This invention belongs to the field of thrusters, specifically relating to an electrically controlled
solid propellant afterburning
propellant and a thruster
system. The electrically controlled
solid propellant afterburning propellant, by weight, comprises 65-95 parts oxidizer, 5-25 parts binder, and 0.3-5 parts curing agent. When the main
combustion chamber is energized, the high-temperature, fuel-rich gas flow generated in the main
combustion chamber washes over the surface of the afterburning propellant, rapidly reaching its
pyrolysis temperature and instantaneously releasing
oxygen. When applied to an electrically stimulated thruster
combustion enhancement device, the afterburning propellant, upon heating, decomposes to produce
oxygen-rich gas, which can mix and burn with the high-temperature, fuel-rich gas generated from incomplete combustion in the main
combustion chamber. This fully utilizes the electrically controlled
solid propellant, and the afterburning propellant offers controllable combustion, thereby significantly improving propellant combustion efficiency and thrust performance without affecting the thruster's electrically controlled combustion characteristics.