Multifunctional electric propulsion system of spacecraft

Abstract

The invention discloses a multifunctional electric propulsion system of a spacecraft, 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 downstream of the gas cylinder module is connected with the fluid management module; the downstream of the fluid management module is connected with the thruster module; the thruster module comprises a Hall thruster, an electric heating type thruster and a cold air thruster. The low-cost working medium gas is utilized, the attitude control system and the orbit control system of the satellite are integrated through modular design and heat flow design, the design and manufacturing difficulty of the satellite is lowered, the launching cost of the satellite is reduced, and meanwhile the integrated control system is combined with an orbit control algorithm, so that intelligent control over the satellite can be achieved.

Description

Technical Field

[0001] The present invention relates to the technical field of space propulsion systems, and in particular to a multifunctional electric propulsion system for spacecraft. Background Art

[0002] The multifunctional propulsion system belongs to the space electric propulsion system, which realizes the propulsion mission of spacecraft through electric energy. Compared with traditional chemical propulsion, it has lighter mass, higher specific impulse, smaller volume and lower development cost. Current electric propulsion technologies include electrothermal propulsion, electrostatic propulsion and electromagnetic propulsion.

[0003] Electrothermal propulsion is to heat the working fluid with electric energy, and the gas expands due to the heat and is ejected through the nozzle at an accelerated speed, including resistance heating propulsion and arc heating propulsion;

[0004] Electrostatic propulsion means that the propellant is ionized into charged particles, and then accelerated and ejected through an electrostatic field. It mainly includes Hall thrusters, ion thrusters, and electrospray thrusters.

[0005] Electromagnetic propulsion means that the propellant is ionized in some way to form charged particles, which are accelerated and ejected under the superposition field of electric and magnetic fields. It mainly includes: variable specific impulse plasma thrusters, magnetic plasma thrusters, pulsed plasma thrusters, etc.

[0006] As the number of electric propulsion systems entering orbit increases and the technology becomes more mature, the demand for multifunctional, less-module, high thrust-to-weight ratio, and small size propulsion systems becomes more important. Therefore, multifunctional propulsion systems are gradually entering the market.

[0007] Currently, there are ammonia multifunctional propulsion systems and multi-working fluid multifunctional propulsion systems on the market. Taking into account the heavy weight of spacecraft that require orbital maneuverability, the working fluid accounts for the vast majority. When realizing multi-functional needs, many gas cylinders are needed to be equipped with different working fluids. Therefore, a multifunctional propulsion system based on krypton, argon, xenon and other working fluids is proposed, which cooperates with Hall thrusters, cold air thrusters and electrothermal thrusters to realize the orbital control, attitude adjustment, emergency maneuvering and other mission requirements of spacecraft.

[0008] The electric propulsion technologies currently available on the market mainly use Hall propulsion systems, ion propulsion technology, and resistive heating propulsion systems. The above electric propulsion systems have single functions, and it is difficult to achieve attitude control while achieving orbit control; it is difficult to achieve high specific impulse while achieving rapid maneuvers; there may be multiple working fluids, and the whole satellite design is complex and redundant, etc., which has many shortcomings.

[0009] The information disclosed in this background technology section is only intended to enhance the understanding of the overall background of the invention and should not be regarded as an acknowledgment or any form of suggestion that the information constitutes the prior art already known to a person skilled in the art. Summary of the invention

[0010] The present invention is based on a multifunctional propulsion system using krypton, argon, xenon and other working fluids, and cooperates with Hall thrusters, electrothermal thrusters and cold air thrusters to complete tasks such as orbit maintenance, orbit transfer, attitude adjustment, emergency maneuvers and other tasks of a spacecraft on orbit. It does not have a complicated design and is decoupled from the spacecraft, thus realizing a multifunctional propulsion system design with small weight and small volume.

