A space vehicle multi-functional electric propulsion system

Abstract

The application discloses a multifunctional electric propulsion system of a space vehicle, and relates to the technical field of space propulsion systems.The multifunctional electric propulsion system comprises a gas cylinder module, a fluid management module and a thruster module; the gas cylinder module is connected downstream to the fluid management module, and the fluid management module is connected downstream to the thruster module; and the thruster module comprises a Hall thruster, an electric heating type thruster and a cold gas thruster.The multifunctional electric propulsion system utilizes low-cost working gas, integrates the attitude control and orbit control systems of a satellite through modular design and heat flow design, reduces the difficulty of design and manufacture of the satellite, reduces the launch cost of the satellite, and simultaneously realizes intelligent control of the satellite through the integrated control system combined with orbit control algorithms.

Description

Technical Field

[0001] This invention relates to the field of space propulsion system technology, and more specifically, to a multi-functional electric propulsion system for spacecraft. Background Technology

[0002] Multifunctional propulsion systems belong to the category of space electric propulsion systems. They use electrical energy to propel spacecraft, offering advantages over traditional chemical propulsion, including lighter weight, higher specific impulse, smaller size, and lower development costs. Current electric propulsion technologies include electrothermal propulsion, electrostatic propulsion, and electromagnetic propulsion.

[0003] Electrothermal propulsion uses electrical energy to heat the working fluid, causing the gas to expand and be accelerated out through a nozzle. It includes resistance heating propulsion and electric arc heating propulsion.

[0004] Electrostatic propulsion involves ionizing the propellant into charged particles, which are then accelerated and ejected through an electrostatic field. It mainly includes Hall thrusters, ion thrusters, and electronic fuel injection thrusters.

[0005] Electromagnetic propulsion involves ionizing the propellant to form charged particles, which are then accelerated and ejected under the superposition of electric and magnetic fields. This type of propulsion mainly includes: variable specific impulse plasma thrusters, magneto-plasma thrusters, and pulsed plasma thrusters.

[0006] As the number of electric propulsion systems entering orbit increases and the technology matures, the demand for multifunctional, modular, high thrust-to-weight ratio, and compact propulsion systems becomes increasingly important. Therefore, multifunctional propulsion systems are gradually entering the market.

[0007] Currently, there are multi-functional propulsion systems based on ammonia and multi-working-propellant systems on the market. Considering the large weight of spacecraft that require orbital maneuverability, the working propellant accounts for the majority of the propulsion. To achieve the multi-functional requirements, many gas cylinders equipped with different working propellants are needed. Therefore, a multi-functional propulsion system based on working propellants such as krypton, argon, and xenon is proposed. This system is combined with Hall thrusters, cold gas thrusters, and electrothermal thrusters to meet the mission requirements of spacecraft for orbital control, attitude adjustment, and emergency maneuvering.

[0008] Currently available electric propulsion technologies mainly utilize Hall thruster systems, ion propulsion technology, and resistance heating propulsion systems. These electric propulsion systems have limited functionality; while achieving orbit control, they struggle with attitude control; while enabling rapid maneuvers, they are not adept at achieving high specific impulse; they may use multiple working propellants, resulting in complex and redundant overall satellite design, among other shortcomings.

[0009] The information disclosed in this background section is intended only to enhance the understanding of the overall background of the invention and should not be construed as an admission or in any way implying that the information constitutes prior art known to those skilled in the art. Summary of the Invention

[0010] This invention is based on a multi-functional propulsion system using working fluids such as krypton, argon, and xenon. Combined with Hall thrusters, electrothermal thrusters, and cold gas thrusters, it can complete tasks such as orbit maintenance, orbit transfer, attitude adjustment, and emergency maneuvering of spacecraft in orbit. It does not have a complicated design and is decoupled from the spacecraft, realizing a multi-functional propulsion system design with small weight and volume.

[0011] This invention provides a multi-functional electric propulsion system for a spacecraft, comprising:

[0012] The system includes a gas cylinder module, a fluid management module, and a thruster module. The gas cylinder module is connected downstream of the fluid management module, and the fluid management module is connected downstream of the thruster module.

[0013] The thruster module includes a Hall thruster, an electrothermal thruster, and a cold gas thruster.

[0014] Furthermore, the gas cylinder module includes a gas cylinder, which is located upstream of the fluid management module, and the gas cylinder and the fluid management module are interconnected via pipelines.

