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A structure to reduce the impact of propellant dissolved gas on arc thrusters

A technology of dissolved gas and thrusters, applied in thrust reversers, space vehicle propulsion system devices, aircraft, etc., can solve problems such as electrode ablation, and achieve the effect of improving utilization rate and simple structure

Active Publication Date: 2021-04-13
BEIJING INST OF CONTROL ENG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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

Method used

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  • A structure to reduce the impact of propellant dissolved gas on arc thrusters
  • A structure to reduce the impact of propellant dissolved gas on arc thrusters
  • A structure to reduce the impact of propellant dissolved gas on arc thrusters

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Embodiment Construction

[0025] Below in conjunction with accompanying drawing, specific embodiment of the present invention is described in further detail:

[0026] Such as figure 1 Shown is the structural representation of the present invention, by figure 1 It can be seen that a structure for reducing the influence of propellant dissolved gas on the arc thruster includes: a damper 1 , a solenoid valve 2 and a gas generator 3 . The liquid propellant is monopropellant grade anhydrous hydrazine.

[0027] The flow channel inside the damper 1 is used as the first channel 4, the flow channel inside the solenoid valve 2 is used as the second channel 5, and the inside of the gas generator 3 is provided with a reaction chamber 7; are connected through the third channel 6; the inlet of the first channel 4 of the damper 1 is connected to the external liquid propellant pipeline;

[0028] The damper 1, the solenoid valve 2 and the gas generator 3 are connected in series in sequence, and the connecting parts b...

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Abstract

A structure for reducing the influence of propellant dissolved gas on an arc thruster, including a damper, a solenoid valve and a gas generator. The damper, solenoid valve and gas generator are connected in series and sealed. When the arc thruster is working, the liquid propellant flows in the channel. According to the flow direction, it first passes through the first channel, then passes through the second channel, and finally enters the reaction chamber through the third channel, where it is converted into gas, and the gas enters the downstream. arc discharge device. The channel has at least one capillary flow section; along the liquid propellant flow direction, the capillary channels from the inlet of the first capillary flow section to the outlet of the channel are all capillary channels; the pressure drop of the propellant liquid inside the arc thruster All distributed in the capillary channel. 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...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F03H1/00B64G1/40
CPCB64G1/405F03H1/0093F03H1/0012B64G1/415
Inventor 仝颖刚魏福智姚兆普胡大为沈岩陈健夏继霞吴耀武
Owner BEIJING INST OF CONTROL ENG