[0011] The present invention provides a multifunctional electric propulsion system for a spacecraft, comprising:

[0012] A gas cylinder module, a fluid management module, and a thruster module, wherein the gas cylinder module is connected to the fluid management module at its downstream, and the fluid management module is connected to the thruster module at its downstream;

[0013] The thruster module includes a Hall thruster, an electrothermal thruster, and a cold air 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 connected to each other through a pipeline.

[0015] Further, the fluid management module includes a filling valve, a first-level pressure sensor, a first-level filter, a first-level solenoid valve, a first-level second solenoid valve, a first pressure reducing valve, a second pressure reducing valve, a second-level first solenoid valve, a second-level second solenoid valve, an air container, a second-level pressure sensor, a second-level filter, a first proportional valve, a second proportional valve, a third proportional valve, a fourth proportional valve, a third-level first pressure sensor, a third-level second pressure sensor, a third-level first solenoid valve, a third-level second solenoid valve, a third-level third solenoid valve, a third-level fourth solenoid valve, a third-level third pressure sensor, a third-level fourth pressure sensor, a first heater, a second heater, a third-level fifth solenoid valve, a third-level sixth solenoid valve, a third-level seventh solenoid valve, a third-level eighth solenoid valve, a third-level ninth solenoid valve, and a third-level tenth solenoid valve;

[0016] The upstream of the primary filter is connected to the filling valve and the primary pressure sensor, and the downstream is divided into two branches for mutual backup, the first branch includes the first-level first solenoid valve, the first pressure reducing valve, and the second-level first solenoid valve, and the second branch includes the first-level second solenoid valve, the second pressure reducing valve, and the second-level second solenoid valve. After the two branches intersect, the downstream is connected to the gas container, and the downstream of the gas container is connected to the secondary pressure sensor and the secondary filter;

[0017] The downstream of the secondary filter is 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 serve as backup for each other to adjust the pressure downstream. The first proportional valve and the second proportional valve intersect downstream and are respectively connected to the three-level first pressure sensor and the three-level second pressure sensor. The three-level first pressure sensor and the three-level second pressure sensor are connected downstream to the three-level first solenoid valve and the three-level second solenoid valve. The three-level first pressure sensor and the three-level 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 serve as backup for each other to adjust the pressure downstream. The third proportional valve and the fourth proportional valve intersect downstream and are respectively connected to the three-level third pressure sensor and the three-level fourth pressure sensor. The three-level third pressure sensor and the three-level fourth pressure sensor are connected downstream to the three-level third solenoid valve and the three-level fourth solenoid valve. The three-level third pressure sensor and the three-level fourth pressure sensor monitor the output pressure of the third proportional valve and the fourth proportional valve.

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

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

[0022] Further, the thruster module includes 1 Hall thruster, 2 electrothermal thrusters and 4 cold air thrusters;

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

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

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

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

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

[0028] Furthermore, the working fluid of the multifunctional electric propulsion system of the spacecraft is one of krypton, argon and xenon, or a mixed gas of two or more selected from krypton, argon and xenon.

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

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

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

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

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

[0034] To improve system reliability.

[0035] Further, the third proportional valve, the fourth proportional valve, the three-stage third solenoid valve, and the three-stage fourth solenoid valve upstream of the anode of the Hall thruster in the multifunctional electric propulsion system of the spacecraft are cross-redundant, and the third proportional valve, the fourth proportional valve, the three-stage third solenoid valve, and the three-stage fourth solenoid valve can realize four working modes:

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

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

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

[0039] The fourth proportional valve is used in conjunction with the three-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 larger power range, and failure of a single heater does not affect system operation, thereby improving system reliability.

[0042] Another aspect of the present invention provides a space device, comprising the multifunctional electric propulsion system for a spacecraft as described above.

[0043] Another aspect of the present invention provides a multifunctional spacecraft control method, including the multifunctional electric propulsion system for a spacecraft as described above or the space equipment as described above, wherein the multifunctional spacecraft control method can perform attitude control and orbit control on the spacecraft, and apply an attitude and orbit control algorithm to realize intelligent control of the spacecraft.

