Abstract
In order to clarify the discharge principle of the self-field magnetoplasmadynamic thruster (MPDT), a two-dimensional axisymmetric particle-in-cell/Monte Carlo collision (PIC/MCC) model is proposed. The spatial distribution and the collision characteristics of discharge plasma were calculated using this model. In addition, the influence of the operation parameters on the plasma was analyzed including the voltage and mass flow rate. The effectiveness of the model was verified by comparison to the experimentally induced magnetic field. It was found that the electrons were mainly accelerated by the electric field in the cathode sheath and the electric field shielding effect of plasma was obvious in the bulk plasma region. Due to the pinch effect, the charged particles were constrained near the cathode. The results of the present work implied that the PIC/MCC model provides an approach to investigate the plasma distribution and a kinetic description of particles for the discharge of the self-field MPDT.
Highlights
Magnetoplasmadynamic thrusters (MPDTs) have been one of the most competitive accelerators for space propulsion application such as deep space exploration, orbit transfer, etc
Considering the distribution of the electrons’ radial velocity, we can guess that the electrons emitted from the cathode were accelerated by the strong electric field in the cathode sheath
This paper presents a particle-in-cell/Monte Carlo collision (PIC/MCC) simulation model for the discharge process of the self-field MPDT
Summary
Magnetoplasmadynamic thrusters (MPDTs) have been one of the most competitive accelerators for space propulsion application such as deep space exploration, orbit transfer, etc. Improvement of the self-field MPDT’s performance is seriously restricted by low efficiency—about. The characteristic feature of the self-field MPDT is that the magnetic field Bsf is induced by the discharge current j. The electromagnetic force Fj×B is generated by coupling the discharge current and induced magnetic field in the azimuthal direction. The gas propellant is heated, ionized, and accelerated by the effect of electrothermal or electromagnetic exhaust as high-enthalpy plasma, approximately tens of kilometers per second eventually. It is extremely difficult to improve thruster performance without a profound insight into such a complicated process
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