CN111648930B - Optimal configuration method for Hall thruster power supply and distribution module architecture - Google Patents
Optimal configuration method for Hall thruster power supply and distribution module architecture Download PDFInfo
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- CN111648930B CN111648930B CN202010427183.0A CN202010427183A CN111648930B CN 111648930 B CN111648930 B CN 111648930B CN 202010427183 A CN202010427183 A CN 202010427183A CN 111648930 B CN111648930 B CN 111648930B
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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
- F03H1/0006—Details applicable to different types of plasma thrusters
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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
- F03H1/0006—Details applicable to different types of plasma thrusters
- F03H1/0018—Arrangements or adaptations of power supply systems
-
- 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
- F03H1/0062—Electrostatic ion thrusters grid-less with an applied magnetic field
- F03H1/0075—Electrostatic ion thrusters grid-less with an applied magnetic field with an annular channel; Hall-effect thrusters with closed electron drift
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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 invention provides an optimal configuration method for a power supply and distribution power module framework of a Hall thruster, wherein the Hall thruster adopts a self-excitation wiring mode, namely, an excitation loop and an anode loop of the Hall thruster are connected in series; the power module of the power processing unit PPU of the Hall thruster comprises: the PPU anode power supply module and the PPU cathode power supply module; the power processing unit PPU is matched with the Hall thruster for use and is a power supply single machine of the Hall thruster. The configuration method simplifies the number and design of the modules of the whole PPU of the Hall thruster, reduces the class of the power supply, further reduces the volume and the weight, and simultaneously reduces the complexity and the implementation cost of the PPU design. The invention can carry out the system design and the modular design of products, and the PPU can be flexibly configured into the maximum or minimum module number so as to meet the task requirements of different models.
Description
Technical Field
The invention relates to the field of thruster power processing units, in particular to an optimal configuration method for a Hall thruster power supply and distribution module framework.
Background
The Hall thruster is a complex system with multiple components working in a coordinated mode, a Power Processing Unit (PPU) is used as energy power input of the Hall thruster, and the PPU needs to provide power supply power modules with different specifications to supply electric energy according to time sequence. The PPU internal power module integrated coupling design and reasonable architecture configuration of the electric propulsion system ensure the optimal design of the PPU structure, function and performance.
The Hall thruster is one of the most widely used electric thrusters at present, and has the advantages of high thrust density, high specific impulse, simple structure and the like. In view of the wide application prospect of the Hall thruster, all countries in the world strive to develop the PPU matched with the Hall thruster. Compared with the traditional chemical propulsion system, the Hall electric propulsion system introduces electric energy, so that the PPU matched with the Hall thruster is very critical.
The Hall thruster is a complex single machine which is cooperatively operated by a plurality of components (four key components, namely an anode, an excitation coil, a cathode ignition electrode and a cathode heating wire), and the PPU is required to provide power supply capacities with different specifications according to the working characteristics of the components of the Hall thruster. The traditional PPU internal power module framework configuration is composed of an anode power supply module, a cathode ignition power supply module, a cathode heating power supply module and an excitation power supply module. The traditional PPU framework has more power modules, the whole machine has large volume and heavy weight, and the requirements of the current satellite platform on smaller mass and volume can not be met. Therefore, the optimal configuration method for the Hall thruster power supply and distribution module architecture is invented. The configuration method of the architecture is matched with a self-excitation ignition mode of the Hall thruster under the conditions of ensuring the reliability and safety of the system, reasonable and effective product design and feasible engineering implementation, so that the number of power modules in the PPU is reasonably simplified, and the space and the quality of a spacecraft are greatly saved.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide an optimal configuration method for a Hall thruster power supply and distribution module architecture.
The Hall thruster provided by the invention adopts a self-excitation wiring mode, namely, a Hall thruster excitation loop is connected with an anode loop in series;
the power module of the power processing unit PPU of the Hall thruster comprises: the PPU anode power supply module and the PPU cathode power supply module;
the power processing unit PPU is matched with the Hall thruster for use and is a power supply single machine of the Hall thruster.
Preferably, the hall thruster adopts a self-excitation ignition mode, that is, the positive end of the hall thruster excitation coil is connected with the cathode common ground, and the negative end of the hall thruster excitation coil is connected with the negative end of the anode power supply.
