Ionic liquid electronic injection thruster for controlling liquid supply through electric field

A technology of ionic liquid and electric field control, which is applied in the direction of using plasma, thrust reverser, machine/engine, etc., to achieve the effect of improving stability, increasing service life, and increasing total volume

Active Publication Date: 2021-05-11
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, it uses liquid working fluid as the propellant. The thrust of the traditional porous media type ionic liquid EFI thruster decreases after the liquid working fluid is consumed to a certain extent. The disadvantage lies in the stability and life of the launch.

Method used

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  • Ionic liquid electronic injection thruster for controlling liquid supply through electric field
  • Ionic liquid electronic injection thruster for controlling liquid supply through electric field
  • Ionic liquid electronic injection thruster for controlling liquid supply through electric field

Examples

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Embodiment 1

[0029] An ionic liquid EFI thruster disclosed in this implementation includes a liquid storage tank 1, a copper sheet 3 covered with a hydrophobic dielectric layer, an insulating gasket 6 for controlling the distance between the copper sheets, and an upper casing 2. Emitter 4 and Extractor 5.

[0030] The liquid storage tank 1 is made of insulating material, has a length of 30 mm, a width of 30 mm, a height of 10 mm, and a bottom wall thickness of 2 mm. Design grooves on opposite side walls, with a length of 5 mm, a width of 1.6 mm, and a depth of 4 mm.

[0031] The hydrophobic dielectric layer is composed of N-type parylene with a thickness of 10 μm and Teflon with a thickness of 500 nm, and has good dielectric and hydrophobic properties.

[0032] The ionic liquid is 1-ethyl-3-methylimidazolium tetrafluoroborate (EMI-BF 4 ), the initial contact angle with the hydrophobic dielectric layer is 100°.

[0033] The copper sheet 3 covered with the hydrophobic dielectric layer is ...

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Abstract

The invention relates to an ionic liquid electronic injection thruster for controlling liquid supply through an electric field, and belongs to the technical field of micro-propulsion of micro-nano satellites. The ionic liquid electronic injection thruster comprises a liquid storage tank, a copper sheet covered with a hydrophobic dielectric layer, an insulating spacer used for controlling the distance of the copper sheet, an upper shell, an emitting electrode and an extraction electrode. According to the thruster, the wettability between the ionic liquid and the porous medium type emitting electrode is improved through the electric field, meanwhile, the flowing characteristic of the ionic liquid in a capillary pipeline is controlled through the electric field, active supply of a propellant can be achieved, the emission stability of the ionic liquid electronic injection thruster is improved, the service life of the ionic liquid electronic injection thruster is prolonged, the thruster is suitable for resistance compensation of low-power micro-nano satellites, and task requirements of position keeping, attitude control and the like are met.

Description

technical field [0001] The invention relates to an ionic liquid electrojet thruster with liquid supply controlled by an electric field, and belongs to the technical field of micro-nano-satellite micro-propulsion. Background technique [0002] Low cost, short development period, and flexible launch are the main advantages of micro-nano satellites. At present, micro-nano satellites have been widely used in the fields of communication, remote sensing, earth observation and space experiments, and have broad prospects. Since the micro-nano satellite is limited by total power, mass and volume, its propulsion system needs to have the characteristics of low power consumption, light weight, small size, long life, and precise thrust. Ionic Liquid Electrospray Thruster (ILET) has the characteristics of small size, light weight, high specific impulse, and high thrust accuracy, which can meet the requirements of micro-nano satellites for propulsion systems, and is an ideal propulsion sys...

Claims

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Application Information

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IPC IPC(8): F03H1/00
CPCF03H1/0037
Inventor 武志文孙伟孙振宁韩雨宁王云冰
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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