CN112145385A - High-thrust magnetic confinement electrostatic ion thruster - Google Patents
High-thrust magnetic confinement electrostatic ion thruster Download PDFInfo
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- CN112145385A CN112145385A CN202011039799.7A CN202011039799A CN112145385A CN 112145385 A CN112145385 A CN 112145385A CN 202011039799 A CN202011039799 A CN 202011039799A CN 112145385 A CN112145385 A CN 112145385A
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- electrode
- electrode ring
- ion
- electrostatic
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0037—Electrostatic ion thrusters
- F03H1/0056—Electrostatic ion thrusters with an acceleration grid and an applied magnetic field
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- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Plasma Technology (AREA)
Abstract
The invention discloses a high-thrust magnetic confinement electrostatic ion thruster, which comprises: protection casing, working medium bin, ion source, fixed plate, accelerator, electron gun and power, the working medium bin install in protection casing's the outside, the ion source set up in the front end of working medium bin, the fixed plate fixed set up in the protection casing, the accelerator include along a plurality of electrode ring unit groups that protection casing's length direction interval set up and with the magnetic ring that electrode ring unit group one-to-one set up, every electrode ring unit group includes two electrode rings, the magnetic ring set up in the inboard of electrode ring unit group and with the coaxial setting of electrode ring, the electron gun is fixed in protection casing's rear portion, the power is ion source, electron gun power supply, still along protection casing by preceding backward direction, for the electrode ring provides the voltage of arithmetic degressive series. The large-thrust magnetic confinement electrostatic ion thruster is reasonable in structure, easy to machine and capable of greatly improving thrust.
Description
Technical Field
The invention relates to the technical field of long-life deep space detectors, satellite motion systems and spacecraft high-thrust space propulsion, in particular to a high-thrust magnetic confinement electrostatic ion thruster.
Background
The electrostatic ion thruster is expected to be the most suitable electric thruster for detecting long-distance interstellar travel in deep space due to the advantages of high specific impulse, high efficiency, long service life and the like. The conventional electrostatic ion thruster accelerates the ion beam through the grid, and has the following problems: 1. the ion beam density is lower due to the limitation of electrostatic field energy, and then the thrust density is lower; 2. the aperture of the grid is millimeter magnitude, which puts more rigorous requirements on production and processing; 3. the grid acceleration working condition is not near the optimal focusing beam density, the grid etching phenomenon can occur to influence the electric field distribution in the grid, and the service life of the grid is further reduced; 4. the distance between the extraction grid and the acceleration grid is about 5mm, and in order to avoid discharge ignition between the extraction grid and the acceleration grid, the acceleration voltage cannot be too large, so that the specific impulse of the thruster is limited; 5. the ion beam is accelerated only once, considering that the beam traversing in the gate hole may impact the etched gate plate.
Therefore, how to further improve the thrust and specific impulse of the thruster and maintain the stability of the electric field distribution becomes an urgent problem to be solved in the field.
Disclosure of Invention
In view of this, the present invention provides a large thrust magnetic confinement electrostatic ion thruster to solve the problems of small thrust density, complex production and processing, poor electric field distribution stability, etc. of the conventional electrostatic ion thruster.
The technical scheme provided by the invention is as follows: a high thrust magnetic confinement electrostatic ion thruster, comprising: protective housing, working medium bin, ion source, fixed plate, accelerator, electron gun and power, wherein, the working medium bin install in protective housing's the outside for leading-in with the working medium the ion source, the ion source set up in the front end of working medium bin for with leading-in working medium ionization one-tenth ionic state and spray into with the ion beam form in the accelerator, the fixed plate is fixed set up in the protective housing, be used for fixing the accelerator, the accelerator include along protective housing's length direction interval set up a plurality of electrode ring unit groups and with the magnetic ring that the electrode ring unit group one-to-one set up, every electrode ring unit group includes two electrode rings that set up along protective housing's length direction relatively, the magnetic ring sets up in electrode ring unit group's inboard and with the coaxial setting of electrode ring, the electron gun is fixed in protective housing's rear portion, the power supply is connected with the ion source, the electrode ring and the electron gun to supply power to the ion source and the electron gun, the voltage with the arithmetic progression is provided for the electrode ring along the front-to-back direction of the protective shell, the electrode ring generates a unidirectional electrostatic field in the accelerator to accelerate the ion beam and generate thrust, and the magnetic ring provides a magnetic field in the same direction as the electrostatic field to restrain the ion beam.