[0015] Furthermore, the fluid management module includes a filling valve, a primary pressure sensor, a primary filter, a primary first solenoid valve, a primary second solenoid valve, a first pressure reducing valve, a second pressure reducing valve, a secondary first solenoid valve, a secondary second solenoid valve, a gas capacitor, a secondary pressure sensor, a secondary filter, a first proportional valve, a second proportional valve, a third proportional valve, a fourth proportional valve, a tertiary first pressure sensor, a tertiary second pressure sensor, a tertiary first solenoid valve, a tertiary second solenoid valve, a tertiary third solenoid valve, a tertiary fourth solenoid valve, a tertiary third pressure sensor, a tertiary fourth pressure sensor, a first heater, a second heater, a tertiary fifth solenoid valve, a tertiary sixth solenoid valve, a tertiary seventh solenoid valve, a tertiary eighth solenoid valve, a tertiary ninth solenoid valve, and a tertiary tenth solenoid valve;

[0016] The primary filter is connected upstream to the filling valve and the primary pressure sensor, and downstream it is divided into two backup branches. Branch one includes the primary first solenoid valve, the first pressure reducing valve, and the secondary first solenoid valve. Branch two includes the primary second solenoid valve, the second pressure reducing valve, and the secondary second solenoid valve. After the two branches intersect, they are connected downstream to the gas container. The gas container is connected downstream to the secondary pressure sensor and the secondary filter.

[0017] The secondary filter is downstream connected to the first proportional valve, the second proportional valve, the third proportional valve, and the fourth proportional valve;

[0018] The first proportional valve and the second proportional valve are backups for each other and regulate the downstream pressure. The first proportional valve and the second proportional valve meet downstream and are respectively connected to the third-stage first pressure sensor and the third-stage second pressure sensor. The third-stage first pressure sensor and the third-stage second pressure sensor are connected downstream to the third-stage first solenoid valve and the third-stage second solenoid valve. The third-stage first pressure sensor and the third-stage second pressure sensor monitor the output pressure of the first proportional valve and the second proportional valve.

[0019] The third proportional valve and the fourth proportional valve are backups for each other and regulate the downstream pressure. The third proportional valve and the fourth proportional valve meet downstream and are respectively connected to the third-stage pressure sensor and the fourth-stage pressure sensor. The third-stage pressure sensor and the fourth-stage pressure sensor are connected downstream to the third-stage solenoid valve and the fourth-stage solenoid valve. The third-stage pressure sensor and the fourth-stage pressure sensor monitor the output pressure of the third proportional valve and the fourth proportional valve.

[0020] The third-stage fourth pressure sensor is connected downstream to the first heater and the second heater. The first heater and the second heater provide energy to the gas from upstream. The second heater is connected downstream to the third-stage fifth solenoid valve, the third-stage sixth solenoid valve, the third-stage seventh solenoid valve, the third-stage eighth solenoid valve, the third-stage ninth solenoid valve, and the third-stage tenth solenoid valve.

[0021] The gas container is used for pressure stabilization of the working fluid flow rate and for pre-storage of the working fluid in the cold gas thruster.

[0022] Furthermore, the thruster module includes one Hall thruster, two electrothermal thrusters, and four cold gas thrusters.

[0023] The Hall thruster includes a first cathode, a second cathode, and an anode; the four cold gas thrusters include a first cold gas thruster, a second cold gas thruster, a third cold gas thruster, and a fourth cold gas thruster; and the two electrothermal thrusters include a first electrothermal thruster and a second electrothermal thruster.

[0024] Furthermore, the Hall thruster is connected upstream to the third-stage first solenoid valve, the third-stage second solenoid valve, the third-stage third solenoid valve, and the third-stage fourth solenoid valve;

[0025] The first air thruster is connected upstream to the third-stage fifth solenoid valve, the second air thruster is connected upstream to the third-stage sixth solenoid valve, the third air thruster is connected upstream to the third-stage seventh solenoid valve, and the fourth air thruster is connected upstream to the third-stage eighth solenoid valve.

[0026] The first electrothermal thruster is connected upstream to the third-stage ninth solenoid valve, and the second electrothermal thruster is connected upstream to the third-stage tenth solenoid valve.