Preferably, the anode power module of the PPU supplies power to an anode assembly inside the hall thruster, and provides a constant voltage source output characteristic, and meanwhile, the output voltage of the anode power module is connected to the cathode ignition electrode of the hall thruster through an LRC filter network, so as to provide an initial ignition voltage required by cathode ignition.
Preferably, the PPU cathode power module supplies power to a cathode assembly (including a cathode ignition electrode and a cathode heating wire) inside the hall electric thruster and is an output characteristic of the constant current source, and the PPU cathode power module is composed of a cathode heating power supply and a cathode ignition power supply.
Preferably, the PPU cathode power module integrates the ignition power low voltage part with the cathode heating power, and the ignition power high voltage part integrates with the anode power, so that the PPU internal power module does not need to be configured with the cathode ignition power module separately.
Preferably, the anode power module of the PPU supplies power to the excitation coil of the Hall thruster, and the independent excitation loop is eliminated by adopting the self-excitation loop, so that the excitation power module does not need to be configured independently in the internal power module of the PPU.
Preferably, D1 and D2 are output isolation diodes of the PPU power module, and prevent the impact stress of the instantaneous high voltage of the hall thruster ignition on components at the output end of the PPU power module from being too large.
Preferably, the PPU cathode power supply module outputs a positive and negative anti-parallel diode D1, and an output positive terminal is connected in series with a diode D2;
the negative terminal of D1 is connected with the negative terminal of D2, the positive terminal of D1 is connected with the negative terminal of a resistor R3 in the RC resistance-capacitance network, and the positive terminal of D2 is connected with the output positive terminal of the PPU cathode power supply module.
Preferably, R1, R2, R3 and C1 are RC.
Preferably, the positive terminal of R1 is connected to the positive terminal of the PPU anode power supply module, the negative terminal of R1 is connected to the positive terminal of R2, the negative terminal of R2 and the negative terminal of C1 are connected to the negative terminal of the PPU cathode power supply module, the positive terminal of R2 is connected to the positive terminal of R3 and the positive terminal of C1, and the negative terminal of R3 is connected to the positive terminal of D1.
Compared with the prior art, the invention has the following beneficial effects:
1) according to the power module configuration for power supply and distribution of the Hall thruster, only 2 power supply modules are adopted for power supply of the thruster, the number and design of the whole power processing unit modules of the Hall thruster are simplified, the class of power supply sources is reduced, the size and the weight are further reduced, and meanwhile the complexity and the implementation cost of the power supply and distribution unit are reduced.
2) The low-voltage part of the ignition power supply is integrated with the cathode heating power supply, the high-voltage part of the ignition power supply is integrated with the anode power supply, and the PPU framework does not need to be separately configured with an independent ignition power supply module. The anode power supply supplies power to the magnetic coil of the thruster, an independent magnetic coil circuit is eliminated, and the PPU framework does not need to be separately configured with an excitation power supply module, so that the integrated coupling design is realized.
3) And optimizing and innovating the system design and the modular design of the product, so that the PPU is flexibly configured into the maximum or minimum module number to meet the task requirements of different models.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
fig. 1 is a schematic diagram of an optimized configuration of a hall thruster power supply and distribution power module architecture provided by the invention.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
The Hall thruster provided by the invention adopts a self-excitation wiring mode, namely, a Hall thruster excitation loop is connected with an anode loop in series;
the power module of the power processing unit PPU of the Hall thruster comprises: the PPU anode power supply module and the PPU cathode power supply module;
the power processing unit PPU is matched with the Hall thruster for use and is a power supply single machine of the Hall thruster.
Specifically, the hall thruster adopts a self-excitation ignition mode, that is, the positive end of the hall thruster excitation coil is connected with the cathode common ground, and the negative end of the hall thruster excitation coil is connected with the negative end of the anode power supply.
Specifically, an anode power supply module of the PPU supplies power to an anode assembly inside the Hall thruster and provides a constant voltage source output characteristic, and meanwhile, the output voltage of the anode power supply module is connected to a cathode ignition electrode of the Hall thruster through an LRC filter network so as to provide an initial ignition voltage required by cathode ignition.
