Ablative pulse plasma thruster based on multi-anode electrode structure

Abstract

The embodiment of the invention provides an ablative pulse plasma thruster based on a multi-anode electrode structure. The ablative pulse plasma thruster comprises a cathode, a multi-anode structure and an insulation part, wherein the cathode is externally connected to a negative high voltage, and the multi-anode structure is connected to the ground. The cathode is of a cylindrical structure, a strong electric field is formed at the junction between three sides of the cathode, field emission is induced, so that initial electrons bombard the insulation part and desorbed gas molecules, and a plasma penetrating a vacuum gap is generated to form a vacuum arc; the multi-anode structure comprises a first anode and a second anode, the first anode is in a nozzle shape, and is used for maintainingthe electric field intensity at the three joint points of the cathode; the second anode is in a ring shape and is arranged at a preset distance from the cathode structure at a preset distance, so thatthe discharging process is completed; and the insulation part is in a cylindrical shape, wraps the outer part of the cathode, is embedded into the first anode, is used for providing a raw material for generating plasma, and is used for conducting insulation and mechanical fixation on the cathode and the first anode. According to the ablative pulse plasma thruster, the full constraint of the plasma propagation process can be realized.

Description

technical field [0001] The invention relates to the technical field of micro-satellite thrusters, in particular to an ablation pulse plasma thruster based on a multi-anode electrode structure. Background technique [0002] APPT (Ablative Pulse Plasma Thruster) has a simple structure, small size and high reliability, and is one of the promising electric thrusters. In recent years, the rapid development of microsatellites has put forward higher requirements for the propulsion effect of APPT. However, the bipolar diffusion of charged particles in the plasma plume has a greater impact on the propulsion effect of the thruster. In fact, beam divergence has become one of the unfavorable characteristics of ablative pulsed plasma thrusters. Therefore, optimizing the plasma plume to increase its density plays a key role in improving the propulsion effect of ablative pulsed plasma thrusters. [0003] In the process of plasma research, Z-pinch is an important plasma confinement metho...

AI Technical Summary

Problems solved by technology

Hu studied the propulsion effect of thrusters with magnetic rings of different diameters and found that the strength of the magnetic field will affect the utilization of the working fluid

Takahashi measured the axial magnetic field generated by the plasma flow in the diffused magnetic nozzle, and detected that the axial magnetic field strength decreased near the nozzle, but the magnetic field strength increased at the upper end of the magnetic nozzle.

However, the magnetic field generated by permanent magnets or external circuits will increase the volume, mass and complexity, which is not conducive to its application in ablative pulsed plasma thrusters

[0005] Therefore, it is necessary to design an ablative pulsed plasma thruster with a multi-anode approach that can redirect the current path to form plasma confinement outside the nozzle and achieve highly pinched plasma without using any external measures. Jet flow, to solve the problem that the traditional Z-pinch cannot effectively act on the plasma leaving the nozzle, and the problem of mass and volume increase caused by the external magnetic field

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