter (S p) were determined. The apparent activation energies obtained from different methods showed a very good agreement.

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Authors and Affiliations

  1. Instituto Tecnológico de Aeronáutica, Centro Técnico, Aeroespacial São José, dos Campos, S.P., Brasil

    J. A. F. F. Rocco, J. E. S. Lima, A. G. Frutuoso, K. Iha, M. Ionashiro, J. R. Matos & M. E. V Suárez-Iha

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  1. J. A. F. F. Rocco
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  2. J. E. S. Lima
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  3. A. G. Frutuoso
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  4. K. Iha
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  5. M. Ionashiro
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  6. J. R. Matos
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  7. M. E. V Suárez-Iha
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Rocco, J.A.F.F., Lima, J.E.S., Frutuoso, A.G. et al. TG studies of a composite solid rocket propellant based on HTPB-binder. Journal of Thermal Analysis and Calorimetry 77, 803–813 (2004). https://doi.org/10.1023/B:JTAN.0000041659.97749.fe

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  • DOI: https://doi.org/10.1023/B:JTAN.0000041659.97749.fe

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