CN115681057B - Hall propulsion system and operation method thereof - Google Patents
Hall propulsion system and operation method thereof Download PDFInfo
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- CN115681057B CN115681057B CN202310000701.4A CN202310000701A CN115681057B CN 115681057 B CN115681057 B CN 115681057B CN 202310000701 A CN202310000701 A CN 202310000701A CN 115681057 B CN115681057 B CN 115681057B
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Abstract
The invention relates to the technical field of plasma propulsion devices, in particular to a Hall propulsion system and an operation method thereof. A hall propulsion system, comprising: the anode assembly comprises an inner magnetic pole and an outer magnetic pole which are sleeved in sequence from inside to outside, a discharge channel is reserved between the inner magnetic pole and the outer magnetic pole, and a gas distributor is arranged in the discharge channel; the gas distributor is connected with the positive electrode of the first power supply, and the outer magnetic pole is connected with the negative electrode of the first power supply. When the system is operated, no external electron source provides neutral electrons, no cathode power is needed, only secondary electrons and plasma electrons are needed to maintain discharge, and the energy consumption of the Hall propulsion system when the system is in low thrust task can be reduced.
Description
Technical Field
The invention relates to the technical field of plasma propulsion devices, in particular to a Hall propulsion system and an operation method thereof.
Background
The Hall propeller is an advanced electric propulsion device, has the outstanding characteristics of high specific impulse, high thrust power ratio, long service life and low cost, and is widely applied to various satellite platforms as a gesture track adjusting device, a track lifting and leaving device, a main propulsion device and a dragging-free compensation device. In a hall thruster the propellant is ionized and a plasma is generated. The Hall thruster restrains electrons in the magnetic field through the radial magnetic field and the axial electric field, and generates plasma by utilizing electron ionization propellant, self-consistent plasma potential drop accelerates ions to spray out of a thruster discharge channel to generate thrust, and other electrons neutralize ions in plume under the attraction of the potential of beam ions.
When the Hall propeller in the prior art works, the cathode power supply continuously works to enable the cathode part to output electrons so as to provide electrons for the anode propelling part. However, when the Hall propeller performs propelling operation, the thrust force is required to be adjusted according to the task type. In the task with smaller thrust requirement, the cathode power supply is continuously discharged, so that the cathode power is higher, and the energy consumption of the Hall thruster is higher when the Hall thruster performs the task with smaller thrust.
Disclosure of Invention
Therefore, the technical problem to be solved by the invention is to overcome the defect of high energy consumption of the Hall propulsion system in the prior art when the Hall propulsion system performs a low thrust task, so as to provide the Hall propulsion system and the operation method thereof.
In order to solve the above technical problems, the present invention provides a hall propulsion system, including:
the anode assembly comprises an inner magnetic pole and an outer magnetic pole which are sleeved in sequence from inside to outside, a discharge channel is reserved between the inner magnetic pole and the outer magnetic pole, and a gas distributor is arranged in the discharge channel;
and the gas distributor is connected with the positive electrode of the first power supply, and the outer magnetic pole is connected with the negative electrode of the first power supply.
Optionally, the discharge channel is annular, and the gas distributor is arranged at the bottom of the discharge channel.
Optionally, the gas outlet on the gas distributor is parallel to the axial direction of the discharge channel.
Optionally, the inner wall of the discharge channel is electrically isolated from the gas distributor.
Optionally, the inner side wall of the discharge channel is a ceramic member.
Optionally, a control switch is installed between the first power supply and the external magnetic pole.
The invention also provides an operation method of the Hall propulsion system, which comprises the following steps of:
controlling the gas distributor to output gas into the discharge channel, and keeping the flow of the gas to be a preset flow;
starting a first power supply, taking a gas distributor as an anode and taking an external magnetic pole as a cathode to discharge, and generating plasma by collision between primary electrons in a discharge channel and gas after the primary electrons are accelerated by an electric field;
part of positive particles in the plasma move to the outer magnetic pole to participate in discharge, and the rest of positive particles are discharged out of the discharge channel to generate thrust.
Optionally, before the step of controlling the gas distributor to output the gas into the discharge channel, the method further comprises: the residual gas inside the gas distributor is discharged.
Optionally, the control switch is adjusted to be connected or disconnected to control the hall propulsion system to operate or stop.