Preferably, the fixed plate is provided with a plurality ofly along the circumference interval of protective housing, and wherein, every fixed plate all is the rectangle, and sets up along protective housing's length direction.
Preferably, the electrode rings are in a hollow round table shape, and the large-diameter ends of the two electrode rings of each electrode ring unit group are arranged oppositely.
Further preferably, the included angle between the generatrix of the electrode ring and the axis thereof is 45 °.
It is further preferred that the outer portions of the electrode rings are wrapped with an insulating material to prevent arcing between adjacent electrode rings.
Preferably, the fixing plate is provided with a clamping groove matched with the electrode ring, and the electrode ring is fixed in the clamping groove.
Preferably, the magnetic ring is a permanent magnet.
Further preferably, the working medium storage tank is connected with the ion source through a conduit.
The invention provides a high-thrust magnetic confinement electrostatic ion thruster, which replaces an original grid accelerating system with an electrostatic accelerating system which is accelerated by an electrode ring and restrained by a magnetic ring, and solves the problem that the density of an ion beam is lower and the density of a thrust is lower due to the fact that an accelerating section consisting of an extraction grid and an accelerating grid in the grid accelerating system is limited by the energy of an electrostatic field. 1. The higher density ion beam is restrained, and higher thrust density is realized; 2. ion beam restraint is in the low-intensity magnetic field region, avoids ion beam striking to the inside equipment that causes of accelerator to damage, leads to the life-span to shorten, and in addition, this application adopts the electrode ring, compares in the electrode ring, and the size of ion beam can be ignored, and this means even take place the sculpture can not influence electric field distribution yet, then can maintain electric field distribution's stability.
The high-thrust magnetic confinement electrostatic ion thruster provided by the invention is reasonable in structure and easy to process, can greatly improve thrust, can generate a unidirectional uniform electrostatic field in an accelerator, and simultaneously provides a magnetic field in the same direction as the electrostatic field, so that an ion beam with higher density can be confined by the magnetic field, and the ion beam is accelerated to MV magnitude by using the electrostatic field, and generates ultra-high thrust in space flight.
Drawings
The invention is described in further detail below with reference to the following figures and embodiments:
fig. 1 is a cross-sectional view of a high thrust magnetic confinement electrostatic ion thruster provided by the present invention;
FIG. 2 is a front view of FIG. 1;
FIG. 3 is a vertical axial cross-sectional view of a high thrust magnetic confinement electrostatic ion thruster provided by the present invention;
fig. 4 is a schematic view of the overall structure of the high thrust magnetic confinement electrostatic ion thruster provided by the invention.
Detailed Description
The invention will be further explained with reference to specific embodiments, without limiting the invention.
As shown in fig. 1 to 4, the present invention provides a high thrust magnetic confinement electrostatic ion thruster, including: protection casing 1, working medium bin 2, ion source 3, fixed plate 4, accelerator, electron gun 6 and power 7, wherein, protection casing is used for protecting the internal plant to avoid the striking of space energetic particle, working medium bin 2 install in protection casing 1's the outside for leading into working medium (like argon) ion source 3, ion source 3 set up in working medium bin 2's front end for ionizing leading-in working medium into the ionic state and spray into with the ion beam form in the accelerator, fixed plate 4 is fixed set up in protection casing 1, be used for fixing the accelerator, the accelerator include along the length direction interval of protection casing 1 a plurality of electrode ring unit groups 51 and with the magnetic ring 52 that electrode ring unit group 51 one-to-one set up, every electrode ring unit group 51 includes two electrode rings 511 that set up along the length direction of protection casing 1 relatively, the magnetic ring 52 is arranged on the inner side of the electrode ring unit group 51 and is coaxially arranged with the electrode ring 511, the electron gun 6 is fixed at the rear part of the protective shell 1 and is used for emitting electron beams to neutralize ion beams leaving the thruster, the power supply 7 is connected with the ion source 3, the electrode ring 511 and the electron gun 6 to supply power to the ion source 3 and the electron gun 6, and the voltage with an arithmetic decreasing series is provided for the electrode ring 511 along the front-to-rear direction of the protective shell 1, the electrode ring 511 generates a unidirectional and more uniform electrostatic field in the accelerator to accelerate the ion beams and generate thrust, and the magnetic ring provides a magnetic field in the same direction as the electrostatic field to restrain the ion beams and prevent the ion beams from diffusing in the accelerator to impact and etch internal facilities.