[0027] Furthermore, the first cathode of the Hall thruster is connected upstream of the third-stage first solenoid valve, the second cathode of the Hall thruster is connected upstream of the third-stage second solenoid valve, and the anode of the Hall thruster is connected upstream of the third-stage third solenoid valve and the third-stage fourth solenoid valve.

[0028] Furthermore, the working fluid of the multi-functional electric propulsion system of the spacecraft is one of krypton, argon, and xenon, or a mixture of two or more of krypton, argon, and xenon.

[0029] Furthermore, in the multi-functional electric propulsion system of the spacecraft, the first proportional valve, the second proportional valve, the third-stage first solenoid valve, and the third-stage second solenoid valve upstream of the cathode of the Hall thruster are cross-redundant, and the first proportional valve, the second proportional valve, the third-stage first solenoid valve, and the third-stage second solenoid valve can realize four operating modes:

[0030] The first proportional valve is used in conjunction with the third-stage first solenoid valve;

[0031] The first proportional valve is used in conjunction with the third-stage second solenoid valve;

[0032] The second proportional valve is used in conjunction with the third-stage first solenoid valve;

[0033] The second proportional valve is used in conjunction with the third-stage second solenoid valve;

[0034] To improve system reliability.

[0035] Furthermore, in the multi-functional electric propulsion system of the spacecraft, the third proportional valve, the fourth proportional valve, the third-stage solenoid valve, and the fourth-stage solenoid valve upstream of the anode of the Hall thruster are cross-redundant, and the third proportional valve, the fourth proportional valve, the third-stage solenoid valve, and the fourth-stage solenoid valve can achieve four operating modes:

[0036] The third proportional valve is used in conjunction with the third-stage solenoid valve.

[0037] The third proportional valve is used in conjunction with the third-stage fourth solenoid valve;

[0038] The fourth proportional valve is used in conjunction with the third-stage solenoid valve.

[0039] The fourth proportional valve is used in conjunction with the third-stage fourth solenoid valve;

[0040] To improve system reliability.

[0041] Furthermore, the first heater and the second heater are connected in series for redundancy, and can work individually or simultaneously, covering a wide power range. The failure of a single heater does not affect the operation of the system, thus improving system reliability.

[0042] Another aspect of the present invention provides a space device including a spacecraft multi-functional electric propulsion system as described above.

[0043] Another aspect of the present invention provides a multi-functional spacecraft control method, including the multi-functional electric propulsion system for spacecraft as described above or the space equipment as described above. The multi-functional spacecraft control method is capable of attitude control and orbit control of the spacecraft, and applies attitude and orbit control algorithms to realize intelligent control of the spacecraft.

[0044] Furthermore, the Hall thruster enables orbit control, the cold gas thruster enables attitude control, and the electrothermal thruster enables orbit control.

[0045] Compared with the prior art, the beneficial technical effects achieved by the present invention are as follows:

[0046] 1. Hall thrusters can achieve long-term propulsion by relying on high specific impulse, and complete tasks such as orbit maintenance and orbit transfer.

[0047] 2. The cold gas thruster has a fast response and instantaneous injection function. Although the specific impulse is low, the thrust is large and the response is rapid. It can generate short-term thrust through solenoid valve pulses. The thruster layout can be used for satellite attitude adjustment.

[0048] 3. Compared with Hall thrusters, electrothermal thrusters have a shorter response time, about 1-2 minutes, a lower specific impulse, and a higher thrust. Compared with cold gas thrusters, they have a longer response time, a higher specific impulse, and a lower thrust. Therefore, electrothermal thrusters are designed for track maneuvering and rapid obstacle avoidance.

[0049] 4. The gas container can be used for pressure stabilization and pre-storage of the working fluid in the cold gas thruster, avoiding insufficient pressure in the cold gas thruster.

[0050] 5. The upstream pressure regulating unit is used to convert high-pressure gas into low-pressure gas that can be safely used downstream.

[0051] 6. The proportional valve can achieve fine-tuning of the on-orbit pressure through electronic control, and the output pressure of the proportional valve can be adjusted according to the operation of different thrusters.

[0052] 7. The heater is used to heat the gas and replenish the temperature lost by the gas during the decompression process. The higher the temperature, the higher the specific impulse of the cold gas thruster and the electric heating thruster.

[0053] 8. Pressure sensors are used to monitor thruster operating pressure and ensure precise control of proportional valves.

[0054] 9. The filter is used to filter out impurities that may exist in the gas and gas flow path to prevent clogging of the thruster.

