Virtual cathode arc propeller adopting dielectric barrier discharge

Abstract

The invention discloses a virtual cathode arc propeller adopting dielectric barrier discharge. The virtual cathode arc propeller adopting dielectric barrier discharge comprises a metal sleeve, a sealing element, an intake port, a cathode, and an anode with a spray port, wherein the cathode is a virtual cathode; the virtual cathode is a metal cylinder with a length; and a glass dielectric is fixedto one end of the virtual cathode in a sintering manner. According to the virtual cathode arc propeller adopting dielectric barrier discharge, the glass dielectric is fixed to the top end of the cylindrical virtual cathode in the sintering manner, so that an ablation effect of the arc propeller on the cathode and the anode in a working process can be avoided, the on-orbit life of the propeller isgreatly prolonged, and the practicability of the arc propeller is improved.

Description

technical field [0001] The invention belongs to the field of space electric propulsion technology, in particular, the invention relates to a dielectric barrier discharge arc thruster. Background technique [0002] Usually, the arc thruster causes ablation of the arc cathode and anode due to its own discharge principle, and its on-orbit working life is generally difficult to exceed 2000h, which greatly limits its application range. [0003] The thermal ablation problem of the cathode and anode of the arc thruster is mainly determined by its discharge principle. The structure of the arc thruster in the prior art refers to figure 1 , the dielectric barrier discharge virtual cathode arc thruster includes a metal casing 1, a seal 2, an air inlet 3, a cathode 4 with a tip portion, and an anode 5 that surrounds the tip portion of the cathode 4 on a circumference and forms a spout near the top of the tip ; Wherein, one end of the metal sleeve 1 is clamped on the protruding part of ...

AI Technical Summary

Problems solved by technology

[0005] Arc discharge is a constant current discharge process, the current of the arc column remains constant, the lap resistance on the anode and cathode increases with the thermal ablation resistance, and the thermal power consumption at the root of the arc increases with the increase of temperature, resulting in lap The resistance shows a non-linear growth, the electric power of the arc is gradually consumed in the heat dissipation of the cathode and anode structures, and the electric power of the arc heating working medium is gradually reduced, which leads to the interruption of the arc

[0006] The service life of general arc thrusters on orbit is difficult to exceed 2000h, which greatly limits its application range

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