[0044] Furthermore, the Hall thrusters realize orbit control, the cold air thrusters realize attitude control, and the electrothermal thrusters realize 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 rely on high specific impulse to achieve long-term propulsion and complete tasks such as orbit maintenance and orbit transfer.

[0047] 2. The cold air thruster has the function of fast response and instant spraying. Although the specific impulse is low, the thrust is large and the response is fast. The solenoid valve pulse can generate short-term thrust. Through the thruster layout, it can be used for satellite attitude adjustment.

[0048] 3. Compared with Hall thrusters, the response time of electrothermal thrusters is shorter, about 1-2 minutes, the specific impulse is reduced, and the thrust is increased; compared with cold air thrusters, the response time is longer, the specific impulse is higher, and the thrust is smaller. Therefore, the positioning of electrothermal thrusters is orbital maneuvers and rapid obstacle avoidance.

[0049] 4. The gas container can be used for pressure stabilization and pre-storage of working fluid for cold air thrusters to avoid the phenomenon of insufficient pressure in cold air thrusters.

[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 on-orbit pressure fine-tuning through electronic control, and different thruster operations can adjust the proportional valve to output different pressures.

[0052] 7. The heater is used to heat the gas and make up for 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 thermal thruster.

[0053] 8. Pressure sensor is used to monitor thruster working pressure and precise control of proportional valve.

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

[0055] The present invention will be further described below in conjunction with the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0056] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0057] Figure 1 It is a schematic diagram of a multifunctional electric propulsion system for a spacecraft according to a specific embodiment of the present invention. DETAILED DESCRIPTION

[0058] Unless explicitly stated otherwise, throughout the specification and claims, the term “comprise” or variations such as “include” or “comprising”, etc., will be understood to include the stated elements or components but not to exclude other elements or components.

[0059] The technical solution of the present invention is described below by specific embodiments. It should be understood that one or more steps mentioned in the present invention do not exclude the existence of other methods and steps before and after the combination step, or other methods and steps can be inserted between these explicitly mentioned steps. It should also be understood that these examples are only used to illustrate the present invention and are not used to limit the scope of the present invention. Unless otherwise specified, the numbering of each method step is only for the purpose of identifying each method step, and does not limit the order of arrangement of each method or limit the scope of implementation of the present invention. The change or adjustment of the relative relationship thereof can also be regarded as the scope of implementation of the present invention without substantial changes in the technical content.

[0060] The sources of the raw materials and instruments used in the examples are not particularly limited and can be purchased from the market or prepared according to conventional methods known to those skilled in the art.

[0061] Embodiment 1

[0062] like Figure 1As shown, a multifunctional 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 gas cylinder module is connected to the fluid management module downstream, and the fluid management module is connected to the thruster module downstream. The thruster module includes a Hall thruster, an electrothermal thruster, and a cold air thruster. Through the multifunctional modular design, the numerous single-machine satellite attitude and orbit control equipment are unified into a single-working fluid but multifunctional satellite control system, reducing the satellite's functional single machines, decoupling the system from the satellite, thereby making the satellite's manufacturing and assembly more convenient. At the same time, through reasonable weight reduction design, the number of single machines is reduced, reducing the launch cost.

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

[0064] like Figure 1 As shown, according to a preferred embodiment of the present invention, a multifunctional electric propulsion system for a spacecraft, the fluid management module includes 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), an air 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). , a three-level first pressure sensor (18), a three-level second pressure sensor (19), a three-level first solenoid valve (20), a three-level second solenoid valve (21), a three-level third solenoid valve (22), a three-level fourth solenoid valve (23), a three-level third pressure sensor (24), a three-level fourth pressure sensor (25), a first heater (26), a second heater (27), a three-level fifth solenoid valve (28), a three-level sixth solenoid valve (29), a three-level seventh solenoid valve (30), a three-level eighth solenoid valve (31), a three-level ninth solenoid valve (32), and a three-level tenth solenoid valve (33).

