Combustion promotion and agglomeration reduction of the composite propellant using graphene

Abstract

Graphene and its composites are promising catalysts for energetic materials. In order to realize the application of graphene in solid propellant, the effects of graphene content on the ignition, combustion and agglomeration characteristics of composite propellant were thoroughly conducted based on thermogravimetric-differential scanning calorimetry measurements (TG-DSC), laser ignition, combustion diagnoses, burning rate test and condensed combustion products collection. Results show that graphene effectively promotes the thermal decomposition of AP. 3 wt.% graphene advances the thermal decomposition temperature of AP by 68.3 °C, and 1 wt.% graphene increases the apparent decomposition heat of AP by 2.6 times. Laser ignition experiments show that the combustion intensity and mass burning rate increase, while the ignition delay time decreases with increasing graphene content. The addition of graphene is found to increase the burning rate at 0.1 MPa, but the effect is not obvious at 1-7 MPa, thus reducing the pressure exponent. 0.5 wt.% graphene can reduce the pressure exponent from 0.43 to 0.34. Compared with the baseline propellant, more aluminum particles are ignited on the surface of the propellant containing graphene and the large size agglomerates in the condensed combustion products decrease significantly. Overall, graphene plays a comprehensive effect on the ignition, combustion and agglomeration characteristics of aluminized propellant. Results of this study can help guide the application and development of graphene or graphene-inclusion materials in solid propellant for solid rocket motors.