Effect of amine-based burning rate suppressants on the HTPB propellants: Thermal decomposition and combustion characteristics.

Slow-burn propellants are crucial for aerospace advancement. This study focuses on the development of slow-burn propellants by replacing a small amount of AP (3–9 %) with various amine-based burning rate suppressants (BRSs). The consistency between thermal analysis and combustion test results indicates a direct link between the main exothermic decomposition process and combustion performance, with changes in onset temperature positively correlated with decreases in combustion parameters. Upon adding 3 % oxamide, the onset temperature of the main decomposition peak in DSC shifted backward by 16.2 °C, significantly higher than the formulations containing ammonium sulfate at 2.6 °C and ammonium oxalate at −0.8 °C. As the content of oxamide further increased from 3 to 9 %, the ignition delay time increased simultaneously by 0.300–1.638 s, atmospheric burning rate decreased by 14.01–45.45 %. These values represent the maximum among formulations with the same content of the BRSs, mainly attributed to its higher heat absorption capacity. • The onset temperature shift of the high-temperature decomposition peak, as the primary energy release phase, is positively correlated with the extent of combustion performance decline. • The introduction of three types of amine-based burning rate suppressants does not affect the light-absorbing properties of the propellants, but significantly influences the ignition behavior. • Infrared cameras have verified that certain particles of ammonium sulfate exit the burning surface alongside the gas before complete decomposition, resulting in a diminished effect on the reduction of the burning rate. [ABSTRACT FROM AUTHOR]