[0055] The invention will now be further described with reference to the accompanying drawings. Attached Figure Description

[0056] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0057] Figure 1 This is a schematic diagram of a multi-functional electric propulsion system for a spacecraft according to a specific embodiment of the present invention. Detailed Implementation

[0058] Unless otherwise expressly stated, throughout the specification and claims, the term "comprising" or its variations such as "including" or "comprises" shall be understood to include the stated elements or components without excluding other elements or other components.

[0059] The technical solution of the present invention is illustrated below through specific embodiments. It should be understood that the one or more steps mentioned in the present invention do not preclude the existence of other methods and steps before or after the combined steps, or that other methods and steps may be inserted between these explicitly mentioned steps. It should also be understood that these examples are for illustrative purposes only and are not intended to limit the scope of the present invention. Unless otherwise stated, the numbering of each method step is only for the purpose of identifying each method step, and not for limiting the order of each method or limiting the scope of the present invention. Changes or adjustments to their relative relationships, without substantial changes to the technical content, can also be considered as within the scope of the present invention.

[0060] The raw materials and instruments used in the examples are not subject to any specific restrictions on their source; they can be purchased from the market or prepared according to conventional methods known to those skilled in the art.

[0061] Example 1

[0062] like Figure 1As shown, a multi-functional electric propulsion system for a spacecraft according to a preferred embodiment of the present invention includes a gas cylinder module, a fluid management module, and a thruster module. The fluid management module is connected downstream of the gas cylinder module, and the thruster module is connected downstream of the fluid management module. The thruster module includes a Hall thruster, an electrothermal thruster, and a cold gas thruster. Through a multi-functional modular design, the numerous individual satellite attitude and orbit control devices are unified into a single-propellant but multi-functional satellite control system. This reduces the number of individual satellite functions, decoupling the system from the satellite, thus making satellite manufacturing and assembly more convenient. Simultaneously, reasonable weight reduction design reduces the number of individual units, lowering launch costs.

[0063] like Figure 1 As shown, according to a preferred embodiment of the present invention, a multi-functional electric propulsion system for a spacecraft includes a gas cylinder module comprising a gas cylinder (1). The gas cylinder (1) is located upstream of the fluid management module and is interconnected with the fluid management module via a pipeline. The gas cylinder (1) is used to store the high-pressure working gas of the thruster.

[0064] like Figure 1 As shown, according to a preferred embodiment of the present invention, a multi-functional electric propulsion system for a spacecraft includes a fluid management module comprising a filling valve (2), a primary pressure sensor (3), a primary filter (4), a primary first solenoid valve (5), a primary second solenoid valve (6), a first pressure reducing valve (7), a second pressure reducing valve (8), a secondary first solenoid valve (9), a secondary second solenoid valve (10), a gas container (11), a secondary pressure sensor (12), a secondary filter (13), a first proportional valve (14), a second proportional valve (15), a third proportional valve (16), and a fourth proportional valve (17). Three-stage first pressure sensor (18), three-stage second pressure sensor (19), three-stage first solenoid valve (20), three-stage second solenoid valve (21), three-stage third solenoid valve (22), three-stage fourth solenoid valve (23), three-stage third pressure sensor (24), three-stage fourth pressure sensor (25), first heater (26), second heater (27), three-stage fifth solenoid valve (28), three-stage sixth solenoid valve (29), three-stage seventh solenoid valve (30), three-stage eighth solenoid valve (31), three-stage ninth solenoid valve (32), three-stage tenth solenoid valve (33).

[0065] Among them, the upstream of the primary filter (4) is connected to the filling valve (2) and the primary pressure sensor (3). The primary pressure sensor (3) is used to monitor the working pressure of the working medium being filled through the gas cylinder (1). The primary filter (4) is used to filter impurities that may exist in the working medium gas and the gas flow channel. The downstream of the primary filter (4) is divided into two branches. Branch one includes the primary first solenoid valve (5), the first pressure reducing valve (7), and the secondary first solenoid valve (9). Branch two includes the primary second solenoid valve (6), the second pressure reducing valve (8), and the secondary second solenoid valve (10). After the two branches intersect, the downstream is connected to the gas container (11). The gas cylinder (11) is connected downstream to the secondary pressure sensor (12) and the secondary filter (13). The two branches are backups for each other. The high-pressure working gas added to the upstream gas cylinder (1) is converted into the low-pressure working gas downstream so that it can be used safely. The solenoid valves at each level are used for on / off control, which can realize the opening and closing of the working gas channel. The two pressure reducing valves are used to reduce the pressure of the working gas. The gas cylinder (11) is used for the working gas flow and pressure stabilization and the pre-storage of the working gas for the cold gas thruster to avoid the phenomenon of insufficient pressure of the cold gas thruster. The secondary filter (13) is used for the second stage of filtration of impurities that may exist in the working gas and the gas flow channel.