[0065] The first filter (4) is connected to a filling valve (2) and a first pressure sensor (3) upstream, the first pressure sensor (3) is used to monitor the working pressure of the working medium filled through the gas cylinder (1), the first filter (4) is used to filter the impurities that may exist in the working medium gas and the gas flow channel at the first stage, and the first filter (4) is divided into two branches downstream, the first branch includes a first electromagnetic valve (5), a first pressure reducing valve (7), and a second electromagnetic valve (9), and the second branch includes a first second electromagnetic valve (6), a second pressure reducing valve (8), and a second second electromagnetic valve (10). After the two branches intersect, the downstream is connected to the gas container (11 ), the gas container (11) is connected downstream to a secondary pressure sensor (12) and a secondary filter (13), the two branches serve as backup for each other, and the high-pressure working fluid gas filled in the upstream gas cylinder (1) is converted into the low-pressure working fluid gas downstream so that it can be used safely, wherein the electromagnetic valves at various levels are used for switch control, which can realize the on-off of the working fluid channel, and the two-way pressure reducing valve is used to reduce the pressure of the working fluid gas. The gas container (11) is used for stabilizing the working fluid flow pressure and pre-storing the working fluid of the cold air thruster to avoid the phenomenon of insufficient pressure of the cold air thruster, and the secondary filter (13) is used for the second stage filtration of impurities that may exist in the working fluid gas and the gas flow channel.

[0066] Among them, four proportional valves are connected downstream of the secondary filter (13). The proportional valves can realize the fine adjustment of the on-orbit pressure of the spacecraft of the working fluid gas of the multifunctional electric propulsion system through electronic control. By adjusting the proportional valves, different working fluid gas pressures can be output to different thrusters. The first proportional valve (14) and the second proportional valve (15) serve as backup for each other to adjust the pressure downstream. The first proportional valve (14) and the second proportional valve (15) intersect downstream and are respectively connected to a three-level first pressure sensor (18) and a three-level second pressure sensor (19). The three-level first pressure sensor (18) and the three-level second pressure sensor (19) are connected downstream to a three-level first solenoid valve (20) and a three-level second solenoid valve (21). The three-level first pressure sensor (18) and the three-level second pressure sensor (19) monitor the output pressures of the first proportional valve (14) and the second proportional valve (15), so as to facilitate the precise control of the working pressure of the thruster by the proportional valve.

[0067] The third proportional valve (16) and the fourth proportional valve (17) serve as backup for each other to adjust the pressure downstream. The third proportional valve (16) and the fourth proportional valve (17) intersect downstream and are respectively connected to a three-level third pressure sensor (24) and a three-level fourth pressure sensor (25). The three-level third pressure sensor (24) and the three-level fourth pressure sensor (25) are connected downstream to a three-level third solenoid valve (22) and a three-level fourth solenoid valve (23). The three-level third pressure sensor (24) and the three-level fourth pressure sensor (25) monitor the output pressure of the third proportional valve (16) and the fourth proportional valve (17).

[0068] The third-level fourth pressure sensor (25) is connected downstream to a first heater (26) and a second heater (27). The first heater (26) and the second heater (27) are used to heat the gas, provide energy for the working fluid gas from the 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. The third-level fifth solenoid valve (28), the third-level sixth solenoid valve (29), the third-level seventh solenoid valve (30), the third-level eighth solenoid valve (31), the third-level ninth solenoid valve (32), and the third-level tenth solenoid valve (33) are connected downstream to the second heater (27). Each solenoid valve can realize the switch control of each output gas.

