A novel hall thruster utilizing space debris as the propellant

摘要

The paper proposed a new conception of using space debris as the working medium of the hall thruster. At first, we described differences of the physical properties between the space debris powder and gaseous propellants and estimated the charge quantity of the charged space debris powder. Then, we dealt with the operating principles and design process of the novel hall thruster with a modified cusped configuration of magnetic field along the discharge channel to make the ionization process more uniform and efficient. Given a design case, we demonstrated the validity of the novel idea through the simulation by the ANSYS Maxwell of the magnetic field distribution. The results are that the cusped configuration is 230-310 Gauss (increasing from the central line of discharge channel to the wall) in magnetic field and its gradient is 107 Gauss/cm, the maximum radial magnetic field is located in the exit plane of the thruster and has a 230 Gauss/cm gradient and a trend of inwards concave. This novel hall thruster with space debris as the propellant will not only augment the effective payload of the spacecraft and decrease the economic burden of the xenon propellant, but also it can resolve the space debris problem substantially.