[0066] Among them, the secondary filter (13) is connected to four proportional valves downstream. The proportional valves can achieve on-orbit pressure fine adjustment of the working gas of the multi-functional electric propulsion system in spacecraft through electronic control. By adjusting the proportional valves, different working gas pressures can be output to different thrusters. The first proportional valve (14) and the second proportional valve (15) are backups for each other and regulate the pressure downstream. The first proportional valve (14) and the second proportional valve (15) meet downstream and are respectively connected to the third-stage first pressure sensor (18) and the third-stage second pressure sensor (19). The third-stage first pressure sensor (18) and the third-stage second pressure sensor (19) are connected downstream to the third-stage first solenoid valve (20) and the third-stage second solenoid valve (21). The third-stage first pressure sensor (18) and the third-stage second pressure sensor (19) monitor the output pressure of the first proportional valve (14) and the second proportional valve (15) to facilitate the precise control of the thruster working pressure by the proportional valves.

[0067] Among them, the third proportional valve (16) and the fourth proportional valve (17) are backups for each other and regulate the downstream pressure. The third proportional valve (16) and the fourth proportional valve (17) meet downstream and are respectively connected to the third-stage third pressure sensor (24) and the fourth-stage third pressure sensor (25). The third-stage third pressure sensor (24) and the fourth-stage third pressure sensor (25) are connected downstream to the third-stage third solenoid valve (22) and the fourth-stage third solenoid valve (23). The third-stage third pressure sensor (24) and the fourth-stage third pressure sensor (25) monitor the output pressure of the third proportional valve (16) and the fourth proportional valve (17).

[0068] Downstream of the third-stage fourth pressure sensor (25) are the first heater (26) and the second heater (27). The first heater (26) and the second heater (27) are used to heat the gas, provide energy to the working gas from upstream, and replenish the temperature lost by the gas during the decompression process. Increasing the temperature can increase the specific impulse of the cold gas thruster and the electric heating thruster. Downstream of the second heater (27) are the third-stage fifth solenoid valve (28), the third-stage sixth solenoid valve (29), the third-stage seventh solenoid valve (30), the third-stage eighth solenoid valve (31), the third-stage ninth solenoid valve (32), and the third-stage tenth solenoid valve (33). Each solenoid valve can realize the switching control of each output gas.

[0069] like Figure 1 As shown, according to a preferred embodiment of the present invention, a multi-functional electric propulsion system for a spacecraft includes a thruster module comprising one Hall thruster, two electrothermal thrusters, and four cold gas thrusters. One Hall thruster includes a first cathode (34), a second cathode (35), and an anode (36); four cold gas thrusters include a first cold gas thruster (37), a second cold gas thruster (38), a third cold gas thruster (39), and a fourth cold gas thruster (40); and two electrothermal thrusters include a first electrothermal thruster (41) and a second electrothermal thruster (42). Hall thrusters can achieve long-term propulsion by relying on high specific impulse, which is convenient for completing tasks such as orbit maintenance and orbit transfer. Cold gas thrusters have the function of fast response and instantaneous injection. Although the specific impulse is low, the thrust is large and the response is rapid. Short-term thrust can be generated by electromagnetic valve pulse. Through thruster layout, it can be used for satellite attitude adjustment. Compared with Hall thrusters, electrothermal thrusters have a shorter response time, about 1 to 2 minutes, a lower specific impulse, and a larger thrust. Compared with cold gas thrusters, the response time is longer, the specific impulse is higher, and the thrust is smaller, which is convenient for orbital maneuvering and rapid obstacle avoidance.

[0070] like Figure 1 As shown, in a preferred embodiment of the present invention, a multi-functional electric propulsion system for a spacecraft is provided, with a first-stage solenoid valve (20) connected upstream of the first cathode (34) of the Hall thruster, a second-stage solenoid valve (21) connected upstream of the second cathode (35) of the Hall thruster, and a third-stage solenoid valve (22) and a fourth-stage solenoid valve (23) connected upstream of the anode (36) of the Hall thruster. Each solenoid valve is capable of controlling the switching of each output gas.

