CN105065221A - Novel four-cathode ion thruster - Google Patents
Novel four-cathode ion thruster Download PDFInfo
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- CN105065221A CN105065221A CN201510419168.0A CN201510419168A CN105065221A CN 105065221 A CN105065221 A CN 105065221A CN 201510419168 A CN201510419168 A CN 201510419168A CN 105065221 A CN105065221 A CN 105065221A
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Abstract
The invention discloses a four-cathode ion thruster. A main cathode of the ion thruster consists of four sub cathodes, wherein the four sub cathodes are distributed on an ion thruster rear wall and are symmetrical relative to the center of the rear wall; every two sub cathodes on the opposite corners form a group; when the ion thruster works, one group of sub cathodes work, and the other group of sub cathodes are in a shutdown state; and when one group of sub cathodes lose efficacy, the other group of sub cathodes are started. The two sub cathodes work simultaneously, so that the maximum emission current of the single main cathode is reduced, the service life of each single sub cathode is prolonged, and the service life of the thruster is prolonged; after one group of sub cathodes lose efficacy, the other group of sub cathodes are started, so that the service life of the ion thruster is greatly prolonged; the symmetrical sub cathodes work, so that the uniformity of ion distribution inside a discharge chamber, in particular in a grid upstream, is improved, the service life of a grid is prolonged, and the service life of the ion thruster is prolonged.
Description
Technical field
The present invention relates to spacecraft propulsion technical field, particularly relate to a kind of four cathode ion thrusters for space.
Background technique
Ion thruster is the magnetically confined plasma apparatus that a kind of electrostatic speeding-up ion produces thrust.Be mainly used in the fields such as the position maintenance of geosynchronous earth orbit satellite, orbit maneuver and the empty detection of deep space.Electric propulsion technology more becomes one of mark weighing related satellite platform advance.Life-span of ion thruster is one of important indicator weighing its performance, especially require in deep space exploration field the life-span of ion thruster reach 50000 hours even longer.Current single cathode ion thruster is difficult to meet some tasks very high to life requirements, as survey of deep space etc. in the life-span.In addition, for single negative electrode thruster, sub-negative electrode was once lose efficacy, and namely whole thruster lost efficacy.It is significant that design has long lifetime highly reliable ion thruster.The life-span of ion thruster needs to propose corresponding requirement to its sub-cathode life simultaneously.
Summary of the invention
In view of this, the invention provides a kind of four cathode ion thrusters for space, by increasing negative electrode number and making its rational deployment increase substantially the life-span of ion thruster.
In order to solve the problems of the technologies described above, the present invention is achieved in that
A kind of four cathode ion thrusters, the main cathode of described ion thruster is made up of four sub-negative electrodes; These four sub-negative electrodes to be arranged on ion thruster rear wall and to arrange relative to rear wall Central Symmetry;
Two the sub-negative electrodes being in diagonal angle are one group, during ion thruster work, and wherein one group of sub-negative electrode work, other one group of sub-negative electrode is in off-mode; When after one group of sub-cathode degradation, other one group of sub-negative electrode starts.
Preferably, the profile of described sub-negative electrode is cylindrical, perpendicular to described thruster rear wall fixed installation.
The present invention has following beneficial effect:
1. two sub-negative electrodes work simultaneously and reduce the emission maximum electric current of single main cathode, improve the life-span of single sub-negative electrode, contribute to the raising in thruster life-span;
2. start other one group of sub-negative electrode after one group of sub-cathode degradation, substantially increase the life-span of ion thruster;
3. symmetrical sub-negative electrode work can improve the uniformity of the ion distribution of especially grid upstream in discharge chamber, is conducive to the life-span of improving grid, thus improves the life-span of ion thruster.
The present invention can be widely used in the higher survey of deep space of life and reliability requirement and geo-synchronous orbit satellite platform.
Accompanying drawing explanation
Fig. 1 is cathode ion thruster discharge chamber structural representation of the present invention.
Fig. 2 is that sub-negative electrode of the present invention is at thruster rear wall schematic layout pattern.
Wherein, 1-thruster rear wall, 2-anode, 3-negative electrode, 4-rear wall center.
Embodiment
To develop simultaneously embodiment below in conjunction with accompanying drawing, describe the present invention.
The discharge chamber of four cathode ion thrusters of the present invention as illustrated in fig. 1 and 2.The main cathode of ion thruster is made up of four sub-negative electrodes 3, and four sub-negative electrodes 3 to be arranged on ion thruster rear wall 1 and relative to rear wall center 4 symmetry arrangement; Angle between two adjacent sub-negative electrodes 3 is equal, is 90 °.
Ion thruster of the prior art only arranges a main cathode, because the Magnetic field distribution of ion thruster is near discharge chamber inwall, when main cathode electron emission, the electron density on axis is larger, ion density near the part of discharge chamber inwall is little, causes electron distributions uneven.Main cathode is designed to 4 sub-negative electrodes 3 by the present invention, because sub-negative electrode 3 is more near discharge chamber anode 2, the electrons of sub-negative electrode 3 transmitting is more guides to discharge chamber anode 2 faster, improve the uniformity of the especially ion distribution of grid upstream in discharge chamber, be conducive to the life-span of improving grid, thus improve the life-span of ion thruster.
