Abstract
This work is devoted to the study of the influence of mechanical activation of aluminum, as well as its modification with graphite on the combustion processes of solid rocket propellant (SRP). Experiments were conducted to determine the ignition induction period, combustion rate and combustion products. Experimental work on ignition and combustion diagnostics was carried out using a diagnostic system at the Institute of Space Propulsion (ISP) of Nanjing University of Science and Technology. A multifunctional combustion diagnostic system was used to characterize the combustion processes of finished SRP samples. A high-speed camera was used to capture the combustion surface regression for various fuels, which can be used to derive their burning rate. The addition of graphite during the mechanochemical activation (MCA) of aluminum significantly affected particle shape and the state of the oxide film, improving the batch homogeneity and increasing the specific surface area. The optimal graphite concentration was approximately 10%, providing additional activation, while 20% graphite caused recoating of the particles and reduced processing efficiency. At constant pressure, it was found that MCA and the introduction of graphite accelerated composite combustion without disrupting stable combustion, with a relatively uniform front. The highest combustion velocity (3.0 mm s−1) was achieved with 10% graphite due to effective heat transfer and catalysis, while increasing its content to 20% reduced the combustion velocity, indicating an optimum of approximately 10%.