Specifically, the PPU cathode power supply module supplies power for a cathode assembly (comprising a cathode ignition electrode and a cathode heating wire) in the Hall electric thruster and is a constant current source output characteristic, and the PPU cathode power supply module is composed of a cathode heating power supply and a cathode ignition power supply.
Specifically, the PPU's negative pole power module integrates ignition power low-voltage part and negative pole heating power, and ignition power high-voltage part integrates with the positive pole power for PPU internal power module need not alone reconfiguration negative pole ignition power module.
Specifically, the anode power supply module of the PPU supplies power to the excitation coil of the Hall thruster, and the independent excitation loop is eliminated by adopting the self-excitation loop, so that the excitation power supply module does not need to be configured independently in the internal power module of the PPU.
Specifically, D1 and D2 are output isolation diodes of the PPU power module, and therefore the impact stress of instantaneous high voltage of ignition of the Hall thruster on components at the output end of the PPU power module is prevented from being overlarge.
Specifically, the PPU cathode power supply module outputs a positive and negative anti-parallel diode D1, and outputs a positive series diode D2;
the negative terminal of D1 is connected with the negative terminal of D2, the positive terminal of D1 is connected with the negative terminal of a resistor R3 in the RC resistance-capacitance network, and the positive terminal of D2 is connected with the output positive terminal of the PPU cathode power supply module.
Specifically, R1, R2, R3 and C1 are RC networks, and when the PPU anode power module is started, during the anode voltage rising process, the output voltage of the PPU anode power module is output to the hall thruster cathode ignition electrode through the RC networks, so as to maintain the thruster cathode in a state of instant successful ignition.
Specifically, the positive terminal of R1 is connected with the positive terminal of the PPU anode power supply module, the negative terminal of R1 is connected with the positive terminal of R2, the negative terminal of R2 and the negative terminal of C1 are connected to the negative terminal of the PPU cathode power supply module in a common mode, the positive terminal of R2 is connected with the positive terminal of R3 and the positive terminal of C1, and the negative terminal of R3 is connected with the positive terminal of D1.
The present invention will be described more specifically below with reference to preferred examples.
Preferred example 1:
aiming at the defects in the prior art, the invention aims to provide an optimal configuration method for a Hall thruster power supply and distribution module architecture. The power supply and distribution framework is configured with the Hall thruster in a self-excitation wiring mode, namely, a Hall thruster excitation loop is connected with an anode loop in series. The power module of the Hall thruster PPU only comprises an anode power module and a cathode power module.
The Hall thruster adopts a self-excitation ignition mode, namely, the positive end (+) cathode of an excitation coil of the Hall thruster is connected with the common ground, and the negative end (-) of the excitation coil of the Hall thruster is connected with the negative end (-) of an anode power supply;
the PPU anode power supply module supplies power to an anode assembly inside the Hall thruster and outputs characteristics for a constant voltage source, and meanwhile, the output voltage of the anode power supply module is connected to a cathode ignition electrode of the Hall thruster through an LRC network (a filtering module, wherein the L (inductance), R (resistance) and C (capacitance) parameter values are designed according to the matching test conditions of different types of Hall thrusters and PPUs) so as to provide initial ignition voltage required by cathode ignition;
the PPU cathode power supply module supplies power to a cathode component (comprising a cathode ignition electrode and a cathode heating wire) in the Hall electric thruster and has the output characteristic of a constant current source, and the PPU cathode power supply module consists of a cathode heating power supply and a cathode ignition power supply which are integrated and coupled;
the PPU cathode power supply module integrates the low-voltage part of the ignition power supply and the cathode heating power supply, and integrates the high-voltage part of the ignition power supply and the anode power supply, so that the PPU internal power module does not need to be separately configured with the cathode ignition power supply module;
the PPU anode power supply module supplies power to a Hall thruster magnet exciting coil, and an independent excitation loop is eliminated by adopting a self-excitation loop, so that an excitation power supply module does not need to be configured independently in a PPU internal power module;
d1, D2 are PPU power module's output isolation diode, and the effect is that the impact stress of the high voltage in the twinkling of an eye that prevents the ignition of hall thruster to PPU power module output terminal components and parts is too big, and the concrete specification lectotype is designed according to hall thruster and PPU matching test condition.
