CN113202709A - Hybrid excitation working mode of Hall electric thruster - Google Patents
Hybrid excitation working mode of Hall electric thruster Download PDFInfo
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- CN113202709A CN113202709A CN202110538690.6A CN202110538690A CN113202709A CN 113202709 A CN113202709 A CN 113202709A CN 202110538690 A CN202110538690 A CN 202110538690A CN 113202709 A CN113202709 A CN 113202709A
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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
- F03H1/0081—Electromagnetic plasma thrusters
Abstract
The application relates to the technical field of aerospace electric propulsion, particularly, relates to a hall electric thruster hybrid excitation working method, including self-excitation hall thruster and excitation power, wherein: the excitation power supply is used as an external power supply and is connected with the self-excitation Hall thruster; the self-excitation Hall thruster comprises an excitation winding and an anode discharge loop; the exciting winding is connected in series in the anode discharge loop. The hybrid excitation working mode of externally connecting an excitation power supply on the basis of the self-excitation working mode is adopted, so that the magnetic field of the thruster can meet the design requirement under the condition that the volume and the weight of the low-power Hall thruster are limited or further optimization is needed, the discharge oscillation of the Hall thruster during working can be effectively suppressed, the service life of the thruster is prolonged, the starting time of the thruster is greatly shortened, and the power of the excitation power supply is reduced.
Description
Technical Field
The application relates to the technical field of aerospace electric propulsion, in particular to a hybrid excitation working mode of a Hall electric thruster.
Background
The working principle of the Hall electric thruster is as follows: two ceramic sleeves with different radiuses are fixed on the same axis to form a plasma discharge channel with an annular structure, namely a discharge chamber, an inner excitation winding and an outer excitation winding form a radially distributed magnetic field in the annular discharge chamber through magnetic poles under the action of excitation current, and the configuration of the magnetic field is determined by the integral magnetic circuit structure and the excitation current. The discharge plasma between the anode and the cathode will generate a self-consistent axial field in the channel under radially distributed magnetic field conditions, so that orthogonal electromagnetic fields will be formed in the annular discharge chamber. After electrons emitted by the cathode enter the annular discharge chamber, circumferential drift, also called Hall drift, is formed under the action of the orthogonal magnetic field, and a large number of electrons drift and move in the annular discharge chamber to form Hall current. Propellant is injected into the annular discharge chamber from the gas distributor, and neutral atoms and electrons which do drift motion are ionized into ions by the collider. The ions have large mass, the motion track of the ions is basically not influenced by a magnetic field, and the ions are ejected at high speed along the axial direction under the action of an axial electric field to generate thrust. Meanwhile, another part of electrons emitted by the cathode are neutralized with the axially ejected ions, and the macroscopic electric neutrality of the thruster plume is maintained.
Therefore, the excitation working mode of the excitation winding directly determines the ionization efficiency, the plasma discharge stability and the beam focusing characteristic of the Hall thruster, and is directly related to the performance and the service life of the thruster, and even influences the success or failure of space flight tasks.
The excitation mode of the traditional Hall thruster mainly comprises two working modes of self-excitation and independent excitation. The self-excitation working mode is that the excitation winding is connected in series into an anode discharge loop of the thruster, and the discharge current generated by plasma discharge between the anode and the cathode is utilized to excite the excitation winding to form a required magnetic field. Under the condition that the whole magnetic circuit structure of the Hall thruster is not changed, the magnetic field configuration depends on the ampere-turn number of the exciting winding, and for a low-power Hall thruster, because the discharge current is small, the number of turns of the coil of the exciting winding must be increased in order to meet the ampere-turn number requirement of self-excitation work, but the number of turns of the coil cannot be increased to the required number of turns due to the structural space and weight limitation of the thruster. In the independent excitation working mode, an excitation loop and an anode discharge loop are completely independent, excitation of an excitation winding is realized by an external excitation power supply, but the working mode has the defects of unstable starting, slow starting, large discharge oscillation and poor matching property with plasma discharge of the thruster, and the response time and the working life of the thruster can be influenced.
