Hot pressurized xenon filling method for satellite electric propulsion system

A thermal pressurization and electric propulsion technology, applied in the container filling method, container discharge method, equipment loaded into the pressure vessel, etc., can solve problems such as leaks, achieve high cleanliness, reasonable test methods, and comprehensive and complete measurement data Effect

Active Publication Date: 2016-02-10
BEIJING INST OF CONTROL ENG
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  • Summary
  • Abstract
  • Description
  • Claims
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Problems solved by technology

[0009] To sum up, the hot pressurized xenon filling method of the satellite electric propulsion system is the result of exploration and summary in the process of gradually realizing the engineering application of the electric propulsion system. For reference, foreign countries rarely disclose similar methods

Method used

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  • Hot pressurized xenon filling method for satellite electric propulsion system
  • Hot pressurized xenon filling method for satellite electric propulsion system
  • Hot pressurized xenon filling method for satellite electric propulsion system

Examples

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Embodiment

[0037] Such as figure 1 As shown, the system includes xenon gas storage tank 1, storage tank weighing electronic scale 2, gas source valve 3, thermal booster A4, thermal booster B5, liquid nitrogen valve A6, liquid nitrogen valve B7, liquid nitrogen valve C8 , liquid nitrogen tank 9, helium cylinder 10, helium valve 11, control and data acquisition module 12, purity analyzer 13, filling valve 14, star cylinder 15, vacuum valve 16, vacuum pump 17, recovery valve 18, Recovery module 19, deflation valve 20, gas cylinder weighing device 21 on the star.

[0038] The pipelines used for system connection are high-polished stainless steel high-pressure pipelines. The specific connection method is as follows: The xenon storage tank 1 is placed on the storage tank weighing electronic scale 2, and the high-pressure pipeline is used to connect it with the gas source valve 3 and The thermal booster device A4 and the thermal booster device B5 are connected; the liquid nitrogen tank 9, the ...

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Abstract

The invention relates to a thermal pressurized xenon filling method of an electric satellite propelling system, belongs to the technical field of high-purity xenon filing experiments in the electric satellite propelling system and is suitable for the filling experiments of electric propelling systems using high-purity xenon as a work medium. According to the technical requirement of high-purity xenon filing in the electric satellite propelling system, a thermal pressurizing type xenon filling method is reasonably designed. The method has the advantage of being high in cleanliness degree, accurate in temperature control, high in reliability, convenient in module replacement and comprehensive in date measurement and the filling task requirement of the high-purity xenon can be effectively met. According to the method, a pneumatic valve is used for automatic control and has the strong matching performance with the system pressure and temperature; the cooperation of the switch control on the pneumatic valve and the filling process is realized; the automatic control on xenon suction and filling can be realized; the xenon in a satellite gas supply bottle can be prevented from flowing back to an experiment system during an experiment and the safety and the reliability of the xenon filling experiment can be guaranteed.

Description

technical field [0001] The invention relates to a hot-pressurized xenon filling method for a satellite electric propulsion system, belongs to the technical field of high-purity xenon filling tests for satellite electric propulsion systems, and is suitable for filling tests of all electric propulsion systems using high-purity xenon as a working medium. Background technique [0002] At present, there are many types of propulsion systems for in-orbit flight, among which the electric propulsion system has developed rapidly in recent years due to its high specific impulse, especially the Hall electric propulsion system and the ion electric propulsion system are popular, and are often used in geostationary orbit satellites The platform performs tasks such as north-south position keeping, attitude control (momentum wheel unloading), orbit control, and even synchronous orbit transfer. In addition, electric propulsion systems can accomplish tasks that conventional propulsion systems ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F17C5/06F17C13/00
Inventor 宋飞孙水生武葱茏刘国西山世华翟阔阔刘学樊超林震宇文雷韩飞龙
Owner BEIJING INST OF CONTROL ENG
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