CN109896050B - Electric control vector thrust electric propeller - Google Patents
Electric control vector thrust electric propeller Download PDFInfo
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- CN109896050B CN109896050B CN201910210393.1A CN201910210393A CN109896050B CN 109896050 B CN109896050 B CN 109896050B CN 201910210393 A CN201910210393 A CN 201910210393A CN 109896050 B CN109896050 B CN 109896050B
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Abstract
The invention provides an electric control vector thrust electric propeller, which comprises a casing, an ion source, a mounting groove, an X-direction deflection electrode, a Y-direction deflection electrode and an induction electrode, wherein the casing is provided with a plurality of grooves; the casing comprises a concave cavity and four upright posts, and mounting grooves are formed in the wall surfaces of the upright posts and the concave cavity; the ion source is arranged in the cavity of the casing, and can be a liquid ion source, a liquid metal ion source, a gas ion source and a solid ion source; the X-direction deflection electrodes form a pair by two electrodes, and a plurality of pairs of X-direction deflection electrodes can be continuously added in the axial direction according to the requirement; the Y-direction deflection electrodes form a pair by two electrodes, and a plurality of pairs of Y-direction deflection electrodes can be continuously added in the axial direction according to the requirement; the invention can realize vector thrust output by simultaneously adjusting the electric potentials of the two pairs of deflection electrodes, thereby completing more complex attitude control tasks or reducing the number of required thrusters; the invention can also realize the control of the plume divergence angle, thereby reducing the non-axial thrust loss of the propeller and improving the efficiency of the propeller.
Description
Technical Field
The invention belongs to the field of aerospace propulsion, and relates to an electric control vector thrust electric propeller.
Background
An electric thruster is a propulsion device that generates charged particles from an ion source and generates thrust by accelerating the charged particles. The electric propeller is widely used for spacecraft orbit maneuvering, attitude control and the like. At present, ion sources commonly used by electric propulsion devices include ionic liquid ion sources, liquid metal ion sources, gas ion sources and the like. Most of the existing electric propulsion devices can only generate thrust in one direction, have no vector thrust capability, and need to be provided with a plurality of pairs of propellers for realizing the three-axis maneuvering of a spacecraft; the electric propeller's emission plume typically has a large divergence angle, resulting in non-axial thrust losses. In order to improve the adjustability of the electric thruster, increase the control capability of the spacecraft, realize the control of the plume divergence angle and reduce the thrust loss, the invention provides the electric control vector thrust electric thruster.
Disclosure of Invention
Technical problem to be solved
The invention provides an electric control vector thrust electric propeller, aiming at solving the problems that an electric propeller does not have vector control capability and non-axial thrust loss is caused by a divergence angle. The invention realizes the two-dimensional deflection direction control of charged particles by two pairs of deflection electrodes, and can realize the control of the direction and the magnitude of the thrust by matching with a corresponding control algorithm, thereby realizing the vector thrust control; when only axial thrust is needed, the non-axial thrust loss can be reduced and the efficiency of the propeller can be improved by controlling the divergence angle of the plume.
Technical scheme
An electric control vector thrust electric propeller is characterized by comprising a casing (1), an ion source (2), a mounting groove (3), an X-direction deflection electrode (4), a Y-direction deflection electrode (5) and an induction electrode (6); the casing (1) comprises a cavity (7) and four columns (8), and mounting grooves (3) are formed in the columns (8) and the wall surface (9) of the cavity; the ion source (2) is arranged in the casing (1), and the induction electrode (6) is inserted into the casing (1) through the mounting groove (3); the induction electrode (6) and the ion source (2) form a potential difference required for generating charged particles; the X-direction deflection electrode (4) and the Y-direction deflection electrode (5) are arranged in the mounting grooves (3) on the upright post (8) and the wall surface (9) of the cavity, the X-direction deflection electrode (4) is formed by two electrodes and is oppositely arranged on the wall surface (9) of the cavity, and the Y-direction deflection electrode (5) is formed by two electrodes and is oppositely arranged on the wall surface (9) of the cavity.
The electric control vector thrust electric propeller is characterized in that an ion source (2) is arranged in a concave cavity (7) of a casing (1), and the ion source (2) can be a liquid ion source, a liquid metal ion source, a gas ion source and a solid ion source.