The technical scheme of the invention has the following advantages:
1. the Hall propulsion system provided by the invention comprises: the anode assembly comprises an inner magnetic pole and an outer magnetic pole which are sleeved in sequence from inside to outside, a discharge channel is reserved between the inner magnetic pole and the outer magnetic pole, and a gas distributor is arranged in the discharge channel; the gas distributor is connected with the positive electrode of the first power supply, and the outer magnetic pole is connected with the negative electrode of the first power supply.
When the Hall propulsion system performs a propulsion task, the gas distributor outputs gas into the discharge channel, the first power supply works, the gas distributor is used as an anode, the outer magnetic pole is used as a cathode, an electric field is formed in the discharge channel, primary electrons in the discharge channel move under the action of the electric field to collide with the gas to generate plasma, most positive particles in the plasma move to the outer magnetic pole to participate in discharge, and the rest of positive particles are discharged outside the discharge channel to generate thrust. Because the high potential of the first power supply is bound, less ions are discharged to the discharge channel, so that the Hall propulsion system can generate smaller thrust, but no external electron source provides neutral electrons when the Hall propulsion system operates, cathode power is not needed, discharge can be maintained only by secondary electrons and plasma electrons, and the energy consumption of the Hall propulsion system when the Hall propulsion system performs a small thrust task can be greatly reduced.
2. In the Hall propulsion system provided by the invention, the gas outlet on the gas distributor is parallel to the axial direction of the discharge channel. The gas is output towards the outlet of the discharge channel, then the generated plasma is sprayed out of the discharge channel under the action of an electric field, so that the collision probability of particles and the inner side wall of the discharge channel is reduced, and the operation efficiency of the Hall propulsion system is improved.
3. The operation method of the Hall propulsion system provided by the invention is based on the Hall propulsion system, and comprises the following steps: controlling the gas distributor to output gas into the discharge channel, and keeping the flow of the gas to be a preset flow; starting a first power supply, taking a gas distributor as an anode and taking an external magnetic pole as a cathode to discharge, and generating plasma by collision between primary electrons in a discharge channel and gas after the primary electrons are accelerated by an electric field; part of positive particles in the plasma move to the outer magnetic pole to participate in discharge, and the rest of positive particles are discharged out of the discharge channel to generate thrust. Because the high potential of the first power supply is bound, particles discharged to the discharge channel are fewer, so that the Hall propulsion system can generate smaller thrust, but when the Hall propulsion system operates, the discharge can be maintained only by secondary electrons and plasma electrons without cathode power, no external electron source is used for providing neutral electrons, and a cathode assembly can be arranged in the Hall propulsion system, but when a small thrust task is carried out, the cathode assembly does not need to work, so that the energy consumption of the Hall propulsion system when the small thrust task is carried out can be greatly reduced.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the present invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
Fig. 1 is a schematic diagram of the operation of a multi-mode hall propulsion system provided in an embodiment of the present invention.
Fig. 2 is a schematic structural diagram of a multi-mode hall propulsion system provided in an embodiment of the present invention.
Fig. 3 is a schematic view of the operation mode selection of the multi-mode hall propulsion system provided in an embodiment of the present invention.
Reference numerals illustrate: 1. a first power supply; 2. a second power supply; 3. a control switch; 4. an inner magnetic pole; 5. an outer magnetic pole; 6. a gas distributor; 7. a discharge channel; 8. a heat shield; 9. an emitter; 10. a heater; 11. a cathode insulating base; 12. a mounting inclined plane; 13. an insulating seat of the propeller; 14. and a system installation seat.
Detailed Description
The following description of the embodiments of the present invention will be made apparent and fully in view of the accompanying drawings, in which some, but not all embodiments of the invention are shown. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In the description of the present invention, it should be noted that the directions or positional relationships indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience of describing the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
In addition, the technical features of the different embodiments of the present invention described below may be combined with each other as long as they do not collide with each other.
Example 1
Fig. 1 to 3 show a multi-mode hall propulsion system according to the present embodiment, which includes a cathode assembly, an anode assembly, a first power source 1 and a second power source 2.