Disclosure of Invention
The main purpose of the application is to provide a hybrid excitation working mode of the Hall electric thruster, wherein an excitation power supply is externally connected on the basis of the working mode of the self-excitation Hall thruster, and the external excitation power supply supplements excitation current, so that the hybrid excitation current formed by combining the excitation power supply with the self-excitation current meets the requirement of the excitation winding on the number of ampere-turns for working.
In order to achieve the above object, the present application provides a hybrid excitation working method for a hall electric thruster, including a self-excitation hall thruster and an excitation power supply, wherein: the excitation power supply is used as an external power supply and is connected with the self-excitation Hall thruster; the self-excitation Hall thruster comprises an excitation winding and an anode discharge loop; the exciting winding is connected in series in the anode discharge loop.
Further, the anode discharge loop comprises an anode, an anode power supply and a hollow cathode, wherein the negative end of the anode power supply is connected with the power supply end of the hollow cathode.
Furthermore, one end of the excitation winding is connected with the negative end of the anode power supply, and the other end of the excitation winding is connected with the power supply ground end.
Furthermore, the negative pole of the excitation power supply is connected with the negative end of the anode power supply, and the positive pole of the excitation power supply is connected with the power supply ground end.
Further, the excitation winding comprises an inner excitation winding and an outer excitation winding, and the inner excitation winding and the outer excitation winding are connected in series.
Further, when the thruster is started, the self-excitation working mode of the Hall thruster is started, and then the excitation power supply is started to supplement the excitation current.
The hybrid excitation working mode of the Hall electric thruster provided by the invention has the following beneficial effects:
the invention adopts a hybrid excitation working mode of externally connecting an excitation power supply on the basis of a self-excitation working mode, can enable the magnetic field of the thruster to meet the design requirement under the condition that the volume and the weight of the low-power Hall thruster are limited or further optimization is needed, and can effectively suppress the discharge oscillation when the Hall thruster works due to the inductance effect and the discharge current of the self-excitation working in the process of gradually increasing, prolong the service life of the thruster, greatly shorten the starting time of the thruster and reduce the power of the excitation power supply.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, serve to provide a further understanding of the application and to enable other features, objects, and advantages of the application to be more apparent. The drawings and their description illustrate the embodiments of the invention and do not limit it. In the drawings:
fig. 1 is a schematic power supply and distribution diagram of a hybrid excitation operation mode of a hall electric thruster according to an embodiment of the present application.
Detailed Description
In order to make the technical solutions better understood by those skilled in the art, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only partial embodiments of the present application, but not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
It should be noted that the terms "first," "second," and the like in the description and claims of this application and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It should be understood that the data so used may be interchanged under appropriate circumstances such that embodiments of the application described herein may be used. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed, but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
In this application, the terms "upper", "lower", "left", "right", "front", "rear", "top", "bottom", "inner", "outer", "middle", "vertical", "horizontal", "lateral", "longitudinal", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings. These terms are used primarily to better describe the present application and its embodiments, and are not used to limit the indicated devices, elements or components to a particular orientation or to be constructed and operated in a particular orientation.
Moreover, some of the above terms may be used to indicate other meanings besides the orientation or positional relationship, for example, the term "on" may also be used to indicate some kind of attachment or connection relationship in some cases. The specific meaning of these terms in this application will be understood by those of ordinary skill in the art as appropriate.
In addition, the term "plurality" shall mean two as well as more than two.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
As shown in fig. 1, the present application provides a hybrid excitation working mode of a hall electric thruster, including a self-excitation hall thruster and an excitation power supply, wherein: the excitation power supply is used as an external power supply and is connected with the self-excitation Hall thruster; the self-excitation Hall thruster comprises an excitation winding and an anode discharge loop; the exciting winding is connected in series in the anode discharge loop.