The electric control vector thrust electric thruster is characterized in that the X-direction deflection electrode (4) is formed into a pair by two electrodes, and a plurality of pairs of X-direction deflection electrodes (4) can be continuously added in the axial direction according to the requirement.
The electric control vector thrust electric thruster is characterized in that an X-direction deflection electrode (4) is installed in an installation groove (3) or is fixedly installed in an adhesion mode, a screw mode and the like.
The electric control vector thrust electric thruster is characterized in that the Y-direction deflection electrodes (5) form a pair by two electrodes, and a plurality of pairs of Y-direction deflection electrodes (5) can be continuously added in the axial direction according to the requirement.
The electric control vector thrust electric thruster is characterized in that a Y-direction deflection electrode (5) is installed in the installation groove (3) or is fixedly installed in a bonding mode, a screw mode and the like.
The electric control vector thrust electric thruster is characterized in that the induction electrode (6) is installed through the installation groove (3).
Advantageous effects
Compared with the common electric thruster, the invention can realize the control of the thrust magnitude and direction by controlling the deflection direction of the charged particles, thereby realizing the vector thrust control. The vector thrust control electric thruster can complete more complex attitude control tasks or reduce the number of required thrusters.
Compared with the common electric propeller, the invention can control the plume divergence angle, thereby reducing the non-axial thrust loss of the propeller and improving the efficiency of the propeller.
Drawings
FIG. 1: axial section view of the invention
FIG. 2: machine case axonometric drawing
In the figure, (1) a casing, (2) an ion source, (3) a mounting groove, (4) an X-direction deflection electrode, (5) a Y-direction deflection electrode, (6) an induction electrode, (7) a cavity, (8) a vertical column and (9) a cavity wall surface.
Detailed Description
The invention will now be further described with reference to the following examples and drawings:
as shown in fig. 1, the invention provides an electric control vector thrust electric thruster, which comprises a casing (1), an ion source (2), a mounting groove (3), an X-direction deflection electrode (4), a Y-direction deflection electrode (5) and an induction electrode (6); the casing (1) comprises a cavity (7) and four columns (8), and mounting grooves (3) are formed in the columns (8) and the wall surface (9) of the cavity.
When the thrust direction is required to deflect in the X direction, the voltages of the two X-direction deflection electrodes (4) are adjusted, for example, positive charge particles are generated by the ion source, a lower positive potential is applied to the electrode on the side needing to deflect to prevent the charged particles from colliding with the deflection electrodes, and a higher positive potential required by deflection is applied to the electrode on the side needing to deflect to realize the deflection of the charged particles; when the thrust is needed to deflect in the Y direction, the two Y-direction deflection electrodes (5) are adjusted in the same way; when the thrust is required to deflect in other directions, the X-direction deflection electrode (4) and the Y-direction deflection electrode (5) are adjusted simultaneously through a certain algorithm.
When the plume divergence angle needs to be controlled, the electric potentials with the same magnitude are simultaneously added to the two pairs of X-direction deflection electrodes (4) and Y-direction deflection electrodes (5), so that the divergence angle can be controlled, and the magnitude of the added electric potential is obtained by the combined action of controlling the magnitude of the front divergence angle and controlling the rear desired divergence angle.
Claims (7)
1. An electric control vector thrust electric propeller is characterized by comprising a casing (1), an ion source (2), a mounting groove (3), an X-direction deflection electrode (4), a Y-direction deflection electrode (5) and an induction electrode (6); the casing (1) comprises a cavity (7) and four columns (8), and mounting grooves (3) are formed in the columns (8) and the wall surface (9) of the cavity; the ion source (2) is arranged inside the casing (1), and the induction electrode (6) is inserted into the casing (1) through the mounting groove (3); the induction electrode (6) and the ion source (2) form a potential difference required for generating charged particles; an X-direction deflection electrode (4) and a Y-direction deflection electrode (5) are arranged in the mounting grooves (3) on the vertical column (8) and the wall surface (9) of the concave cavity, the X-direction deflection electrode (4) is formed by two electrodes in a pair and is oppositely arranged on the wall surface (9) of the concave cavity, and the Y-direction deflection electrode (5) is formed by two electrodes in a pair and is oppositely arranged on the wall surface (9) of the concave cavity.