The anode component comprises an inner magnetic pole 4 and an outer magnetic pole 5, the outer magnetic pole 5 is sleeved outside the inner magnetic pole 4 in a ring shape, a discharge channel 7 is reserved between the inner magnetic pole 4 and the outer magnetic pole 5, and a gas distributor 6 is arranged in the discharge channel 7. The anode component is used for attracting electrons, providing energy for the electrons and ionizing neutral gas to generate ions, and accelerating the ions to make the ions spray out of the discharge channel 7 to generate thrust. The inner magnetic pole 4 and the outer magnetic pole 5 form a radial magnetic field in the discharge channel 7, electrons drift in the orthogonal electromagnetic field under the combined action of an axial electric field generated by the gas distributor 6 serving as an anode, ions are generated by ionizing neutral gas, plasma potential drops are generated, an ion accelerating electric field is generated, and the self-consistent ionization accelerating process is completed. In this embodiment, the discharge channel is annular, and the gas distributor 6 is disposed at the bottom of the discharge channel. The gas outlets on the gas distributor 6 are parallel to the axial direction of the discharge channel 7. The inner wall of the discharge channel 7 is electrically isolated from the gas distributor 6. In this embodiment, the inner side wall of the discharge channel 7 is a ceramic member made of ceramic material, so that the discharge channel is isolated from the gas distributor by electric potential. So as to prevent charged particles in the plasma from being attracted to the inner wall of the discharge channel 7, ensure that the plasma can smoothly flush the discharge channel for output, and generate thrust. In other embodiments, the discharge channel may also be a metal piece made of a metal material, in which case an insulating isolation layer is provided between the discharge channel and the gas distributor to electrically isolate the discharge channel from the gas distributor.
The cathode assembly comprises a heat shield 8 and an emitter 9, wherein the heat shield 8 is sleeved outside the emitter 9, and one end of the emitter 9 is abutted to be provided with a heater 10 so as to facilitate heat transfer between the heater 10 and the emitter 9. The cathode assembly is configured to emit electrons toward the anode assembly when the hall propulsion system is in operation. The emitter 9 of the cathode assembly generates electrons, a part of which enter the discharge channel 7 to participate in ionization under the attraction of the high potential of the anode assembly, and another part of which are used for neutralizing the outgoing ion beam current. The heater 10 is used for heating the emitter 9 to enable the emitter 9 to reach a critical electron emission temperature, and electrons can be emitted for ionization and neutralization. The heat shield 8 is used for reflecting the heat radiation emitted by the emitter 9, reducing the heat dissipation of the emitter 9 and effectively reducing the power of the heater 10. One end of the heater is connected with a second power supply, and the joint at the other end of the heater is welded on the heat shield so that the heater is connected with the heat shield in a conductive mode. In this embodiment, the cathode assembly is a heating type working medium-free cathode, and the emitter is heated by the heating resistance wire serving as a heater, so that the emitter reaches the electron emission temperature, electrons are emitted for the anode assembly to use, and the heat shield serves as an auxiliary component for reducing the heat dissipation of the emitter, thereby reducing the power of the cathode assembly and improving the efficiency. One end of the second power supply is connected to the heater, the other end is connected to the heat shield, and the emitter is provided with no electrode interface. In other embodiments, the second power source may be connected directly across the heater. The positive pole of the first power supply 1 is connected with the gas distributor 6, and the negative pole of the first power supply 1 is connected with the heat shield 8. The negative pole side of the first power supply 1 is also connected with an external magnetic pole 5, the external magnetic pole 5 is connected with a heat shield 8 in parallel, and a control switch 3 is arranged between the first power supply 1 and the external magnetic pole 5. The positive electrode of the second power supply 2 is connected with the heater 10, and the negative electrode of the second power supply 2 is connected with the heat shield 8. The second power supply 2 is used to heat the emitter 9 to an electron emission temperature.
A cathode insulating seat 11 is installed at one side of the anode assembly, a mounting inclined surface 12 is arranged at one side of the cathode insulating seat 11 facing the anode assembly, the mounting inclined surface 12 is arranged in an upward inclined manner, and the cathode assembly is installed on the mounting inclined surface 12. The anode assembly is mounted on a propeller insulating mount 13 to electrically isolate the anode assembly from the cathode assembly. The propeller insulating base 13 and the propeller insulating base 13 are fixedly arranged on the system mounting base 14. The hall propulsion system is mounted on the spacecraft by a system mount 14.