[0071] Among them, the first cold air thruster (37) is connected upstream to the third-stage fifth solenoid valve (28), the second cold air thruster (38) is connected upstream to the third-stage sixth solenoid valve (29), the third cold air thruster (39) is connected upstream to the third-stage seventh solenoid valve (30), and the fourth cold air thruster (40) is connected upstream to the third-stage eighth solenoid valve (31). Each solenoid valve can realize the switching control of each output gas.

[0072] Among them, the first electrothermal thruster (41) is connected upstream to the third-stage ninth solenoid valve (32), and the second electrothermal thruster (42) is connected upstream to the third-stage tenth solenoid valve (33). Each solenoid valve can realize the switching control of each output gas.

[0073] like Figure 1 As shown, according to a preferred embodiment of the present invention, a multi-functional electric propulsion system for a spacecraft uses krypton, argon, and xenon as the working fluid, or a mixture of two or more of krypton, argon, and xenon. Xenon has a high production cost, while krypton and argon have low production costs and are readily available in the atmosphere, thereby indirectly reducing satellite manufacturing costs and constellation construction costs.

[0074] like Figure 1 As shown, in a preferred embodiment of the present invention, a multi-functional electric propulsion system for a spacecraft, the first proportional valve (14), the second proportional valve (15), and the third-stage first solenoid valve (20) and the third-stage second solenoid valve (21) upstream of the cathode of the Hall thruster are cross-redundant, enabling four working modes: the first proportional valve (14) is used in conjunction with the third-stage first solenoid valve (20), the first proportional valve (14) is used in conjunction with the third-stage second solenoid valve (21), the second proportional valve (15) is used in conjunction with the third-stage first solenoid valve (20), and the second proportional valve (15) is used in conjunction with the third-stage second solenoid valve (21), thereby improving the reliability of the propulsion system.

[0075] like Figure 1 As shown, in a preferred embodiment of the present invention, a multi-functional electric propulsion system for a spacecraft has a third proportional valve (16), a fourth proportional valve (17), and a third-stage solenoid valve (22) and a fourth-stage solenoid valve (23) upstream of the anode of the Hall thruster, which are cross-redundant and can realize four working modes: the third proportional valve (16) is used in conjunction with the third-stage solenoid valve (22), the third proportional valve (16) is used in conjunction with the fourth-stage solenoid valve (23), the fourth proportional valve (17) is used in conjunction with the third-stage solenoid valve (22), and the fourth proportional valve (17) is used in conjunction with the fourth-stage solenoid valve (23), thereby improving the reliability of the propulsion system.

[0076] like Figure 1As shown, in a preferred embodiment of the present invention, a multi-functional electric propulsion system for a spacecraft has a first heater (26) and a second heater (27) connected in series with redundancy. They can work individually or simultaneously, covering a large power range, and the failure of a single heater does not affect the operation of the system, thereby improving the reliability of the propulsion system.

[0077] Another aspect of the present invention provides a space device including a spacecraft multi-functional electric propulsion system as described above.

[0078] Another aspect of the present invention provides a multi-functional spacecraft control method, including the multi-functional electric propulsion system for spacecraft as described above, or the space equipment as described above. The multi-functional spacecraft control method is capable of attitude control and orbit control of the spacecraft, using Hall thrusters to achieve orbit control, using cold gas thrusters to achieve attitude control, using electrothermal thrusters to achieve orbit control, and applying attitude and orbit control algorithms to achieve intelligent control of the spacecraft.

[0079] In summary, the present invention utilizes a low-cost working gas and integrates the satellite's attitude control and orbit control systems through modular and thermal design. This reduces the difficulty of satellite design and manufacturing, lowers launch costs, and enables intelligent satellite control through integrated control systems combined with orbit control algorithms. This allows the satellite to adjust its orbit and attitude automatically, reducing the workload of satellite control personnel who need to monitor and control the satellite day and night.

[0080] The foregoing description of specific exemplary embodiments of the invention is for illustrative and explanatory purposes. These descriptions are not intended to limit the invention to the precise forms disclosed, and it will be apparent that many changes and variations can be made in accordance with the foregoing teachings. The exemplary embodiments were chosen and described in order to explain the specific principles of the invention and its practical application, thereby enabling those skilled in the art to implement and utilize various different exemplary embodiments of the invention, as well as various different choices and variations. The scope of the invention is intended to be defined by the claims and their equivalents.

