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

Authors :: Rocco, J. A. F. F.
Lima, J. E. S.
Frutuoso, A. G.
Iha, K.
Ionashiro, M.
Matos, J. R.
Suárez-Iha, M. E. V
Source :: Journal of Thermal Analysis & Calorimetry; 2004, Vol. 77 Issue 3, p803-813, 11p
Publication Year :: 2004
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<subscript>a</subscript> (activation energy) and A (pre-exponential factor) and the compensation parameter (S<subscript>p</subscript>) were determined. The apparent activation energies obtained from different methods showed a very good agreement. [ABSTRACT FROM AUTHOR]