The cathode components are connected in parallel and are at least two, and the cathode components are mutually backed up. The cathode assemblies which are mutually backup are arranged at intervals around the anode assemblies or are arranged at equal intervals in a circumferential array shape, or are arranged on the same side of the anode assemblies in parallel. The cathode assembly in this embodiment is provided with a pair of cathode assemblies which are mutually backup and are mounted in parallel on the mounting inclined surface 12 of the cathode insulating base 11.
The multi-mode hall propulsion system provided in this embodiment needs to perform the following operations when it is started for the first time:
firstly, a satellite power supply is connected, and a system is electrified; after the system is electrified, a self-checking program of a system circuit and control is carried out, so that the normal operation of the electric control of the propulsion system is ensured; after the electric control is confirmed to be normal, keeping the gas tank valve closed, opening all subsequent gas valves, and discharging residual gas reserved in a gas storage and supply system pipeline; after the gas storage and supply system is exhausted, primary exhaust of the cathode assembly is carried out, the heater 10 is heated to a temperature slightly higher than the temperature of the normal working condition for 15 minutes, and the emission of residual gas and impurities in the emitter 9 is carried out; and after all preparation procedures are finished, opening a gas tank valve, and setting working parameters such as working voltage, cathode current, gas flow and the like according to the requirements of working conditions.
The multi-working mode Hall propulsion system can have five different working modes according to different task demands and propeller conditions, and the five working modes are respectively as follows: a low thrust self-discharge mode, a cathodic self-neutralization-cathodic auxiliary ignition mode, a system lossless cathode full power mode, and a system lossy cathode full power mode.
When the low-thrust self-discharge mode is operated, the first power supply 1 is started, the control switch 3 connected with the outer magnetic pole 5 is connected, and the second power supply 2 is closed. In this working mode, the hall propulsion system uses the gas distributor 6 of the anode assembly as positive, the outer magnetic pole 5 is negative to discharge, the discharge is simpler, cathode power is not needed, at this time, most of ions directly return to the cathode of the first power supply 1 through the outer magnetic pole 5 and the control switch 3, only a few ions are led out of the propeller as beam current, so that the thrust generated in this mode is smaller, no external electron source provides neutralizing electrons, and the suspension potential in this mode is also higher. The low-thrust self-discharge mode is suitable for space tasks with smaller thrust requirements and low requirements on load levitation potential.
When the cathode-free self-neutralization mode is operated, the control switch 3 is required to be closed, the second power supply 2 is closed, and the operation is carried out according to the following working procedures: setting the working flow of the output gas to be more than twice of the rated flow, and waiting for the flow to be stable; then the first power supply 1 is started, and under the impact heating of large-flow large-ion flux, a certain amount of electrons are emitted from the surface of an emitter of the cathode assembly to participate in discharge; waiting for avalanche discharge of the Hall propulsion system, successfully starting the Hall propulsion system to enter a stable working condition, then reducing the flow of the gas back to the rated working condition flow, and entering a cathodic-free self-neutralization mode to operate.
Unlike the low-thrust self-discharge mode, the cathode-free self-neutralization mode uses the cathode assembly as the cathode, a small portion of ions flow back to the cathode of the first power supply 1 through the cathode assembly, and the other large portion of ions are led out of the discharge channel 7 as beam ions to generate thrust, so that the thrust generated by the mode is higher than that generated by the low-thrust self-discharge mode. The mode has normal appearance of the propeller, no deformation of the magnetic field position type, and quick start when the working condition of the cathode is normal, is generally suitable for the first half life cycle of a Hall propulsion system, and is difficult to realize due to the deviation of the magnetic field position type and the reduction of the cathode emission capability along with the generation of the propeller etching. The cathode component is quickly heated by large ion flux generated by large flow at the beginning of the cathode-free self-neutralization mode, electrons are generated and gradually started, the flow is regulated to the rated working condition after the starting, the surface of the cathode component is stably and continuously heated by bombardment of high-energy ions, a small amount of electrons are generated to participate in discharge, so that cathode power is not needed, the total system power consumption can be greatly reduced, and the efficiency of a propulsion system is improved. However, the corresponding electron pair Shu Liuli is not added to neutralize the electron pair, so that the floating potential is higher in the working mode. The cathodic-free self-neutralization mode is suitable for space tasks with higher requirements on thrust force and lower requirements on levitation potential.