This big thrust magnetic confinement static ion thrustor can make the ion thrustor obtain bigger thrust through improving accelerating voltage and through the ion beam of the great density of strong magnetic field restraint, can realize the quick start and the braking of spacecraft in the space, specifically: can produce the even strong electrostatic field of one-way in the accelerator through applying arithmetic progression voltage, adopt multistage acceleration mode, can improve acceleration voltage, and then improve specific impulse and thrust, can restraint higher density ion beam through magnetic field, and then improve thrust density, wherein, the magnetic field intensity of magnetic field is along radial crescent (being the magnetic field intensity of axle center position weakest), and this structure can reach following effect: 1. the higher density ion beam is restrained, and higher thrust density is realized; 2. ion beam restraint is in the low-intensity magnetic field region, avoids ion beam striking to the inside equipment that causes of accelerator to damage, leads to the life-span to shorten, and in addition, this application adopts the electrode ring, compares in the electrode ring, and the size of ion beam can be ignored, and this means even take place the sculpture can not influence electric field distribution yet, then can maintain electric field distribution's stability.
As an improvement of the technical solution, the fixing plates 4 are arranged at intervals along the circumferential direction of the protective shell 1, wherein each fixing plate 4 is rectangular and arranged along the length direction of the protective shell 1, and fig. 3 shows 4 embodiments of the fixing plates.
As an improvement of the technical solution, as shown in fig. 1 and 2, the electrode ring 511 is in the shape of a hollow circular truncated cone, and the large-diameter ends of the two electrode rings 511 of each electrode ring unit group 51 are arranged opposite to each other.
As an improvement of the technical scheme, as shown in fig. 1 and 2, an included angle between a generatrix of the electrode ring 511 and an axis thereof is 45 °, and the included angle is matched with an arithmetic progression voltage to generate a unidirectional uniform electric field, so that the effect is obviously different from other angles.
As a technical improvement, the outer part of the electrode ring 511 is wrapped with an insulating material to avoid electric arcs between adjacent electrode rings.
As an improvement of the technical solution, a clamping groove (not labeled in the figure) matched with the electrode ring 511 is arranged on the fixing plate 4, and the electrode ring 511 is fixed in the clamping groove.
As an improvement of the technical scheme, the magnetic ring 52 is a permanent magnet and provides a unidirectional magnetic field for the interior of the accelerator.
As a technical improvement, as shown in fig. 1, 2 and 4, the working medium storage tank 2 is connected with the ion source 3 through a conduit 8.
The embodiments of the present invention have been written in a progressive manner with emphasis placed on the differences between the various embodiments, and similar elements may be found in relation to each other.
The embodiments of the present invention have been described in detail with reference to the drawings, but the present invention is not limited to the above embodiments, and various changes can be made within the knowledge of those skilled in the art without departing from the gist of the present invention.
Claims (8)
1. A high thrust magnetic confinement electrostatic ion thruster is characterized by comprising: protection casing (1), working medium bin (2), ion source (3), fixed plate (4), accelerator, electron gun (6) and power (7), wherein, working medium bin (2) install in the outside of protection casing (1) is used for leading-in with working medium ion source (3), ion source (3) set up in the front end of working medium bin (2) is used for ionizing leading-in working medium into the ionic state and jet into with the ion beam form in the accelerator, fixed plate (4) fixed set up in protection casing (1) is used for fixing the accelerator, the accelerator include along the length direction interval of protection casing (1) a plurality of electrode ring unit groups (51) that set up and with magnetic ring (52) that electrode ring unit group (51) one-to-one set up, every electrode ring unit group (51) include two electrode rings (511) that set up along the length direction of protection casing (1) relatively, the ion source is characterized in that the magnetic ring (52) is arranged on the inner side of the electrode ring unit group (51) and is coaxially arranged with the electrode ring (511), the electron gun (6) is fixed at the rear part of the protective shell (1) and used for emitting electron beams to neutralize ion beams leaving the thruster, the power supply (7) is connected with the ion source (3), the electrode ring (511) and the electron gun (6) to supply power to the ion source (3) and the electron gun (6), voltage in an arithmetic decreasing series is provided for the electrode ring (511) along the front-to-rear direction of the protective shell (1), the electrode ring (511) generates a unidirectional electrostatic field in an accelerator and is used for accelerating the ion beams and generating thrust, and the magnetic ring provides a magnetic field in the same direction as the electrostatic field and is used for restraining the ion beams.
