The combustion waves of double-base propellants containing reactive metals such as aluminum (Al), magnesium (Mg), boron (B), nickel (Ni) and Mg-Al mechanical alloy (Mg/Al=3/4) has been experimentally investigated by means of thermal couple method. The heat effect of metals in the condensed phase which might control the burning characteristics of the double-base propellant was systematically investigated and descriptions of the detailed combustion physical model of the metals from solid phase to liquid phase or to gas phase are also included. Moreover, a numerical calculation method for analyzing combustion wave structure of metallized propellants has been designed and the fitting functions for the
temperature profiles were obtained by Origin 7.5 software. It is believed that in gas phase there would be multi-stage reaction mechanism and that the reaction mechanism would be identical in condensed phase for different metallized propellants, only the heat release value was different.