The resistors R1, R2, R3 and the capacitor C1 are RC resistance-capacitance networks, and are used for outputting the output voltage of the anode power supply module to the cathode ignition electrode of the Hall thruster through the resistance-capacitance networks in the process of anode voltage rising when the PPU anode power supply module is started, so that the cathode of the thruster is maintained in a state of successful instant ignition.
Preferred example 2:
according to the optimal configuration method for the power supply and distribution module architecture of the hall thruster provided by the invention, as shown in fig. 1, the power module of the hall thruster PPU in the optimal configuration method only comprises an anode power module and a cathode power module.
Specifically, the Hall thruster adopts a self-excitation ignition mode, so that excitation current oscillation caused by oscillation of a discharge loop can be reduced, the positive end (+) cathode of the exciting coil of the Hall thruster is connected with the common ground, and the negative end (-) of the exciting coil of the thruster is connected with the negative end (-) of an anode power supply;
specifically, the PPU anode power supply module supplies power to an anode assembly inside the hall thruster and outputs characteristics of a constant voltage source, and meanwhile, the output voltage of the anode power supply module is connected to a hall thruster cathode ignition electrode through an LRC network (a filtering module, wherein L (inductance), R (resistance) and C (capacitance) parameter values are designed according to the matching test conditions of the hall thruster and the PPU) so as to provide an initial ignition voltage (generally 300V) required by cathode ignition;
specifically, PPU negative pole power module is the inside negative pole subassembly of hall electric thruster (containing negative pole ignition electrode and cathode heating wire) power supply, and for constant current source output characteristic, PPU negative pole power module comprises two parts of negative pole heating power and negative pole ignition power, and two parts integrate the coupling design.
Specifically, the PPU cathode power supply module integrates the low-voltage part of the ignition power supply and the cathode heating power supply, and the high-voltage part of the ignition power supply and the anode power supply, so that the PPU internal power module does not need to be configured with the cathode ignition power supply module independently.
Specifically, the PPU anode power supply module supplies power to a magnet exciting coil of the Hall thruster, and an independent excitation loop is eliminated by adopting a self-excitation loop, so that an excitation power supply module does not need to be configured independently in a PPU internal power module.
Specifically, D1, D2 are PPU power module's output isolation diode, and the effect is that the impact stress of the high voltage in the twinkling of an eye that prevents the ignition of hall thruster to PPU power module output terminal components and parts is too big, and specific specification lectotype is designed according to hall thruster and PPU matching test condition.
Specifically, after the cathode heating wire of the Hall thruster is powered for a period of time (generally 5 min-8 min), the relay inside the PPU cathode power module is closed, the cathode power supply is connected to the cathode ignition electrode, meanwhile, the PPU anode power module is started by a 'slow start' circuit, and in the step rising process of the anode voltage, the output voltage of the anode power module is output to the cathode ignition electrode of the Hall thruster through resistors R1, R2, R3 and a capacitor C1 resistor-capacitor network (the specific parameter values of the resistors R1, R2, R3 and the capacitor C1 are designed according to the matching test condition of the Hall thruster and the PPU), so that the stress level of internal components of the PPU and the instantaneous ignition impact of the thruster are effectively reduced, and the cathode of the thruster is enabled to be maintained in the state of instantaneous successful ignition.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
Those skilled in the art will appreciate that, in addition to implementing the systems, apparatus, and various modules thereof provided by the present invention in purely computer readable program code, the same procedures can be implemented entirely by logically programming method steps such that the systems, apparatus, and various modules thereof are provided in the form of logic gates, switches, application specific integrated circuits, programmable logic controllers, embedded microcontrollers and the like. Therefore, the system, the device and the modules thereof provided by the present invention can be considered as a hardware component, and the modules included in the system, the device and the modules thereof for implementing various programs can also be considered as structures in the hardware component; modules for performing various functions may also be considered to be both software programs for performing the methods and structures within hardware components.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (5)
1. An optimal configuration method for a power supply and distribution power module framework of a Hall thruster is characterized in that the Hall thruster adopts a self-excitation wiring mode, namely, an excitation loop of the Hall thruster is connected with an anode loop in series;