2. An electrically controlled vector thrust electric thruster according to claim 1, characterized in that the ion source (2) is mounted in the cavity (7) of the casing (1), the ion source (2) being a liquid ion source, a liquid metal ion source, a gas ion source, a solid ion source.
3. An electric control vector thrust electric thruster according to claim 1, characterized in that the X-direction deflecting electrodes (4) are formed as a pair by two electrodes, and a plurality of pairs of X-direction deflecting electrodes (4) can be added in the axial direction as required.
4. An electric control vector thrust electric thruster according to claim 1, characterized in that the X-direction deflecting electrode (4) is mounted in the mounting groove (3) or fixed by means of bonding, screws, etc.
5. An electric control vector thrust electric thruster as claimed in claim 1, characterized in that the Y-deflection electrodes (5) are formed as a pair by two electrodes, and a plurality of pairs of Y-deflection electrodes (5) can be added in the axial direction as required.
6. An electric control vector thrust electric thruster according to claim 1, characterized in that the Y-deflection electrode (5) is mounted in the mounting groove (3) or fixed by means of bonding, screws, etc.
7. An electric control vector thrust electric thruster according to claim 1, characterized in that the induction electrodes (6) are mounted through mounting slots (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910210393.1A CN109896050B (en) | 2019-03-20 | 2019-03-20 | Electric control vector thrust electric propeller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910210393.1A CN109896050B (en) | 2019-03-20 | 2019-03-20 | Electric control vector thrust electric propeller |
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| Publication Number | Publication Date |
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| CN109896050A CN109896050A (en) | 2019-06-18 |
| CN109896050B true CN109896050B (en) | 2022-05-20 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910210393.1A Active CN109896050B (en) | 2019-03-20 | 2019-03-20 | Electric control vector thrust electric propeller |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110230582B (en) * | 2019-07-16 | 2021-01-26 | 四川牧天移星科技有限公司 | Ionic liquid electric propeller structure |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB465144A (en) * | 1935-11-02 | 1937-05-03 | Cabot Seaton Bull | Improvements in or relating to electron discharge devices |
| JPH11230024A (en) * | 1998-02-19 | 1999-08-24 | Mitsubishi Electric Corp | Liquid metal ion thruster |
| WO2015031234A1 (en) * | 2013-08-27 | 2015-03-05 | Inspirotec Llc | Electrokinetic device for capturing assayable agents in a dielectric fluid utilizing removable electrodes |
| CN108872000A (en) * | 2018-05-11 | 2018-11-23 | 北京卫星环境工程研究所 | The measuring device of electric propulsion plume sedimentary effect based on electric field deflection |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3014082B1 (en) * | 2013-11-29 | 2016-01-01 | Thales Sa | TUYER SYSTEM AND METHOD FOR ORBIT AND ATTITUDE CONTROL FOR GEOSTATIONARY SATELLITE |
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2019
- 2019-03-20 CN CN201910210393.1A patent/CN109896050B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB465144A (en) * | 1935-11-02 | 1937-05-03 | Cabot Seaton Bull | Improvements in or relating to electron discharge devices |
| JPH11230024A (en) * | 1998-02-19 | 1999-08-24 | Mitsubishi Electric Corp | Liquid metal ion thruster |
| WO2015031234A1 (en) * | 2013-08-27 | 2015-03-05 | Inspirotec Llc | Electrokinetic device for capturing assayable agents in a dielectric fluid utilizing removable electrodes |
| CN108872000A (en) * | 2018-05-11 | 2018-11-23 | 北京卫星环境工程研究所 | The measuring device of electric propulsion plume sedimentary effect based on electric field deflection |
Non-Patent Citations (2)
| Title |
|---|
| 基于全阶状态观测的无速度传感器矢量控制仿真研究;马继先等;《江苏科技大学学报(自然科学版)》;20141215(第06期);全文 * |
| 等离子体激励器在航空航天工程中的应用前景;SHANG Joseph J S等;《气体物理》;20180315(第02期);全文 * |
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| CN109896050A (en) | 2019-06-18 |
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