A universal modular configuration structure of an electric propulsion subsystem

Abstract

According to the electric propulsion subsystem principle diagram and in combination with the specific structural forms of different satellite platforms, the present invention proposes a universal modular configuration structure of the electric propulsion subsystem. The universal modular configuration structure of the electric propulsion subsystem proposed in the present invention does not occupy the main line of satellite development, has a clear principle, a simple connection relationship, and a small space occupied by the equipment. The related equipment is uniformly arranged on a structural plate, and the matching adaptation of the electric propulsion subsystem equipment to the mechanical interface, electrical interface and thermal interface of the whole satellite is achieved at the same time, which is convenient for pipeline welding and forward testing of the electric propulsion subsystem. On this basis, according to the different satellite structural design forms, the electric propulsion subsystem configures equipment installation, pipeline welding, and cable connection on the structural plate of the corresponding configuration, thereby realizing a modular layout.

Description

Technical Field

[0001] The invention relates to an electric propulsion subsystem structure. Background Art

[0002] In recent years, with the improvement of traditional satellite production capacity, the reduction of production costs, and the gradual inclination of advanced science and technology to the field of satellite development, the satellite application model has also changed, and new requirements have been put forward for the various business capabilities of satellites. At the same time, the construction of low-orbit satellite constellations is in the ascendant. The number of satellites in common low-orbit satellite constellations is usually hundreds or even thousands, achieving seamless global coverage. All these current situations have put forward higher requirements for satellite development capabilities and output.

[0003] The electric propulsion subsystem can realize the satellite's orbit change and on-orbit position maintenance. It has the advantages of large specific impulse, high propellant utilization efficiency and no pollution, and has the conditions for mass production and development. The traditional electric propulsion subsystem is complex in structure and is usually arranged on multiple structural plates of the satellite. There is a problem of occupying too much satellite layout space, and the pipe welding related work needs to be carried out in the satellite development and assembly stage after the equipment is installed on the satellite. Once a problem occurs in the welding, the relevant equipment and pipelines need to be removed separately, and the equipment needs to be repaired before the satellite is installed to complete the pipeline welding. At the same time, it is not convenient to test the electric propulsion subsystem. If design or quality problems are found in the later stage of satellite development, it may be impossible to repair it. The traditional electric propulsion layout method occupies the main line of development and is not conducive to pipeline welding and troubleshooting. Summary of the invention

[0004] The technical problem solved by the present invention is: to overcome the shortcomings of the prior art, the present invention proposes a universal modular configuration structure of an electric propulsion subsystem, which does not occupy the main line of satellite development, has a clear principle, a simple connection relationship, and a small equipment footprint. At the same time, it realizes the matching and adaptation of the electric propulsion subsystem equipment with the mechanical interface, electrical interface and thermal interface of the whole satellite, which is convenient for pipeline welding and forward testing of the electric propulsion subsystem.

[0005] The technical solution adopted by the present invention is: a universal modular configuration structure of an electric propulsion subsystem, comprising: the electric propulsion subsystem and pipelines are arranged on a structural plate;

[0006] The electric propulsion subsystem includes: a first xenon gas bottle, a second xenon gas bottle, a power processing unit, a pressure regulating module, a first flow control module, a second flow control module, a first self-latching valve, a second self-latching valve, a third self-latching valve, a fourth self-latching valve, a high-pressure pressure sensor, a first additional discharge valve, a second additional discharge valve, a third additional discharge valve, a first cold air thruster, a second cold air thruster, a third cold air thruster, a fourth cold air thruster, a fifth cold air thruster, a sixth cold air thruster, a seventh cold air thruster, an eighth cold air thruster, a Hall thruster and an adapter electrical connector bracket;

[0007] The first xenon gas bottle, the second xenon gas bottle, the power processing unit, the pressure regulating module, the first flow control module, the second flow control module, the first self-latching valve, the second self-latching valve, the third self-latching valve, the fourth self-latching valve, the high-pressure pressure sensor, and the adapter electrical connector bracket are arranged on one side surface of the structural plate;

[0008] The first addition and discharge valve, the second addition and discharge valve, the third addition and discharge valve, the first cold air thruster, the second cold air thruster, the third cold air thruster, the fourth cold air thruster, the fifth cold air thruster, the sixth cold air thruster, the seventh cold air thruster, the eighth cold air thruster, and the Hall thruster are arranged on the other side surface of the structural plate;