When the cathode auxiliary ignition mode is operated, the control switch 3 is required to be closed, and the operation is carried out according to the following working procedures: starting a second power supply 2, setting the cathode working current to be a numerical value of a cathode full power mode, and waiting for the cathode to reach the expected temperature; setting a rated gas flow, and waiting for stable gas flow; starting a first power supply 1, and starting the propeller by means of electrons generated by an emitter of the cathode assembly to stably discharge; after the working condition of the propeller is stable, the second power supply 2 is turned off, and the propeller continues to discharge stably depending on the formed stable working condition.
Unlike the cathodically self-neutralising mode, the cathodically assisted ignition mode requires the formation of an initial glow discharge by means of electrons emitted by the emitter of the cathode assembly, and does not require a high flow regime, and after a stable discharge has been formed by means of the cathode, the second power supply 2 is turned off, i.e. a discharge mode consistent with the cathodically self-neutralising mode is entered. When the cathode-free self-neutralization mode cannot be started smoothly due to the fact that a propeller is etched, a magnetic field bit type is deformed, a cathode component is gradually disabled, the generation of an initial avalanche starting process can be carried out by means of full power of the cathode, stable self-sustaining discharge can be carried out after stable discharge is carried out, and the cathode-free self-neutralization mode is carried out again. The thrust, levitation potential and other operating characteristics of this mode are consistent with those of the cathodic-free self-neutralization mode.
When the cathode full-power mode is operated, the control switch 3 is required to be turned off, the rest working flows are consistent with the working flows before the second power supply 2 is turned off in the cathode auxiliary ignition mode, the cathode thermal power is loaded in the whole working process, and the second power supply 2 is not turned off. In this mode, the propulsion system thrust and specific impulse are both slightly raised and the levitation potential is reduced to approximately 0V, since the cathode assembly can generate sufficient electrons for ionization of the propeller and neutralization of Shu Liuli due to heating of the cathode thermal power. However, due to the heating of the cathode thermal power, the overall power consumption of the system increases and the overall efficiency of the propulsion system correspondingly decreases. The cathode full power mode is universal, can work at all stages in the working life cycle of the propulsion system, is the most stable and reliable working mode in all working modes, and is also a working mode with larger cathode consumption. The cathodic full power mode is suitable for satellite platforms or missions where thrust forces are higher than the thrust demands and where the levitation potential of the propulsion system is critical.
The cathode-free self-neutralization mode, the cathode auxiliary ignition mode and the cathode full-power mode can have the following progressive relation with the working condition of the propeller, and can stably operate in three working modes to generate larger thrust and specific impulse when the propeller is slightly etched, the magnetic field is complete and the cathode assembly is normal. When the propeller is subjected to certain etching, magnetic field deformation or cathode performance is reduced, no cathode self-neutralization mode is disabled, and the second power supply 2 is required to work to perform the ignition process of the propeller avalanche glow. When the propulsion system enters the end of life and both the anode assembly and the cathode assembly are lowered, the cathode power needs to be maintained to maintain stable operation of the propeller, and only the cathode full power mode is effective at this time.
The first power supply 1 and the second power supply 2 are arranged, the negative pole of the first power supply 1 is connected with the external magnetic pole 5, the control switch 3 is arranged, the working mode of the Hall propulsion system is changed by matching the first power supply 1 and the second power supply 2 through controlling the on-off of the control switch 3, and the Hall propulsion system can work in a multi-working mode to adapt to propulsion tasks with various different requirements.
Example 2
The present embodiment provides a method for operating a hall propulsion system, which is based on the hall propulsion system described in embodiment 1, and operates in the low-thrust self-discharge mode described in embodiment 1. The gas output from the gas distributor 6 in this embodiment is xenon. The gas of the hall propulsion system may also be krypton, iodine vapor, bismuth vapor, or the like, which may be ionized to form a plasma.
The following operations are required to be executed when the power is started for the first time: firstly, a satellite power supply is connected, and a system is electrified; after the system is electrified, a self-checking program of a system circuit and control is carried out, so that the normal operation of the electric control of the propulsion system is ensured; after the electric control is confirmed to be normal, keeping the gas tank valve closed, opening all subsequent gas valves, and discharging residual gas reserved in a gas storage and supply system pipeline; after the gas storage and supply system is exhausted, primary exhaust of the cathode assembly is carried out, the heater 10 is heated to a temperature slightly higher than the temperature of the normal working condition for 15 minutes, and the emission of residual gas and impurities in the emitter 9 is carried out; and after all preparation procedures are finished, opening a gas tank valve, and setting working parameters such as working voltage, cathode current, gas flow and the like according to the requirements of working conditions.