the power module of the power processing unit PPU of the Hall thruster comprises: the PPU anode power supply module and the PPU cathode power supply module;
the power processing unit PPU is matched with the Hall thruster for use and is a power supply single machine of the Hall thruster;
the positive and negative ends of the output of the PPU cathode power supply module are connected with a diode D1 in an anti-parallel mode, and the positive end of the output of the PPU cathode power supply module is connected with a diode D2 in series;
d1 and D2 are output isolation diodes of the PPU power module, so that the impact stress of instantaneous high voltage ignited by the Hall thruster on components at the output end of the PPU power module is prevented from being overlarge;
the low-voltage part of the ignition power supply and the cathode heating power supply are integrated by the cathode power supply module of the PPU, and the high-voltage part of the ignition power supply and the anode power supply are integrated, so that the cathode ignition power supply module does not need to be configured independently in the internal power module of the PPU;
the negative end of D1 is connected with the negative end of D2, the positive end of D1 is connected with the negative end of a resistor R3 in an RC resistance-capacitance network, and the positive end of D2 is connected with the output positive end of the PPU cathode power supply module;
r1, R2, R3 and C1 are RC resistance-capacitance networks, when the PPU anode power supply module is started, in the process of anode voltage rising, the output voltage of the PPU anode power supply module is output to a cathode ignition electrode of the Hall thruster through the resistance-capacitance networks, and the cathode of the thruster is enabled to be maintained in a state of successful instant ignition;
the positive end of the R1 is connected with the positive end of the PPU anode power supply module, the negative end of the R1 is connected with the positive end of the R2, the negative end of the R2 and the negative end of the C1 are connected to the negative end of the PPU cathode power supply module in a common mode, the positive end of the R2 is connected with the positive end of the R3 and the positive end of the C1, and the negative end of the R3 is connected with the positive end of the D1.
2. The optimal configuration method for the Hall thruster power supply and distribution module architecture according to claim 1, wherein the Hall thruster adopts a self-excitation ignition mode, that is, a positive end of a Hall thruster excitation coil is connected with a cathode common ground, and a negative end of the Hall thruster excitation coil is connected with a negative end of an anode power supply.
3. The optimal configuration method for the power supply and distribution module architecture of the hall thruster, as claimed in claim 1, wherein the anode power module of the PPU supplies power to an anode assembly inside the hall thruster to provide a constant voltage source output characteristic, and the output voltage of the anode power module is connected to the cathode ignition electrode of the hall thruster through an LRC filter network to provide an initial ignition voltage required for cathode ignition.
4. The optimal configuration method for the power supply and distribution module architecture of the hall thruster, as claimed in claim 1, wherein the PPU cathode power module supplies power to the hall electric thruster internal cathode assembly, which includes the cathode ignition electrode and the cathode heating wire, and the PPU cathode power module is composed of two parts, namely a cathode heating power supply and a cathode ignition power supply, and provides constant current source output characteristics.
5. The optimal configuration method for the Hall thruster power supply and distribution module architecture according to claim 1, wherein an anode power supply module of the PPU supplies power to a magnet exciting coil of the Hall thruster, and a self-excitation loop is adopted to eliminate an independent excitation loop, so that an excitation power supply module does not need to be configured independently in the PPU.
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| RU2741401C1 (en) * | 2020-01-29 | 2021-01-25 | Андрей Иванович Шумейко | Module with multichannel plasma propulsion system for small spacecraft |
| CN113202706A (en) * | 2021-04-25 | 2021-08-03 | 上海宇航***工程研究所 | Hall electric propulsion system for GEO (geostationary orbit) satellite |
| CN113202709A (en) * | 2021-05-17 | 2021-08-03 | 兰州空间技术物理研究所 | Hybrid excitation working mode of Hall electric thruster |
| US11649072B1 (en) * | 2022-05-05 | 2023-05-16 | Maxar Space Llc | Power processing unit (PPU) and electric propulsion system (EPS) for spacecraft |
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| WO1997037519A1 (en) * | 1996-04-01 | 1997-10-09 | Keldysh Research Center | Plasma accelerator |
| CN103917034A (en) * | 2014-03-17 | 2014-07-09 | 上海空间推进研究所 | Ignition circuit with hollow cathode |
| JP2019065703A (en) * | 2017-09-28 | 2019-04-25 | 株式会社Ihi | Hall thruster |
| FR3071886A1 (en) * | 2017-10-03 | 2019-04-05 | Centre National D'etudes Spatiales | TWO-STAGE HALL EFFECTOR |
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