Specifically, according to the working mode of the self-excitation hall thruster, the excitation winding is connected in series to the anode discharge loop, and then the excitation power supply is used as an external excitation power supply to be connected to the anode discharge loop. In the starting process of the Hall electric thruster, ignition is carried out through a hollow cathode in an anode discharge loop, an anode power supply in the anode discharge loop can be started after ignition is successful, the anode discharge loop starts to work, a discharge chamber of the Hall electric thruster starts to discharge, the Hall thruster enters a self-excitation working mode as discharge current passes through an excitation winding, and then the excitation power supply is started to supplement excitation current, so that mixed excitation current formed by combining the discharge current with the self-excitation current meets the requirement of the excitation winding on the number of ampere-turns for working.
Further, the anode discharge loop comprises an anode, an anode power supply and a hollow cathode, and the negative end of the anode power supply is connected with the power supply end of the hollow cathode. The anode, the anode power supply and the hollow cathode form an anode discharge loop, and are used for emitting electrons to enter the discharge chamber on one hand and generating discharge current through plasma discharge between the anode, the anode power supply and the hollow cathode.
Furthermore, one end of the excitation winding is connected with the negative end of the anode power supply, and the other end of the excitation winding is connected with the power supply ground end. The exciting winding is mainly excited by the discharge current generated by plasma discharge between the anode and the cathode to form a required magnetic field.
Furthermore, the negative pole of the excitation power supply is connected with the negative end of the anode power supply, and the positive pole of the excitation power supply is connected with the power supply ground end. The excitation power supply is directly connected with the self-excitation Hall thruster and is mainly used for supplementing excitation current in the self-excitation working state of the Hall thruster, so that the supplemented excitation current and the self-excitation current are combined to form mixed excitation current, and the requirement of the number of working ampere-turns design of an excitation winding is met.
Further, the excitation winding comprises an inner excitation winding and an outer excitation winding, and the inner excitation winding and the outer excitation winding are connected in series. The inner exciting winding and the outer exciting winding form a radially distributed magnetic field in the annular discharge chamber through magnetic poles under the action of exciting current, and discharge plasma between an anode and a cathode generates a self-consistent axial field in a channel under the condition of the radially distributed magnetic field, so that an orthogonal electromagnetic field is formed in the annular discharge chamber.
Further, when the thruster is started, the self-excitation working mode of the Hall thruster is started, and then the excitation power supply is started to supplement the excitation current. In the embodiment of the invention, in the starting process of the Hall electric thruster, the hollow cathode is firstly ignited, the anode power supply is firstly started after the ignition is successful, the discharge chamber of the Hall electric thruster starts to discharge, the Hall thruster enters a self-excitation working mode because the discharge current passes through the excitation winding, and then the excitation power supply is started to supplement the excitation current, so that the mixed excitation current formed by combining the Hall thruster and the self-excitation current meets the design requirement of the number of ampere turns of the excitation winding during working.
The above description is only a preferred embodiment of the present application and is not intended to limit the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application.
Claims (6)
1. The utility model provides a hall electric thruster hybrid excitation working method which characterized in that, includes self-excitation hall thruster and excitation power supply, wherein:
the excitation power supply is used as an external power supply and is connected with the self-excitation Hall thruster;
the self-excitation Hall thruster comprises an excitation winding and an anode discharge loop;
the excitation winding is connected in series into the anode discharge loop.
2. The hall electric thruster hybrid excitation operating mode as set forth in claim 1, wherein said anode discharge circuit comprises an anode, an anode power supply and a hollow cathode, and wherein a negative terminal of said anode power supply is connected to a power ground terminal of said hollow cathode.
3. The hall electric thruster hybrid excitation operating mode as set forth in claim 2, wherein said excitation winding is connected at one end to the negative terminal of the anode power supply and at the other end to the power supply ground.
4. The hall electric thruster hybrid excitation operating mode as set forth in claim 2, wherein the negative pole of the excitation power supply is connected to the negative terminal of the anode power supply and the positive pole is connected to the power supply ground.