Two the sub-negative electrodes 3 being in diagonal angle are one group, and during ion thruster work, wherein one group of sub-negative electrode 3 works, and other one group of sub-negative electrode 3 is in off-mode; After one group of sub-negative electrode 3 lost efficacy, started other one group of sub-negative electrode 3.The profile of sub-negative electrode 3 is cylindrical, fixedly mounts perpendicular to described thruster rear wall 1.Two sub-negative electrodes 3 work simultaneously and reduce the emission maximum electric current of single main cathode, improve the life-span of single sub-negative electrode 3, contribute to the raising in thruster life-span.
To sum up, the present invention can improve the life-span of thruster to a great extent, thus improve the performance of thruster, the higher survey of deep space of power requirements such as jupiter's exploration, planetoid sampling can be widely used in return, also can be applicable to the station-keeping satellite platform that the life-span is had high requirements, as earth synchronous orbit communication satellite.
In sum, these are only preferred embodiment of the present invention, be not intended to limit protection scope of the present invention.Within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (2)
1. four cathode ion thrusters, is characterized in that, the main cathode of described ion thruster is made up of four sub-negative electrodes (3); It is upper and relative to rear wall center (4) symmetry arrangement that these four sub-negative electrodes (3) are arranged in ion thruster rear wall (1);
Two the sub-negative electrodes (3) being in diagonal angle are one group, during ion thruster work, and wherein one group of sub-negative electrode (3) work, other one group of sub-negative electrode (3) is in off-mode; After one group of sub-negative electrode (3) was lost efficacy, other one group of sub-negative electrode (3) started.
2. four cathode ion thrusters, is characterized in that, the profile of described sub-negative electrode (3) is cylindrical, perpendicular to described thruster rear wall (1) fixed installation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201510419168.0A CN105065221A (en) | 2015-07-16 | 2015-07-16 | Novel four-cathode ion thruster |
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| CN201510419168.0A CN105065221A (en) | 2015-07-16 | 2015-07-16 | Novel four-cathode ion thruster |
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| CN105065221A true CN105065221A (en) | 2015-11-18 |
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| CN201510419168.0A Pending CN105065221A (en) | 2015-07-16 | 2015-07-16 | Novel four-cathode ion thruster |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106523313A (en) * | 2016-12-07 | 2017-03-22 | 兰州空间技术物理研究所 | Micropulse plasma thruster |
| CN107729602A (en) * | 2017-09-01 | 2018-02-23 | 兰州空间技术物理研究所 | A kind of ion thruster working parameters Optimal Design Method |
| CN111516907A (en) * | 2020-04-27 | 2020-08-11 | 哈尔滨工业大学 | Micro-cathode arc thrust array system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2149440C1 (en) * | 1998-01-12 | 2000-05-20 | Опытное конструкторское бюро "Факел" | Device for actuating medium supply for plasma accelerators |
| RU2188337C2 (en) * | 2000-07-12 | 2002-08-27 | Федеральное государственное унитарное предприятие Российского авиационно-космического агентства "Опытное конструкторское бюро "Факел" | Closed electron drift plasma jet engine |
| WO2005044664A2 (en) * | 2003-11-05 | 2005-05-19 | Eads Space Transportation Gmbh | Carrier for transporting a payload and method for altering the orbit of a carrier |
| CN101462587A (en) * | 2009-01-16 | 2009-06-24 | 哈尔滨工程大学 | Redundant controlled microminiature underwater robot, and method for failure diagnosis and fault tolerant control |
| US20140070663A1 (en) * | 2012-09-11 | 2014-03-13 | Rutgers, The State University Of New Jersey | Electrokinetic nanothrusters and applications thereof |
-
2015
- 2015-07-16 CN CN201510419168.0A patent/CN105065221A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2149440C1 (en) * | 1998-01-12 | 2000-05-20 | Опытное конструкторское бюро "Факел" | Device for actuating medium supply for plasma accelerators |
| RU2188337C2 (en) * | 2000-07-12 | 2002-08-27 | Федеральное государственное унитарное предприятие Российского авиационно-космического агентства "Опытное конструкторское бюро "Факел" | Closed electron drift plasma jet engine |
| WO2005044664A2 (en) * | 2003-11-05 | 2005-05-19 | Eads Space Transportation Gmbh | Carrier for transporting a payload and method for altering the orbit of a carrier |
| CN101462587A (en) * | 2009-01-16 | 2009-06-24 | 哈尔滨工程大学 | Redundant controlled microminiature underwater robot, and method for failure diagnosis and fault tolerant control |
| US20140070663A1 (en) * | 2012-09-11 | 2014-03-13 | Rutgers, The State University Of New Jersey | Electrokinetic nanothrusters and applications thereof |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106523313A (en) * | 2016-12-07 | 2017-03-22 | 兰州空间技术物理研究所 | Micropulse plasma thruster |
| CN106523313B (en) * | 2016-12-07 | 2019-03-15 | 兰州空间技术物理研究所 | A kind of micropulse plasma thruster |
| CN107729602A (en) * | 2017-09-01 | 2018-02-23 | 兰州空间技术物理研究所 | A kind of ion thruster working parameters Optimal Design Method |
| CN111516907A (en) * | 2020-04-27 | 2020-08-11 | 哈尔滨工业大学 | Micro-cathode arc thrust array system |
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