[0069] like Figure 1 As shown, according to a multifunctional electric propulsion system for a spacecraft according to a preferred embodiment of the present invention, the thruster module includes 1 Hall thruster, 2 electrothermal thrusters and 4 cold air thrusters. A Hall thruster comprises a first cathode (34), a second cathode (35) and an anode (36); four cold air thrusters comprise a first cold air thruster (37), a second cold air thruster (38), a third cold air thruster (39) and a fourth cold air thruster (40); and two electrothermal thrusters comprise a first electrothermal thruster (41) and a second electrothermal thruster (42). The Hall thruster can achieve long-term propulsion by relying on high specific impulse, and is convenient for completing tasks such as orbit maintenance and orbit transfer. The cold air thruster has the functions of rapid response and instant spraying. It has low specific impulse but large thrust and rapid response. It can generate short-term thrust through electromagnetic valve pulses and can be used for satellite attitude adjustment through thruster layout. Compared with the Hall thruster, the electrothermal thruster has a shorter response time, which is about 1 to 2 minutes, a lower specific impulse and an increased thrust. Compared with the cold air thruster, the electrothermal thruster has a longer response time, a higher specific impulse and a smaller thrust, and is convenient for orbit maneuvers and rapid obstacle avoidance.

[0070] like Figure 1 As shown, according to a preferred embodiment of the present invention, a multifunctional electric propulsion system for a spacecraft is provided, wherein the upstream of the first cathode (34) of the Hall thruster is connected to a three-stage first solenoid valve (20), the upstream of the second cathode (35) of the Hall thruster is connected to a three-stage second solenoid valve (21), and the upstream of the anode (36) of the Hall thruster is connected to a three-stage third solenoid valve (22) and a three-stage fourth solenoid valve (23), and each solenoid valve can realize the on-off control of each output gas.

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

[0072] The first electrothermal thruster (41) is connected upstream to a third-stage ninth solenoid valve (32), and the second electrothermal thruster (42) is connected upstream to a third-stage tenth solenoid valve (33), and each solenoid valve can realize on / off control of each output gas.

[0073] like Figure 1 As shown, according to a preferred embodiment of the present invention, a multifunctional electric propulsion system for a spacecraft is provided, wherein the working fluid of the propulsion system is one of krypton, argon, and xenon, or a mixture of two or more of the gases selected from krypton, argon, and xenon. Among them, the production cost of xenon is relatively high, while the production cost of krypton and argon is low and they are extremely easy to obtain in the atmospheric environment, thereby indirectly reducing the cost of satellite manufacturing and the cost of constellation construction.

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

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

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

[0077] Another aspect of the present invention provides a space device, comprising the multifunctional electric propulsion system for a spacecraft as described above.

[0078] Another aspect of the present invention provides a multifunctional spacecraft control method, including the multifunctional electric propulsion system for spacecraft as described above, or the space equipment as described above. The multifunctional spacecraft control method can perform attitude control and orbit control on the spacecraft, use Hall thrusters to achieve orbit control, use cold air thrusters to achieve attitude control, use electrothermal thrusters to achieve orbit control, and apply attitude and orbit control algorithms to achieve intelligent control of the spacecraft.

[0079] The implementation scheme of the present invention is briefly described as utilizing low-cost working fluid gas, through modular design and heat flow design, to integrate the attitude control and orbit control system of the satellite, thereby reducing the difficulty of satellite design and manufacturing, and reducing the launch cost of the satellite. At the same time, the integrated control system combined with the information and orbit control algorithm can realize the intelligent control of the satellite, so that the satellite can adjust its orbit and attitude according to the situation, thereby reducing the workload of satellite control personnel who are on duty day and night to monitor and control the satellite.

[0080] The foregoing description of specific exemplary embodiments of the present invention is for the purpose of illustration and demonstration. These descriptions are not intended to limit the present invention to the precise form disclosed, and it is clear that many changes and variations can be made based on the above teachings. The purpose of selecting and describing the exemplary embodiments is to explain the specific principles of the present invention and its practical application, so that those skilled in the art can realize and utilize various different exemplary embodiments of the present invention and various different selections and changes. The scope of the present invention is intended to be limited by the claims and their equivalents.