5. The hall electric thruster hybrid excitation operating mode as set forth in claim 1, wherein said field winding comprises an inner field winding and an outer field winding, said inner field winding and said outer field winding being connected in series.
6. The hybrid excitation working mode of the hall electric thruster as claimed in claim 1, wherein when the thruster is started, the self-excitation working mode of the hall thruster is started, and then the excitation power supply is started to supplement the excitation current.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202110538690.6A CN113202709A (en) | 2021-05-17 | 2021-05-17 | Hybrid excitation working mode of Hall electric thruster |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110538690.6A CN113202709A (en) | 2021-05-17 | 2021-05-17 | Hybrid excitation working mode of Hall electric thruster |
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| CN113202709A true CN113202709A (en) | 2021-08-03 |
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| CN202110538690.6A Pending CN113202709A (en) | 2021-05-17 | 2021-05-17 | Hybrid excitation working mode of Hall electric thruster |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115681062A (en) * | 2023-01-03 | 2023-02-03 | 国科大杭州高等研究院 | Hybrid working mode Hall propulsion system and spacecraft with same |
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| CN102493937A (en) * | 2011-12-15 | 2012-06-13 | 哈尔滨工业大学 | Hall thrustor capable of realizing self cleaning of polluted membrane of discharge channel and self cleaning method of Hall thrustor |
| JP2012149617A (en) * | 2011-01-21 | 2012-08-09 | Mitsubishi Electric Corp | Power supply device |
| CN102711354A (en) * | 2012-05-28 | 2012-10-03 | 哈尔滨工业大学 | Decoupling control method applied to coupling magnetic field of twin-stage Hall thruster |
| CN103953517A (en) * | 2014-05-13 | 2014-07-30 | 哈尔滨工业大学 | Hall thruster improving device |
| US20170284380A1 (en) * | 2016-03-30 | 2017-10-05 | California Institute Of Technology | Hall effect thruster electrical configuration |
| CN109751213A (en) * | 2019-02-15 | 2019-05-14 | 上海空间推进研究所 | Reduce the discharge loop and soft-start method of hall thruster starting impact |
| CN111075676A (en) * | 2019-11-28 | 2020-04-28 | 兰州空间技术物理研究所 | Permanent magnet Hall thruster |
| CN111648930A (en) * | 2020-05-19 | 2020-09-11 | 上海空间推进研究所 | Optimal configuration method for Hall thruster power supply and distribution module architecture |
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2021
- 2021-05-17 CN CN202110538690.6A patent/CN113202709A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2012149617A (en) * | 2011-01-21 | 2012-08-09 | Mitsubishi Electric Corp | Power supply device |
| CN102493937A (en) * | 2011-12-15 | 2012-06-13 | 哈尔滨工业大学 | Hall thrustor capable of realizing self cleaning of polluted membrane of discharge channel and self cleaning method of Hall thrustor |
| CN102711354A (en) * | 2012-05-28 | 2012-10-03 | 哈尔滨工业大学 | Decoupling control method applied to coupling magnetic field of twin-stage Hall thruster |
| CN103953517A (en) * | 2014-05-13 | 2014-07-30 | 哈尔滨工业大学 | Hall thruster improving device |
| US20170284380A1 (en) * | 2016-03-30 | 2017-10-05 | California Institute Of Technology | Hall effect thruster electrical configuration |
| CN109751213A (en) * | 2019-02-15 | 2019-05-14 | 上海空间推进研究所 | Reduce the discharge loop and soft-start method of hall thruster starting impact |
| CN111075676A (en) * | 2019-11-28 | 2020-04-28 | 兰州空间技术物理研究所 | Permanent magnet Hall thruster |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115681062A (en) * | 2023-01-03 | 2023-02-03 | 国科大杭州高等研究院 | Hybrid working mode Hall propulsion system and spacecraft with same |
| CN115681062B (en) * | 2023-01-03 | 2023-06-02 | 国科大杭州高等研究院 | Mixed working mode Hall propulsion system and spacecraft with same |
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