[0009] The first xenon cylinder, the second xenon cylinder, the first to fourth self-locking valves, the high-pressure pressure sensor, the second addition and discharge valve, the first to eighth cold air thrusters form a first branch, and the various devices are connected through pipelines;

[0010] The first xenon cylinder, the pressure regulating module, the first flow control module, the second flow control module, the first adding and discharging valve, the third adding and discharging valve, and the Hall thruster form a second branch, and each device is connected by a pipeline;

[0011] Balancing is performed so that the mass center of the electric propulsion subsystem universal modular configuration structure and the mass center of the first xenon cylinder are located on the Z axis, the Z axis points from the center point of the first frame of the structural plate to the center point of the second frame, and the first frame is parallel to the second frame;

[0012] The first xenon gas bottle is filled with the propellant required for the satellite's on-orbit operation. The first xenon gas bottle replenishes gas for the second xenon gas bottle on the first branch and directly supplies gas to the second branch, thereby realizing the on-orbit ignition of the first to eighth cold air thrusters and the Hall thrusters respectively.

[0013] Furthermore, in the first branch, the first xenon bottle outputs xenon propellant, and the cold air system is replenished for the second xenon bottle through the first self-locking valve and the second self-locking valve connected in series. The xenon gas in the second xenon bottle provides propellant to the first to fourth cold air thrusters and the fifth to eighth cold air thrusters through the third self-locking valve and the fourth self-locking valve, respectively, to realize the on-orbit cold air ignition of the cold air thrusters. The high-pressure pressure sensor is connected to the second xenon bottle and the second self-locking valve to measure and obtain propellant pressure data and monitor the pressure status of the electric propulsion subsystem pipeline; the second filling and discharging valve is connected to the second xenon bottle to pre-fill the second xenon bottle with propellant.

[0014] Furthermore, in the second branch, the first xenon gas bottle outputs xenon propellant, and the high-pressure xenon gas propellant is converted into low-pressure xenon gas through the pressure regulating module, and the propellant is provided to the Hall thruster through the first flow control module and the second flow control module respectively, so as to realize the on-orbit electric propulsion ignition of the Hall thruster. The first adding and discharging valve is connected to the first xenon gas bottle, and the third adding and discharging valve is connected to the pressure regulating module. The first adding and discharging valve is used to pre-fill the first xenon gas bottle with propellant, and the third adding and discharging valve is used to replenish the propellant in the pipeline after the outlet of the pressure regulating module.

[0015] Furthermore, the material of the pipeline is titanium tube, and the pipeline is connected to the first xenon gas bottle, the second xenon gas bottle, the pressure regulating module, the high-pressure pressure sensor, the first cold air thruster to the eighth cold air thruster, and the Hall thruster by threaded connection; the pipeline is connected to the first flow control module, the second flow control module, the first self-locking valve to the fourth self-locking valve, and the first adding and discharging valve to the third adding and discharging valve by welding.

[0016] Furthermore, the power processing unit realizes electrical signal management and control. The power processing unit is connected to the pressure regulating module, the first flow control module, the second flow control module, the first to fourth self-locking valves, the high-pressure pressure sensor, the first to eighth cold air thrusters and the Hall thruster through cables. The cables are aggregated and installed on the adapter electrical connector bracket. The cables aggregated on the adapter electrical connector bracket realize the electrical connection relationship between the electric propulsion subsystem and the entire satellite through the form of electrical connector plug-in.

[0017] Furthermore, the electric propulsion subsystem realizes thermal control through thermal control multiple layers, heating plates, thermistors, and OSR plates, and all thermal control cables are connected to the power processing unit through electrical connectors to realize control of the thermal control cables.

[0018] Furthermore, the shape of the structural plate is adjusted according to different satellite configurations, and the mechanical connection between the structural plate and other satellite structures is achieved through screw connection.

[0019] Furthermore, the structural panel is an aluminum-skinned aluminum honeycomb sandwich panel.

[0020] The advantages of the present invention compared with the prior art are:

[0021] (1) The modular configuration proposed in the present invention has a clear principle, a simple connection relationship, and a small space occupied by the equipment. At the same time, the electric propulsion subsystem equipment can be matched and adapted to the mechanical interface, electrical interface, and thermal interface of the entire satellite, which is convenient for pipeline welding. The overall installation and testing of the electric propulsion subsystem can be achieved through integration. If any problems are found, they can be tested during the development stage of the electric propulsion module without the need to install the entire satellite before testing. The electric propulsion subsystem test can be moved forward to the development stage of the electric propulsion module, reducing the number of satellite mainline test items.

