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Hollow cathode thruster for cubesats

A cube satellite, hollow cathode technology, applied in thrust reverser, using plasma, machine/engine, etc., can solve the problems of complex structure of electric propulsion system, and achieve the effect of simple structure, high temperature of the launcher, and low power consumption

Active Publication Date: 2017-11-24
HARBIN INST OF TECH
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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 solve the problem that the structure of the existing electric propulsion system is complex and cannot be directly miniaturized to 1U, thereby providing a hollow cathode thruster for a cube satellite

Method used

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  • Hollow cathode thruster for cubesats
  • Hollow cathode thruster for cubesats
  • Hollow cathode thruster for cubesats

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specific Embodiment approach 1

[0028] Specific implementation mode one: combine figure 1 Describe this embodiment in detail, the hollow cathode thruster for CubeSat described in this embodiment, the hollow cathode thruster includes base 1, vent tube, emitter 4, anode tube 5 and anode plate 6;

[0029] The ventilation tube includes a first ventilation tube 2 and a second ventilation tube 3; the first ventilation tube 2 passes through the base 1 and communicates with the second ventilation tube 3, the anode tube 5 is set outside the second ventilation tube 3, and one end of the anode tube 5 and one end of the second air pipe 3 are fixed on the base 1, the other end of the anode pipe 5 is embedded with an anode plate 6, the center of the anode plate 6 is provided with a throttle hole 6-1, and the other end of the second air pipe 3 is embedded The inherent emitter 4; the emitter 4 is connected to the negative pole of the power supply, and the anode plate 6 is connected to the positive pole of the power supply; ...

specific Embodiment approach 2

[0033] Specific implementation mode two: combination figure 2 and image 3 This embodiment is described in detail. This embodiment is a further description of the hollow cathode thruster for a cube satellite described in the first embodiment. The titanium silicide-copper conductive material and the first ventilation pipe 2 are connected to the negative pole of the power supply. The anode plate 6 is connected to the positive pole of the power supply through the stainless steel material on the side wall of the anode tube 5 .

[0034] The discharge of the hollow cathode thruster needs to connect the emitter 4 to the negative pole of the power supply, so a conductive material is connected between the first vent pipe 2 and the emitter. Since the electronegative gas has strong oxidation after decomposition, the conductive material is pure titanium silicide carbon-copper conductive material with good oxidation resistance, and the first ventilation pipe 2 made of stainless steel is...

specific Embodiment approach 3

[0035] Specific implementation mode three: combination Figure 4 to Figure 6 This embodiment is described in detail. This embodiment is a further description of the hollow cathode thruster for a cube satellite described in the second embodiment. In this embodiment, the pure titanium silicide carbon-copper conductive material is in the shape of a filament or a strip or cylindrical.

[0036] A pure titanium silicide carbon-copper conductive material with good oxidation resistance is used to conduct electricity between the first air pipe 2 and the emitter, and the conductive material can adopt three shapes. The first is filamentous, called conductive filament, such as Figure 4 As shown, this kind of scheme can save materials, and at the same time, it can conduct between the first vent pipe 2 and the emitter; the second one is a strip, called a conductive strip, such as Figure 5 As shown, this scheme can reduce the current co-current density, prevent fusing, and increase the s...

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Abstract

The invention discloses a hollow cathode thruster for cubesats, and relates to the field of thrusters. In order to solve the problems that an existing electric propulsion system is complex in structure and cannot be miniaturized onto 1U directly, discharging gas and electronegative gas are connected into a hollow cathode ventilation pipe. According to the hollow cathode thruster, the electronegative gas is used as a main propulsive working medium, the discharging gas is used for discharging in the hollow cathode thruster to form a high-density plasma environment, the electronegative gas can be decomposed through electrons to form negative ions, the negative ions are accelerated outwards under the potential effect inside the hollow cathode thruster, and accordingly a high specific impulse propulsion effect can be achieved. The hollow cathode thruster is suitable for the cubesats.

Description

technical field [0001] The invention relates to the field of thrusters. Background technique [0002] In the classification of small satellites, nano-satellites have a mass of 1 to 10 kg, and pico-satellites have a mass of 0.1 to 1 kg. CubeSat (CubeSat) is a new concept pico-satellite specification, its mass is about 1kg, and its structural size is a cube of 10cm×10cm×10cm, also known as 1U (a CubeSat unit). Several CubeSat units are assembled into nanosatellites. CubeSat has the characteristics of simple structure, small size, light weight, low cost, short development cycle and low launch cost, etc. It has broad development prospects in space demonstration and verification and the use of CubeSat network to improve the spatial and temporal resolution of earth observation. . [0003] At present, the attitude control of CubeSat in orbit uses miniature three-axis strong magnetometer, miniature momentum wheel and magnetic torquer to form an attitude control system to complete...

Claims

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Application Information

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IPC IPC(8): F03H1/00
CPCF03H1/0081
Inventor 宁中喜刘晨光朱悉铭于达仁王福峰韩星
Owner HARBIN INST OF TECH
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