2. The high thrust magnetic confinement electrostatic ion thruster of claim 1, wherein: the fixed plates (4) are arranged along the circumferential direction of the protective shell (1) at intervals, wherein each fixed plate (4) is rectangular and is arranged along the length direction of the protective shell (1).
3. The high thrust magnetic confinement electrostatic ion thruster of claim 1, wherein: the electrode rings (511) are in the shape of hollow truncated cones, and the large-diameter ends of the two electrode rings (511) of each electrode ring unit group (51) are arranged oppositely.
4. The high thrust magnetic confinement electrostatic ion thruster of claim 3, wherein: the included angle between the generatrix of the electrode ring (511) and the axis thereof is 45 degrees.
5. The high thrust magnetic confinement electrostatic ion thruster of claim 1, wherein: the outer portion of the electrode rings (511) is covered with an insulating material to prevent arcing between adjacent electrode rings.
6. The high thrust magnetic confinement electrostatic ion thruster of claim 1, wherein: the electrode fixing device is characterized in that a clamping groove matched with the electrode ring (511) is formed in the fixing plate (4), and the electrode ring (511) is fixed in the clamping groove.
7. The high thrust magnetic confinement electrostatic ion thruster of claim 1, wherein: the magnetic ring (52) is a permanent magnet.
8. The high thrust magnetic confinement electrostatic ion thruster of claim 1, wherein: the working medium storage tank (2) is connected with the ion source (3) through a conduit (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011039799.7A CN112145385A (en) | 2020-09-28 | 2020-09-28 | High-thrust magnetic confinement electrostatic ion thruster |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011039799.7A CN112145385A (en) | 2020-09-28 | 2020-09-28 | High-thrust magnetic confinement electrostatic ion thruster |
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| CN112145385A true CN112145385A (en) | 2020-12-29 |
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| CN202011039799.7A Pending CN112145385A (en) | 2020-09-28 | 2020-09-28 | High-thrust magnetic confinement electrostatic ion thruster |
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Citations (7)
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|---|---|---|---|---|
| CN1675730A (en) * | 2002-06-21 | 2005-09-28 | 克洛诺斯先进技术股份有限公司 | Method for electrostatic fluid acceleration control of a fluid flow |
| WO2011151636A1 (en) * | 2010-06-01 | 2011-12-08 | Astrium Limited | Plasma thrusters |
| CN102903595A (en) * | 2011-07-29 | 2013-01-30 | 北京普析通用仪器有限责任公司 | Atmosphere interface ion source and mass spectrometer |
| WO2015031447A1 (en) * | 2013-08-27 | 2015-03-05 | The Regents Of The University Of Michigan | Converging/diverging magnetic nozzle |
| CN104583589A (en) * | 2012-06-21 | 2015-04-29 | 萨里大学 | Ion accelerators |
| CN110206700A (en) * | 2019-04-30 | 2019-09-06 | 大连理工大学 | A kind of electrostatic ionic thruster |
| CN110925157A (en) * | 2019-12-11 | 2020-03-27 | 大连理工大学 | Electrostatic plasma thruster |
-
2020
- 2020-09-28 CN CN202011039799.7A patent/CN112145385A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1675730A (en) * | 2002-06-21 | 2005-09-28 | 克洛诺斯先进技术股份有限公司 | Method for electrostatic fluid acceleration control of a fluid flow |
| WO2011151636A1 (en) * | 2010-06-01 | 2011-12-08 | Astrium Limited | Plasma thrusters |
| CN102903595A (en) * | 2011-07-29 | 2013-01-30 | 北京普析通用仪器有限责任公司 | Atmosphere interface ion source and mass spectrometer |
| CN104583589A (en) * | 2012-06-21 | 2015-04-29 | 萨里大学 | Ion accelerators |
| WO2015031447A1 (en) * | 2013-08-27 | 2015-03-05 | The Regents Of The University Of Michigan | Converging/diverging magnetic nozzle |
| CN110206700A (en) * | 2019-04-30 | 2019-09-06 | 大连理工大学 | A kind of electrostatic ionic thruster |
| CN110925157A (en) * | 2019-12-11 | 2020-03-27 | 大连理工大学 | Electrostatic plasma thruster |
Non-Patent Citations (1)
| Title |
|---|
| 沙占友: "《新型数字电压表原理与应用》", 31 May 1995, 国防工业出版社 * |
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Application publication date: 20201229 |
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