Non-toxic dual mode micropropulsion system and working method thereof

A micro-propulsion, dual-mode technology, which is applied to the propulsion system devices of space navigation vehicles, space navigation equipment, space navigation vehicles, etc. Effect

Active Publication Date: 2018-07-13
SHANGHAI INST OF SPACE PROPULSION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] At present, the conventional chemical propulsion system and electric propulsion system used by satellites require a propellant supply system composed of pressure-resistant storage tanks, valves, pressure sensors, and pipelines. The system is complex, and the thrust is generally in the order of cattle, making miniaturization difficult
Hydrazine, dinitrogen tetroxide, monomethylhydrazine and other propellants commonly used in chemical propulsion systems are highly toxic, which is not conducive to use, maintenance and environmental protection
The power of conventional Hall and ion electric propulsion systems is generally on the order of hundreds of watts to kilowatts, and it is difficult to miniaturize to the order of watts, or the performance of the thruster is very poor after reaching the order of watts, making it difficult to use in engineering
Although the xenon propellant commonly used in electric propulsion is non-toxic, it is expensive, which limits its application to a certain extent

Method used

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  • Non-toxic dual mode micropropulsion system and working method thereof
  • Non-toxic dual mode micropropulsion system and working method thereof
  • Non-toxic dual mode micropropulsion system and working method thereof

Examples

Experimental program
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Effect test

Embodiment 1

[0090] The non-toxic dual-mode micro-propulsion system of the present invention has a thruster body 1 with a diameter of 20mm, a spray ultrasonic vibration unit 5 with a frequency of 180kHz, a diameter of 15mm, a spray grid 26 with a diameter of 15mm, and 320 pieces with a top diameter of 2μm and a bottom diameter of 30μm distributed in the center Tapered grid holes 29, the distance between the grid holes 29 is 0.13mm. The propellant 36 adopts EMI-Im (1-ethyl-3-methylimidazoline bis(trifluoromethylsulfonyl)imide) ionic liquid, the storage capacity is 30ml, and the injection shell 4 is made of polyether ether ketone. The jet transport element 7 is made of fibers. The neutralizer 2 adopts a carbon nanotube field emission neutralizer that does not require propellants, and has a diameter of 15 mm. The carbon nanotube emitter 15 is used to emit electrons, and the electrons can be extracted by applying a certain voltage to the neutralizer grid 14 . The power processing unit 3 is co...

Embodiment 2

[0095] In the non-toxic dual-mode micro propulsion system of the present invention, the thruster body 1 and the neutralizer 2 adopt modules with the same structure. The neutralization shell 16 of the neutralizer 2 has a diameter of 20mm, and adopts a 180kHz frequency neutralization ultrasonic vibration unit 17 with a diameter of 15mm, a neutralization grid 28 with a diameter of 15mm, and 320 cones with a top diameter of 2μm and a bottom diameter of 30μm distributed in the center Grid hole 29, the distance between grid hole 29 is 0.13mm. The propellant 36 adopts EMI-Im (1-ethyl-3-methylimidazoline bis(trifluoromethylsulfonyl)imide) ionic liquid, the storage capacity is 30ml, and passes through. Neutralizing housing 16 is made of polyether ether ketone. The neutralization transport element 19 is made of fibers. The neutralization electrostatic acceleration unit 18 is composed of a neutralization extraction pole 20 and a neutralization acceleration pole 21 .

[0096] Thruster ...

Embodiment 3

[0100] In the non-toxic dual-mode micro-propulsion system of the present invention, the electrostatic acceleration grid of the thruster body 1 only adopts a jetting extraction pole 8, and the jetting extraction pole 8 also takes into account the charged particle acceleration function, and the corresponding power processing unit 3 is composed of jetting ultrasonic drive power supply 10, jet Draw out power supply 9 and neutralizer power supply 11 lamp modules to form. When the thruster body 1 works in the electrostatic spraying mode, the ejection pole 8 is negatively charged, and the sprayed particles are positively charged droplets, and the droplets are ejected by the electrostatic field formed by the ejection pole 8 and the spray grid 26 to generate thrust . Neutralizer 2 ejects neutralization stream 33 for neutralization. According to the difference in the voltage of the ejection electrode 8, the ejection speed of the body beam is different. The higher the voltage, the faste...

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Abstract

The invention provides a non-toxic dual mode micropropulsion system and a working method thereof. The system comprises a thruster body, a neutralizer and a power processing unit; the power processingunit is connected with the neutralizer and the thruster body separately; the thruster body comprises a spray shell which is divided into a spray shell emission cavity and a spray shell storage cavitywhich are mutually independent; a spray ultrasonic vibration unit is arranged on the lower portion of the spray shell emission cavity; a spray electrostatic acceleration unit is arranged on the upperportion of the spray shell emission cavity; one end of a spray transport element stretches into the spray shell storage cavity, the other end of the spray transport element stretches into the spray shell emission cavity from the interior of the spray shell storage cavity and is connected with the spray ultrasonic vibration unit. The system has the following advantages that thrust ranges from microNewton to milliNewton, the specific impulse ranges from seconds to hundreds of seconds, the power ranged from a value smaller than one watt to multiple watt, the system can work in the two modes of ultrasonic spray and electrostatic spray, and the thrust ranging from micro Newton to milliNewton can be adjusted.

Description

technical field [0001] The invention relates to a non-toxic micro-propulsion system with a thrust of micro-newton to millineww and a power of less than 1 watt to several watts for a pina satellite, especially a non-toxic dual-mode micro-propulsion system and a working method thereof. Background technique [0002] The number of Pina satellites with a launch weight of 1 kg to 10 kg has increased rapidly in recent years, and their performance has continued to improve. However, most of the Pina satellites do not have a propulsion system, resulting in poor space maneuverability, short life, and greatly limited functions and performance. At the end of its lifespan, it cannot de-orbit and become space junk, which is not conducive to the space environment. [0003] The power of Pina satellites is generally in the order of watts, and the thrust required for tasks such as attitude control and orbit transfer is generally in the order of micronewtons to millinenewtons. [0004] At pres...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/40
CPCB64G1/409
Inventor 杭观荣李林张岩王仲远康小录康小明
Owner SHANGHAI INST OF SPACE PROPULSION
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