The paper is focused on the effects of carbonaceous materials on the combustion performance of widely known rocket propellant hydroxylammonium nitrate (HAN:[NH3OH]+[NO3]-). In this work compared the combustion of the HAN-based propellant with that of carboxymethyl cellulose gel and high surface area activated carbon based on vegetable raw materials as a carbonized rice husk. Based on results described the influence of additives on the reaching of linear burning rates of the propellant, were determined under a range of pressures up 10 atm to 70 atm in nitrogen media as a pressurizing agent. A kinetics study of thermal decomposition of HAN propellant with the activated carbon activated carbon 1 wt. were assessed by differential thermal analysis (DTA–TG) at different heating rates. Based on DTA results shown, that the additives of activated carbon decreases the ignition temperature and activation energy of HAN propellant compared to the propellant alone. Carried out the hard ionization of the HAN and activated carbon mixture that investigated by electron ionization mass spectrometry at different heating rates (from 16 K/min to 128 K/min). The formation intensity of major products and product distribution showing the effect of activated carbon on thermal decomposition of HAN based propellant.