[0022] (2) The existing satellite electric propulsion subsystem occupies the main line of satellite development. Pipe welding related work needs to be carried out in the satellite development and assembly stage after the equipment is installed on the satellite. Once a problem occurs in the welding, the relevant equipment and pipelines need to be removed separately. After the equipment is troubleshooted, the satellite can be installed and the pipeline welding can be completed. The modular configuration proposed in the present invention can achieve the modular development of the electric propulsion subsystem without occupying the main line of satellite development, and is convenient for mass production, and has a low-cost advantage in the actual development process.

[0023] (3) The modular configuration proposed in the present invention arranges all the related equipment and pipelines on a structural plate. Only screws and electrical connectors are used to achieve the matching and adaptation between the electric propulsion subsystem and the mechanical interface, electrical interface and thermal interface of the entire satellite, thereby realizing a modular layout. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is a schematic diagram of the equipment and pipeline layout of an electric propulsion subsystem of the present invention;

[0025] Figure 2 It is a front schematic diagram of the trapezoidal structure plate equipment and pipeline layout of the present invention;

[0026] Figure 3 It is a schematic diagram of the back side of the trapezoidal structure plate equipment and pipeline layout of the present invention;

[0027] Figure 4 It is a front view schematic diagram of the rectangular structure plate equipment and pipeline layout of the present invention;

[0028] Figure 5 It is a schematic diagram of the reverse side of the rectangular structure plate equipment and pipeline layout of the present invention. DETAILED DESCRIPTION

[0029] The present invention is described with reference to the accompanying drawings.

[0030] The present invention proposes a universal modular configuration structure of an electric propulsion subsystem, and the layout of the electric propulsion subsystem equipment and pipelines is as follows: Figure 1 As shown in the figure, the electric propulsion subsystem body coordinate system (O-XYZ) is established and defined as follows:

[0031] Coordinate origin O: Figure 2 As shown, the center point of the lower bottom edge of the trapezoid of the structural plate 101;

[0032] +Z axis: Figure 2 As shown, the +Z direction is the direction from the lower base of the trapezoid of the structural plate 101 to the upper base;

[0033] +X axis: Figure 1 As shown, the +X direction vertical structural plate 101 plane points out of the paper;

[0034] +Y axis: Figure 2 As shown, the +Z axis and +X axis conform to the right-hand rule.

[0035] All equipment and pipelines 201 of the electric propulsion subsystem are arranged on a structural plate 101.

[0036] The electric propulsion subsystem includes: a first xenon gas cylinder 1, a second xenon gas cylinder 2, a power processing control unit 3, a pressure regulating module 4, a first flow control module 5, a second flow control module 6, a first self-locking valve 7, a second self-locking valve 8, a third self-locking valve 9, a fourth self-locking valve 10, a high-pressure pressure sensor 11, a first additional discharge valve 12, a second additional discharge valve 13, a third additional discharge valve 14, a first cold air thruster 15, a second cold air thruster 16, a third cold air thruster 17, a fourth cold air thruster 18, a fifth cold air thruster 19, a sixth cold air thruster 20, a seventh cold air thruster 21, an eighth cold air thruster 22, a Hall thruster 23, a pipeline 201 and an adapter electrical connector bracket 202.

[0037] The layout of the electric propulsion subsystem equipment and pipelines 201 is as follows Figure 1 As shown in the figure, the installation position, connection relationship and configuration of the electric propulsion subsystem equipment and pipelines are as follows Figure 2 , Figure 3 , Figure 4 , Figure 5 shown.

[0038] A first xenon gas cylinder 1, a second xenon gas cylinder 2, a power processing unit 3, a pressure regulating module 4, a first flow control module 5, a second flow control module 6, a first self-latching valve 7, a second self-latching valve 8, a third self-latching valve 9, a fourth self-latching valve 10, a high-pressure pressure sensor 11, and an adapter electrical connector bracket 202 are arranged on one side surface of the structural plate 101;

[0039] The first exhaust valve 12, the second exhaust valve 13, the third exhaust valve 14, the first cold air thruster 15, the second cold air thruster 16, the third cold air thruster 17, the fourth cold air thruster 18, the fifth cold air thruster 19, the sixth cold air thruster 20, the seventh cold air thruster 21, the eighth cold air thruster 22, and the Hall thruster 23 are arranged on the other side surface of the structural plate 101;