The gas distributor 6 is controlled to output gas into the discharge channel 7 and to maintain the flow rate of the gas at a predetermined flow rate. The first power supply 1 is started, the control switch 3 connected with the outer magnetic pole 5 is turned off, and the second power supply 2 is turned off. The gas distributor 6 is used as an anode, the external magnetic pole 5 is used as a cathode to discharge, and primary electrons in the discharge channel 7 are accelerated by an electric field and collide with gas to generate plasma; part of positive particles in the plasma move to the outer magnetic pole 5 to participate in discharge, and the rest of positive particles are discharged out of the discharge channel 7 to generate thrust.
Because the high potential of the first power supply is bound, the particles discharged to the discharge channel 7 are fewer, so that the Hall propulsion system can generate smaller thrust, but when the Hall propulsion system operates, the discharge can be maintained only by secondary electrons and plasma electrons without cathode power, no external electron source provides neutral electrons, and a cathode assembly can be arranged in the Hall propulsion system, but when a small thrust task is carried out, the cathode assembly does not need to work, so that the energy consumption of the Hall propulsion system when the small thrust task is carried out can be greatly reduced.
It is apparent that the above examples are given by way of illustration only and are not limiting of the embodiments. Other variations or modifications of the above teachings will be apparent to those of ordinary skill in the art. It is not necessary here nor is it exhaustive of all embodiments. While still being apparent from variations or modifications that may be made by those skilled in the art are within the scope of the invention.
Claims (8)
1. A hall propulsion system, comprising:
the anode assembly comprises an inner magnetic pole (4) and an outer magnetic pole (5) which are sleeved in sequence from inside to outside, a discharge channel (7) is reserved between the inner magnetic pole (4) and the outer magnetic pole (5), and a gas distributor (6) is arranged in the discharge channel (7);
the gas distributor (6) is connected with the positive electrode of the first power supply (1), and the outer magnetic pole (5) is connected with the negative electrode of the first power supply (1);
the operation method of the Hall propulsion system comprises the following steps:
controlling the gas distributor (6) to output gas into the discharge channel (7) and keeping the flow of the gas to be a preset flow;
starting a first power supply (1), taking a gas distributor (6) as an anode, taking an external magnetic pole (5) as a cathode to discharge, accelerating the primary electrons in a discharge channel (7) by an electric field, and then colliding with the gas to generate plasma, wherein no external electron source provides neutral electrons;
part of positive particles in the plasma move to the outer magnetic pole (5) to participate in discharge, and the rest of positive particles are discharged out of the discharge channel (7) to generate thrust.
2. Hall propulsion system according to claim 1, characterized in that the discharge channel (7) is ring-shaped, the gas distributor (6) being arranged at the bottom of the discharge channel (7).
3. Hall propulsion system according to claim 2, characterized in that the gas outlets on the gas distributor (6) are parallel to the axial direction of the discharge channel (7).
4. A hall propulsion system according to any of claims 1-3, characterized in that the inner wall of the discharge channel (7) is electrically isolated from the gas distributor (6).
5. Hall propulsion system according to claim 4, characterized in that the inner side wall of the discharge channel (7) is a ceramic piece.
6. A hall propulsion system according to any one of claims 1-3, characterized in that a control switch (3) is mounted between the first power source (1) and the outer pole (5).
7. The method of operating a hall propulsion system according to claim 1, characterized in that before the step of controlling the gas distributor (6) to output gas into the discharge channel (7), further comprises: the residual gas inside the gas distributor (6) is discharged.
8. Method of operating a hall propulsion system according to claim 1 or 7, characterized in that the control switch (3) is adjusted to be switched on or off to control the hall propulsion system to be operated or shut down.
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| CN115263703A (en) * | 2022-07-29 | 2022-11-01 | 上海空间推进研究所 | Hall thruster working circuit suitable for ground test and starting method |
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2023
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN103953517A (en) * | 2014-05-13 | 2014-07-30 | 哈尔滨工业大学 | Hall thruster improving device |
| JP2019065703A (en) * | 2017-09-28 | 2019-04-25 | 株式会社Ihi | Hall thruster |
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