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Ionization Acceleration Integrated Space Debris Plasma Thruster

A technology of space debris and plasma, applied in the field of thrusters, can solve problems such as discontinuous plasma flow, large difference in ionization energy, grid electrode blockage, etc., to achieve improved control accuracy and stability, sufficient and uniform ionization, The effect of reducing the diffusivity

Active Publication Date: 2018-06-19
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Since the powder particles of space debris are much larger than conventional propellant (such as argon) particles, if the electrostatic thruster proposed in the paper "Debris Engine: APotential Thruster for Space Debris Removal" by Lei Lan et al. Space debris powder particles, grid electrode blockage and collision damage are more serious, resulting in low system efficiency and poor reliability. This defect can be compensated by the electromagnetic plasma thruster
However, due to the complex composition of space debris powder particles and the large difference in ionization energy, if a traditional electromagnetic plasma thruster is simply used, a longer ionization region is required to take into account the ionization of most particles, and the ionized powder The charge-to-mass ratio of the particles varies greatly, and the plasma flow ejected from the thruster is discontinuous, which is not conducive to the control of the acceleration process of the thruster, and will lead to a decrease in the control accuracy, stability and efficiency of the system
[0004] The root cause of the above-mentioned problems is that the ionization and acceleration process of the working fluid in the traditional electromagnetic plasma thruster are separated, forming two separate functional areas in space. Therefore, only the fully ionized working fluid can be released from the electric field. Gain energy and eject it at a speed dozens of times higher than the neutral airflow to generate thrust, which puts forward higher requirements on the uniformity of the propellant working medium, but as mentioned above, the composition of the space debris powder particle working medium Complex, traditional electromagnetic plasma propulsion does not match the working fluid conditions

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  • Ionization Acceleration Integrated Space Debris Plasma Thruster
  • Ionization Acceleration Integrated Space Debris Plasma Thruster
  • Ionization Acceleration Integrated Space Debris Plasma Thruster

Examples

Experimental program
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specific Embodiment approach 1

[0020] Specific implementation mode one: as figure 1 with Figure 4 As shown, an ionization acceleration integrated space debris plasma thruster includes: pulverizer 1, ball mill 2, powder particle charging system 3 and propeller 4;

[0021] The outlet of the pulverizer 1 is connected to the entrance of the ball mill 2, and the powder particle charging system 3 is fixed inside the outlet of the ball mill 2. The pulverizer 1 is used for primary pulverization of space debris, and the ball mill 2 is used for primary pulverization of space debris. Pulverized into submicron powder particles, the powder particle charging system 3 is used to positively charge the submicron powder particles;

[0022] The propeller 4 includes a No. 1 base 5, an anode 6, a No. 2 base 7, an outer yoke 8, a No. 1 outer magnetic pole 9, a No. 1 outer coil 10, a No. 2 outer magnetic pole 11, a No. 3 outer magnetic pole 12, a No. 2 outer coil 13, and a jacket Tube 14, inner casing 15, No. 1 inner magnetic ...

specific Embodiment approach 2

[0043] Specific implementation mode two: as shown in Figure 2 and image 3 As shown, the geometric structure parameters of the propeller 4 are: h=15mm, L=62mm, d=51mm; The cross-sectional size is 15mm×10mm, and the current passed is 500A, so the current density is 3.33A / mm 2 , within the insulation limits of copper conductors. Simulation in ANSYS Maxwell shows that the ionization acceleration integrated space debris plasma thruster of the present invention can generate the required magnetic field configuration. Compared with the traditional electromagnetic plasma thruster, there are more places on the inner wall of the four channels A "tangential" magnetic field with a strength of 0.023-0.031T (intensified radially from the centerline of the discharge channel to the inner wall), and the radial gradient of this magnetic field is 107Gass / cm, but the diameter near the exit of the discharge channel The configuration of the radial magnetic field is basically the same. The largest...

specific Embodiment approach 3

[0044] Specific implementation mode three: as figure 1 As shown, the axial positions of No. 1 inner coil 17 and No. 1 outer coil 10 relative to the propeller 4 main shaft 20 are the same, and the number of ampere turns and the cross section are the same. Align with the No. 2 outer magnetic pole 11 in the axial direction, so as to ensure that the tangential magnetic field generated at the inner wall of the discharge channel is symmetrical with respect to the center line of the channel, and the plasma in the discharge channel is confined in a narrow area; the No. 2 inner coil 19 The axial position of No. 2 outer coil 13 and propeller 4 main shaft 20 is the same, and the number of ampere turns and cross-section are the same. No. 3 inner magnetic pole 21 and No. 3 outer magnetic pole 12 are at the outlet of propeller 4 and the inner casing 15 of discharge channel and the outer casing 14 are respectively aligned to ensure that the magnetic field at the outlet of the discharge chann...

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Abstract

The invention discloses a space debris plasma propeller integrating ionization and acceleration. By means of the propeller, the working medium ionization process and the acceleration process in a traditional propeller are combined into a whole, so that the propeller is matched with the working medium condition of space debris powder particles. Each pulverizer of the propeller is connected with a ball mill, and each powder charging system is fixed into the ball mill; a first inner magnetic pole, a second inner magnetic pole and a third inner magnetic pole are fixed to a main shaft, and a first inner coil and a second inner coil are wound on the main shaft; an inner casing pipe and an outer casing pipe are fixed to a second base, and an outer magnet yoke is fixed to a first base; a first outer magnetic pole and a second outer magnetic pole are fixed to the outer casing pipe, a third magnetic pole is fixed to the outer magnet yoke, and a first outer coil and a second outer coil are wound on the outer casing pipe; positive poles are fixed to the second base, propellant injection pipelines of the positive poles penetrate through the first base and extend out of the propeller, the positive poles are located nearby the outer magnet yoke outside an outlet of the propeller, and the positive poles and a negative pole are all connected with a power source. By means of the space debris plasma propeller, space debris powder particles are ionized more sufficiently and uniformly, and the propeller is more stable, more compact and suitable for serving as a propeller of a spacecraft.

Description

technical field [0001] The invention relates to an ionization acceleration integrated space debris plasma thruster, which belongs to the technical field of thrusters. Background technique [0002] Space debris refers to non-functional objects distributed in the earth's orbit (usually at a height of 100km to 40,000km above the ground), including cosmic dust of natural origin and fragments and parts of man-made objects. With the progress of space activities, the mass of space debris has reached more than 3,000 tons, of which only the number of large debris (size>10cm) is about 19,000, and the number of small debris (size<1mm) is too many to count. These huge amounts of space debris can cause serious damage or even destruction to spacecraft. Therefore, it is particularly important to prevent the hazards of space debris. At present, the main development trend is from observation and avoidance of space debris to cleaning and on-orbit utilization. Among them, observation an...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F03H1/00
CPCF03H1/0081
Inventor 鄂鹏凌文斌毛傲华
Owner HARBIN INST OF TECH