[0040] The first xenon cylinder 1, the second xenon cylinder 2, the first to fourth self-locking valves 7 to 10, the high-pressure pressure sensor 11, the second addition and discharge valve 13, the first to eighth cold air thrusters 15 to 22 form a first branch, and the various devices are connected through pipelines 201;

[0041] The first xenon cylinder 1, the pressure regulating module 4, the first flow control module 5, the second flow control module 6, the first adding and discharging valve 12, the third adding and discharging valve 14, and the Hall thruster 23 form a second branch, and each device is connected through a pipeline 201;

[0042] The first xenon gas bottle 1 is filled with propellant required for the on-orbit operation of the satellite. The first xenon gas bottle 1 replenishes gas for the second xenon gas bottle 2 on the first branch and directly supplies gas to the second branch, thereby realizing the on-orbit ignition of the first cold air thruster 15 to the eighth cold air thruster 22 and the Hall thruster 23 respectively.

[0043] Through balancing, the center of mass of the universal modular configuration structure of the entire electric propulsion subsystem and the center of mass of the first xenon bottle 1 are located on the Z axis. With the loss of propellant in the first xenon bottle 1, the reduction in the weight of the pre-filled propellant does not affect the center of mass position of the electric propulsion subsystem. This is a reasonable layout plan.

[0044] In the first branch, the first xenon bottle 1 outputs xenon propellant, and the second xenon bottle 2 is replenished with air in the cold air system through the first self-locking valve 7 and the second self-locking valve 8 connected in series. The xenon gas in the second xenon bottle 2 provides propellant to the first cold air thruster 15 to the fourth cold air thruster 18 and the fifth cold air thruster 19 to the eighth cold air thruster 22 respectively through the third self-locking valve 9 and the fourth self-locking valve 10, so as to realize the on-orbit cold air ignition of the cold air thruster. The high-pressure pressure sensor 11 is connected with the second xenon bottle 2 and the second self-locking valve 8 to measure and obtain the propellant pressure data and monitor the pressure status of the electric propulsion subsystem pipeline; the second filling and discharging valve 13 is connected with the second xenon bottle 2 to pre-fill the second xenon bottle 2 with propellant.

[0045] In the second branch, the first xenon gas cylinder 1 outputs xenon propellant, and the high-pressure xenon propellant (gas pressure greater than 15Mpa) is converted into low-pressure xenon gas (gas pressure less than 2Mpa) through the pressure regulating module 4, and the propellant is provided to the Hall thruster 23 through the first flow control module 5 and the second flow control module 6 respectively, so as to realize the on-orbit electric propulsion ignition of the Hall thruster 23. The first adding and discharging valve 12 is connected with the first xenon gas cylinder 1, and the third adding and discharging valve 14 is connected with the pressure regulating module 4. The first adding and discharging valve 12 is used to pre-fill the first xenon gas cylinder 1 with propellant, and the third adding and discharging valve 14 is used to supplement the propellant for the pipeline after the outlet of the pressure regulating module 4.

[0046] The pipeline 201 is a titanium tube, and the connection forms with other equipment are divided into welding and screw connection. The specific design state is: the pipeline 201 is connected to the first xenon bottle 1, the second xenon bottle 2, the pressure regulating module 4, the high-pressure pressure sensor 11, the first cold air thruster 15 to the eighth cold air thruster 22, and the Hall thruster 23 by threaded connection; the pipeline 201 is connected to the first flow control module 5, the second flow control module 6, the first self-locking valve 7 to the fourth self-locking valve 10, and the first adding and discharging valve 12 to the third adding and discharging valve 14 by welding.

[0047] The devices with electrical connection relationship in the electric propulsion subsystem are connected through universal cables: the power processing unit 3 realizes electrical signal management and control, and the power processing unit 3 is connected to the pressure regulating module 4, the first flow control module 5, the second flow control module 6, the first self-locking valve 7 to the fourth self-locking valve 10, the high-pressure pressure sensor 11, the first cold air thruster 15 to the eighth cold air thruster 22 and the Hall thruster 23 through cables. The cables are aggregated and installed on the adapter electrical connector bracket 202. The cables aggregated on the adapter electrical connector bracket 202 realize the electrical connection relationship between the electric propulsion subsystem and the entire satellite through the form of electrical connector plug-in.