Claims

1. A space vehicle multi-functional electric propulsion system, characterized by, The gas cylinder module, the fluid management module, and the thruster module are connected in sequence, the gas cylinder module is connected downstream to the fluid management module, and the fluid management module is connected downstream to the thruster module; The thruster module comprises a Hall thruster, an electrothermal thruster, and a cold-gas thruster; The fluid management module comprises a filling valve (2), a first-stage pressure sensor (3), a first-stage filter (4), a first-stage first electromagnetic valve (5), a first-stage second electromagnetic valve (6), a first pressure-reducing valve (7), a second pressure-reducing valve (8), a second-stage first electromagnetic valve (9), a second-stage second electromagnetic valve (10), a gas tank (11), a second-stage pressure sensor (12), a second-stage filter (13), a first proportional valve (14), a second proportional valve (15), a third proportional valve (16), a fourth proportional valve (17), a third-stage first pressure sensor (18), a third-stage second pressure sensor (19), a third-stage first electromagnetic valve (20), a third-stage second electromagnetic valve (21), a third-stage third electromagnetic valve (22), a third-stage fourth electromagnetic valve (23), a third-stage third pressure sensor (24), a third-stage fourth pressure sensor (25), a first heater (26), a second heater (27), a third-stage fifth electromagnetic valve (28), a third-stage sixth electromagnetic valve (29), a third-stage seventh electromagnetic valve (30), a third-stage eighth electromagnetic valve (31), a third-stage ninth electromagnetic valve (32), and a third-stage tenth electromagnetic valve (33); The first-stage filter (4) is connected upstream to the filling valve (2) and the first-stage pressure sensor (3), and is divided downstream into two branches in backup to each other, branch one comprising the first-stage first electromagnetic valve (5), the first pressure-reducing valve (7), and the second-stage first electromagnetic valve (9), and branch two comprising the first-stage second electromagnetic valve (6), the second pressure-reducing valve (8), and the second-stage second electromagnetic valve (10), the two branches intersecting downstream to be connected to the gas tank (11), and the gas tank (11) being connected downstream to the second-stage pressure sensor (12) and the second-stage filter (13); The second-stage filter (13) is connected downstream to the first proportional valve (14), the second proportional valve (15), the third proportional valve (16), and the fourth proportional valve (17); The first proportional valve (14) and the second proportional valve (15) are in backup to each other, and are used to adjust the pressure of downstream cathodes (34) and (35), the first proportional valve (14) and the second proportional valve (15) intersecting downstream are respectively connected to the third-stage first pressure sensor (18) and the third-stage second pressure sensor (19), the third-stage first pressure sensor (18) and the third-stage second pressure sensor (19) are connected downstream to the third-stage first electromagnetic valve (20) and the third-stage second electromagnetic valve (21), and the third-stage first pressure sensor (18) and the third-stage second pressure sensor (19) monitor the output pressure of the first proportional valve (14) and the second proportional valve (15); The third proportional valve (16) and the fourth proportional valve (17) are backups for downstream pressure regulation, and are connected to the third third pressure sensor (24) and the third fourth pressure sensor (25) downstream, respectively. The third fourth pressure sensor (25) is connected to the first heater (26) and the second heater (27) downstream, and the second heater (27) is connected to the third fifth solenoid valve (28), the third sixth solenoid valve (29), the third seventh solenoid valve (30), the third eighth solenoid valve (31), the third ninth solenoid valve (32) and the third tenth solenoid valve (33) downstream.

2. The space vehicle multi-functional electric propulsion system of claim 1, wherein, The gas cylinder module includes a gas cylinder (1), which is upstream of the fluid management module, and is connected to the fluid management module through pipelines.

3. The space vehicle multi-functional electric propulsion system of claim 1, wherein, The gas tank (11) is used for pressure stabilization of working fluid flow and pre-storage of working fluid of the cold gas thruster.

