Structure for reducing influence of dissolved gas of the propellant on arc thruster

Abstract

The invention discloses a structure for reducing the influence of a dissolved gas of a propellant on an arc thruster. The structure for reducing the influence of the dissolved gas of the propellant onthe arc thruster includes a damper, an electromagnetic valve and a gas generator. The damper, the electromagnetic valve and the gas generator are hermetically connected in series. When the arc thruster works, the liquid propellant flows in a channel; according to the flow direction, the liquid propellant first passes through a first channel, then through a second channel, and finally enters a reaction chamber through a third channel, and is converted into the gas in the reaction chamber; and the gas enters the downstream arc discharge device. The channel is provided with at least one capillary throttling section; along the flow direction of the liquid propellant, all the capillary channels from the entrance of the first capillary throttling section to the exit of the channel are all capillary channels; and the pressure drop of the propellant liquid inside the arc thruster is all distributed in the capillary channels. The invention can significantly reduce the influence of the gas dissolved in the liquid propellant on the arc thruster.

Description

technical field [0001] The invention relates to an arc discharge device, in particular to an arc thruster suitable for a satellite propulsion system. Background technique [0002] At present, most of the arc propulsion systems used in satellite orbits use surface tension tanks to store liquid propellants (such as anhydrous hydrazine). Part of the extruded gas (usually helium) in the surface tension tank will be dissolved in the liquid propellant. It will precipitate out and accumulate into large bubbles during the long-term working process. When large bubbles pass through the arc thruster, the propellant mass flow rate in the discharge area inside the arc thruster will be greatly reduced, resulting in problems such as arc discharge instability, electrode ablation, sudden decrease in thrust, and arc extinguishment, which restrict the performance of the arc thruster performance and longevity. [0003] The existing technology is mainly to install a bubble interception and ac...

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to overcome the above-mentioned deficiencies of the prior art, provide a structure that reduces the influence of propellant dissolved gas on the arc thruster, and solve problems such as electrode ablation caused by air bubbles

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