[0048] A single structural board is used to implement thermal control of the electric propulsion subsystem related equipment and pipelines, and the interface matching with the whole satellite thermal control is completed through single-board thermal control. In terms of electrical signal transmission, with the power processing unit 3 as the core, the electric propulsion subsystem realizes thermal control through thermal control multilayer, heating plate, thermistor, and OSR plate. All thermal control cables are aggregated to the power processing unit 3 through electrical connectors to realize the control of thermal control cables.

[0049] The structural plate 101 is a complete satellite structural plate. The design configuration of the structural plate can be adjusted according to the different satellite configuration designs, such as trapezoidal, rectangular, etc. Figure 2 , Figure 3 In order to use the trapezoidal structural plate to complete the layout of the electric propulsion subsystem equipment and pipelines, Figure 4 , Figure 5 In order to use a rectangular structural plate to complete the layout of the electric propulsion subsystem equipment and pipelines (if the structural plate 101 is a trapezoid, the +Z direction points from the center point of one long side of the structural plate 101 to the center point of the parallel frame of the above long side), the mechanical connection between the structural plate 101 and other satellite structures is achieved through screw connection. Therefore, all the equipment and pipelines of the electric propulsion subsystem are installed on a structural plate, and only through screws and electrical connectors, the matching and adaptation of the mechanical interface, electrical interface and thermal interface of the electric propulsion subsystem and the entire satellite are achieved, thereby realizing a modular layout with certain versatility. The material of the structural plate 101 is an aluminum skin aluminum honeycomb sandwich plate, which can be designed according to trapezoidal, rectangular and other configurations, and has certain versatility.

[0050] Depending on the different structural design forms of the satellite, the electric propulsion subsystem will configure equipment installation, pipeline welding, and cable connections on structural plates of corresponding configurations, such as trapezoidal, rectangular, etc., thereby achieving a modular layout.

[0051] Parts of the present invention that are not described in detail belong to the common knowledge of those skilled in the art.

Claims

1. A universal modular configuration structure of an electric propulsion subsystem, characterized in that: include: The electric propulsion subsystem and pipeline (201) are arranged on the structural plate (101); The electric propulsion subsystem comprises: a first xenon gas cylinder (1), a second xenon gas cylinder (2), a power processing unit (3), a pressure regulating module (4), a first flow control module (5), a second flow control module (6), a first self-latching valve (7), a second self-latching valve (8), a third self-latching valve (9), a fourth self-latching valve (10), a high-pressure pressure sensor (11), a first additional discharge valve (12), a second additional discharge valve (13), a third additional discharge valve (14), a first cold air thruster (15), a second cold air thruster (16), a third cold air thruster (17), a fourth cold air thruster (18), a fifth cold air thruster (19), a sixth cold air thruster (20), a seventh cold air thruster (21), an eighth cold air thruster (22), a Hall thruster (23) and an adapter electrical connector bracket (202); A first xenon gas bottle (1), a second xenon gas bottle (2), a power processing unit (3), a pressure regulating module (4), a first flow control module (5), a second flow control module (6), a first self-latching valve (7), a second self-latching valve (8), a third self-latching valve (9), a fourth self-latching valve (10), a high-pressure pressure sensor (11), and an adapter electrical connector bracket (202) are arranged on a side surface of the structural plate (101); A first discharge adding valve (12), a second discharge adding valve (13), a third discharge adding valve (14), a first cold air thruster (15), a second cold air thruster (16), a third cold air thruster (17), a fourth cold air thruster (18), a fifth cold air thruster (19), a sixth cold air thruster (20), a seventh cold air thruster (21), an eighth cold air thruster (22), and a Hall thruster (23) are arranged on the other side surface of the structural plate (101); The first xenon gas bottle (1), the second xenon gas bottle (2), the first self-locking valve (7) to the fourth self-locking valve (10), the high-pressure pressure sensor (11), the second addition and discharge valve (13), the first cold air thruster (15) to the eighth cold air thruster (22) form a first branch circuit, and the various devices are connected through pipelines (201); The first xenon cylinder (1), the pressure regulating module (4), the first flow control module (5), the second flow control module (6), the first adding and discharging valve (12), the third adding and discharging valve (14), and the Hall thruster (23) form a second branch, and the various devices are connected via a pipeline (201); Balancing is performed so that the center of mass of the electric propulsion subsystem universal modular configuration structure and the center of mass of the first xenon cylinder (1) are located on a Z axis, the Z axis points from the center point of a first frame of the structural plate (101) to the center point of a second frame, the first frame being parallel to the second frame; The first xenon gas bottle (1) is filled with propellant required for the on-orbit operation of the satellite. The first xenon gas bottle (1) replenishes gas for the second xenon gas bottle (2) on the first branch and directly supplies gas to the second branch, thereby respectively realizing on-orbit ignition of the first cold air thruster (15) to the eighth cold air thruster (22) and the Hall thruster (23).