4. The space vehicle multi-functional electric propulsion system of claim 3, wherein, The thruster module includes one Hall thruster, two electrothermal thrusters and four cold gas thrusters. The one Hall thruster includes a first cathode (34), a second cathode (35) and an anode (36), and the four cold gas thrusters include a first cold gas thruster (37), a second cold gas thruster (38), a third cold gas thruster (39) and a fourth cold gas thruster (40), and the two electrothermal thrusters include a first electrothermal thruster (41) and a second electrothermal thruster (42).

5. The space vehicle multi-functional electric propulsion system of claim 4, wherein, The Hall thruster is connected to the third first solenoid valve (20), the third second solenoid valve (21), the third third solenoid valve (22) and the third fourth solenoid valve (23) upstream. The first cold gas thruster (37) is connected to the third fifth solenoid valve (28) upstream, the second cold gas thruster (38) is connected to the third sixth solenoid valve (29) upstream, the third cold gas thruster (39) is connected to the third seventh solenoid valve (30) upstream, and the fourth cold gas thruster (40) is connected to the third eighth solenoid valve (31) upstream. The first electrothermal thruster (41) is connected to the third ninth solenoid valve (32) upstream, and the second electrothermal thruster (42) is connected to the third tenth solenoid valve (33) upstream.

6. The space vehicle multi-functional electric propulsion system according to claim 4 or 5, characterized in that, The first cathode (34) of the Hall thruster is connected with the third-stage first electromagnetic valve (20) upstream, the second cathode (35) of the Hall thruster is connected with the third-stage second electromagnetic valve (21) upstream, and the anode (36) of the Hall thruster is connected with the third-stage third electromagnetic valve (22) and the third-stage fourth electromagnetic valve (23) upstream.

7. The space vehicle multi-functional electric propulsion system of any one of claims 1 to 6, wherein, The working medium of the space vehicle multifunctional electric propulsion system is one of krypton, argon and xenon or a mixed gas selected from krypton, argon and xenon.

8. The space vehicle multi-functional electric propulsion system of any one of claims 3 to 6, wherein, The first proportional valve (14) and the second proportional valve (15) upstream of the cathode of the Hall thruster in the space vehicle multifunctional electric propulsion system are cross-redundant with the third-stage first electromagnetic valve (20) and the third-stage second electromagnetic valve (21), and the first proportional valve (14) and the second proportional valve (15) can realize four working modes with the third-stage first electromagnetic valve (20) and the third-stage second electromagnetic valve (21). The first proportional valve (14) is used in cooperation with the third-stage first electromagnetic valve (20). The first proportional valve (14) is used in cooperation with the third-stage second electromagnetic valve (21). The second proportional valve (15) is used in cooperation with the third-stage first electromagnetic valve (20). The second proportional valve (15) is used in cooperation with the third-stage second electromagnetic valve (21). The system reliability is improved.

9. The space vehicle multi-functional electric propulsion system of any one of claims 3 to 6, wherein, The third proportional valve (16) and the fourth proportional valve (17) upstream of the anode of the Hall thruster in the space vehicle multifunctional electric propulsion system are cross-redundant with the third-stage third electromagnetic valve (22) and the third-stage fourth electromagnetic valve (23), and the third proportional valve (16) and the fourth proportional valve (17) can realize four working modes with the third-stage third electromagnetic valve (22) and the third-stage fourth electromagnetic valve (23). The third proportional valve (16) is used in cooperation with the third-stage third electromagnetic valve (22). The third proportional valve (16) is used in cooperation with the third-stage fourth electromagnetic valve (23). The fourth proportional valve (17) is used in cooperation with the third-stage third electromagnetic valve (22). The fourth proportional valve (17) is used in cooperation with the third-stage fourth electromagnetic valve (23). The system reliability is improved.

10. The space vehicle multi-functional electric propulsion system of any one of claims 3 to 6, wherein, The first heater (26) and the second heater (27) are in series redundancy.

11. A space device, characterized by The space device comprises the space vehicle multifunctional electric propulsion system according to any one of the preceding claims 1 to 10.

12. A method of controlling a multi-function space vehicle, the method comprising: The multifunctional space vehicle control method can be applied to the space vehicle multifunctional electric propulsion system according to any one of the preceding claims 1 to 10 or the space device according to claim 11, and can realize attitude control and orbit control of the space vehicle, and intelligent control of the space vehicle by using an attitude and orbit control algorithm.

13. The multi-functional space vehicle control method according to claim 12, wherein, The Hall thruster realizes orbit control, the cold gas thruster realizes attitude control, and the electrothermal thruster realizes orbit control.

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