Claims

1. A multifunctional electric propulsion system for a spacecraft, characterized in that: It comprises a gas cylinder module, a fluid management module and a thruster module, wherein the gas cylinder module is connected to the fluid management module at its downstream, and the fluid management module is connected to the thruster module at its downstream; The thruster module includes a Hall thruster, an electrothermal thruster, and a cold air thruster.

2. The multifunctional electric propulsion system for spacecraft according to claim 1, characterized in that: The gas cylinder module comprises a gas cylinder (1), wherein the gas cylinder (1) is located upstream of the fluid management module, and the gas cylinder (1) and the fluid management module are connected to each other via a pipeline.

3. The multifunctional electric propulsion system for spacecraft according to claim 1, characterized in that: The fluid management module comprises 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), an air 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), a fourth proportional valve (17), and a third first pressure sensor (18). , a third-level second pressure sensor (19), a third-level first solenoid valve (20), a third-level second solenoid valve (21), a third-level third solenoid valve (22), a third-level fourth solenoid valve (23), a third-level third pressure sensor (24), a third-level fourth pressure sensor (25), a first heater (26), a second heater (27), a third-level fifth solenoid valve (28), a third-level sixth solenoid valve (29), a third-level seventh solenoid valve (30), a third-level eighth solenoid valve (31), a third-level ninth solenoid valve (32), and a third-level tenth solenoid valve (33); The upstream of the primary filter (4) is connected to the filling valve (2) and the primary pressure sensor (3), and the downstream is divided into two branches that serve as backup for each other. Branch one includes the primary first solenoid valve (5), the first pressure reducing valve (7), and the secondary first solenoid valve (9), and 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), and the downstream of the gas container (11) is connected to the secondary pressure sensor (12) and the secondary 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) serve as backup for each other and adjust the pressure for the downstream cathode (34) and the cathode (35). The first proportional valve (14) and the second proportional valve (15) intersect at the downstream and are respectively connected to the three-level first pressure sensor (18) and the three-level second pressure sensor (19). The three-level first pressure sensor (18) and the three-level second pressure sensor (19) are connected to the three-level first solenoid valve (20) and the three-level second solenoid valve (21) at the downstream. The three-level first pressure sensor (18) and the three-level 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) serve as backup for each other to adjust the pressure downstream. The third proportional valve (16) and the fourth proportional valve (17) intersect at their downstream and are respectively connected to the three-level third pressure sensor (24) and the three-level fourth pressure sensor (25). The three-level third pressure sensor (24) and the three-level fourth pressure sensor (25) are connected to the three-level third solenoid valve (22) and the three-level fourth solenoid valve (23) downstream. The three-level third pressure sensor (24) and the three-level fourth pressure sensor (25) monitor the output pressure of the third proportional valve (16) and the fourth proportional valve (17); The third-level fourth pressure sensor (25) is connected downstream to the first heater (26) and the second heater (27), the first heater (26) and the second heater (27) provide energy for the gas from the upstream, and the third-level fifth solenoid valve (28), the third-level sixth solenoid valve (29), the third-level seventh solenoid valve (30), the third-level eighth solenoid valve (31), the third-level ninth solenoid valve (32), and the third-level tenth solenoid valve (33) are connected downstream to the second heater (27); The gas container (11) is used for stabilizing the pressure of the working fluid flow and pre-storing the working fluid of the cold air thruster.

4. The multifunctional electric propulsion system for spacecraft according to claim 3, characterized in that: The thruster module includes 1 Hall thruster, 2 electrothermal thrusters and 4 cold air thrusters; The one Hall thruster comprises a first cathode (34), a second cathode (35) and an anode (36); the four cold air thrusters comprise a first cold air thruster (37), a second cold air thruster (38), a third cold air thruster (39) and a fourth cold air thruster (40); and the two electrothermal thrusters comprise a first electrothermal thruster (41) and a second electrothermal thruster (42).