2. A universal modular configuration structure of an electric propulsion subsystem according to claim 1, characterized in that: In the first branch, the first xenon bottle (1) outputs xenon propellant, and the second xenon bottle (2) is supplied with air through the first self-locking valve (7) and the second self-locking valve (8) connected in series. The xenon in the second xenon bottle (2) is supplied with propellant to the first cold air thruster (15) to the fourth cold air thruster (18) and the fifth cold air thruster (19) to the eighth cold air thruster (22) through the third self-locking valve (9) and the fourth self-locking valve (10), respectively, to realize the cold air ignition of the cold air thruster on orbit. The high-pressure pressure sensor (11) is connected to the second xenon bottle (2) and the second self-locking valve (8), and the propellant pressure data is measured to monitor the pressure state of the electric propulsion subsystem pipeline. The second filling and discharging valve (13) is connected to the second xenon bottle (2), and the second xenon bottle (2) is pre-filled with propellant.

3. The universal modular configuration structure of an electric propulsion subsystem according to claim 1, characterized in that: In the second branch, the first xenon gas cylinder (1) outputs xenon gas propellant, and the high-pressure xenon gas propellant is converted into low-pressure xenon gas through the pressure regulating module (4), and the propellant is provided to the Hall thruster (23) through the first flow control module (5) and the second flow control module (6), respectively, so as to realize the on-orbit electric propulsion ignition of the Hall thruster (23). The first adding and discharging valve (12) is connected to the first xenon gas cylinder (1), and the third adding and discharging valve (14) is connected to the pressure regulating module (4). The first adding and discharging valve (12) is used to pre-fill the first xenon gas cylinder (1) with propellant, and the third adding and discharging valve (14) is used to replenish the propellant in the pipeline after the outlet of the pressure regulating module (4).

4. The universal modular configuration structure of an electric propulsion subsystem according to claim 1, characterized in that: The material of the pipeline (201) is a titanium tube. The pipeline (201) is connected to the first xenon gas bottle (1), the second xenon gas bottle (2), the pressure regulating module (4), the high-pressure pressure sensor (11), the first cold air thruster (15) to the eighth cold air thruster (22), and the Hall thruster (23) by threaded connection; the pipeline (201) is connected to the first flow control module (5), the second flow control module (6), the first self-locking valve (7) to the fourth self-locking valve (10), and the first adding and discharging valve (12) to the third adding and discharging valve (14) by welding.

5. The universal modular configuration structure of an electric propulsion subsystem according to claim 1, characterized in that: The power processing unit (3) realizes electrical signal management and control. The power processing unit (3) is connected to the pressure regulating module (4), the first flow control module (5), the second flow control module (6), the first self-locking valve (7) to the fourth self-locking valve (10), the high-pressure pressure sensor (11), the first cold air thruster (15) to the eighth cold air thruster (22) and the Hall thruster (23) through cables. The cables are aggregated and installed on the transfer electrical connector bracket (202). The cables aggregated on the transfer electrical connector bracket (202) realize the electrical connection relationship between the electric propulsion subsystem and the entire satellite in the form of electrical connector plug-in.

6. The universal modular configuration structure of an electric propulsion subsystem according to claim 1, characterized in that: The electric propulsion subsystem realizes thermal control through thermal control multiple layers, heating plates, thermistors, and OSR plates. All thermal control cables are connected to the power processing unit (3) through electrical connectors to realize control of the thermal control cables.

7. The universal modular configuration structure of an electric propulsion subsystem according to claim 1, characterized in that: The shape of the structural plate (101) is adjusted according to different satellite configurations, and the mechanical connection between the structural plate (101) and other satellite structures is achieved through screw connection.

8. The universal modular configuration structure of an electric propulsion subsystem according to claim 1, characterized in that: The structural panel (101) is an aluminum-skinned aluminum honeycomb sandwich panel.

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