5. The multifunctional electric propulsion system for spacecraft according to claim 4, characterized in that: The Hall thruster is connected upstream to the three-stage first solenoid valve (20), the three-stage second solenoid valve (21), the three-stage third solenoid valve (22), and the three-stage fourth solenoid valve (23); The first cold air thruster (37) is connected upstream to the three-stage fifth solenoid valve (28), the second cold air thruster (38) is connected upstream to the three-stage sixth solenoid valve (29), the third cold air thruster (39) is connected upstream to the three-stage seventh solenoid valve (30), and the fourth cold air thruster (40) is connected upstream to the three-stage eighth solenoid valve (31); 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).

6. The multifunctional electric propulsion system for spacecraft according to claim 4 or 5, characterized in that: The first cathode (34) of the Hall thruster is connected upstream to the three-stage first solenoid valve (20), the second cathode (35) of the Hall thruster is connected upstream to the three-stage second solenoid valve (21), and the anode (36) of the Hall thruster is connected upstream to the three-stage third solenoid valve (22) and the three-stage fourth solenoid valve (23).

7. The multifunctional electric propulsion system for spacecraft according to any one of claims 1 to 6, characterized in that: The working fluid of the multifunctional electric propulsion system of the spacecraft is one of krypton, argon and xenon, or a mixed gas of two or more of them.

8. The multifunctional electric propulsion system for spacecraft according to any one of claims 3 to 6, characterized in that: The first proportional valve (14), the second proportional valve (15), the three-stage first solenoid valve (20), and the three-stage second solenoid valve (21) upstream of the cathode of the Hall thruster in the multifunctional electric propulsion system of the spacecraft are cross-redundant, and the first proportional valve (14), the second proportional valve (15), the three-stage first solenoid valve (20), and the three-stage second solenoid valve (21) can realize four working modes: The first proportional valve (14) is used in conjunction with the three-stage first solenoid valve (20); The first proportional valve (14) is used in conjunction with the three-stage second solenoid valve (21); The second proportional valve (15) is used in conjunction with the three-stage first solenoid valve (20); The second proportional valve (15) is used in conjunction with the three-stage second solenoid valve (21); To improve system reliability.

9. The multifunctional electric propulsion system for spacecraft according to any one of claims 3 to 6, characterized in that: The third proportional valve (16), the fourth proportional valve (17), the three-stage third solenoid valve (22), and the three-stage fourth solenoid valve (23) upstream of the anode of the Hall thruster in the multifunctional electric propulsion system of the spacecraft are cross-redundant, and the third proportional valve (16), the fourth proportional valve (17), the three-stage third solenoid valve (22), and the three-stage fourth solenoid valve (23) can realize four working modes: The third proportional valve (16) is used in conjunction with the three-stage third solenoid valve (22); The third proportional valve (16) is used in conjunction with the third-level fourth solenoid valve (23); The fourth proportional valve (17) is used in conjunction with the three-stage third solenoid valve (22); The fourth proportional valve (17) is used in conjunction with the three-stage fourth solenoid valve (23); To improve system reliability.

10. The multifunctional electric propulsion system for spacecraft according to any one of claims 3 to 6, characterized in that: The first heater (26) and the second heater (27) are connected in series for redundancy and can work individually or simultaneously, covering a larger power range. Failure of a single heater does not affect system operation, thereby improving system reliability.

11. A space device, characterized in that: The space equipment comprises a multifunctional electric propulsion system for a spacecraft as claimed in any one of claims 1 to 10.

12. A multifunctional spacecraft control method, characterized in that: It comprises a multifunctional electric propulsion system for a spacecraft according to any one of claims 1 to 10 or a space device according to claim 11, wherein the multifunctional spacecraft control method is capable of performing attitude control and orbit control on the spacecraft, and applying an attitude and orbit control algorithm to realize intelligent control of the spacecraft.

13. The multifunctional spacecraft control method according to claim 12, characterized in that: The Hall thrusters realize orbit control, the cold air thrusters realize attitude control, and the electrothermal thrusters realize orbit control.

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