A fully automated bidirectional on-orbit replenishment system for spacecraft surface tension tanks based on active gas-liquid separation technology.

Abstract

This invention provides a fully automated bidirectional on-orbit refueling device for spacecraft surface tension tanks based on active gas-liquid separation technology, relating to the field of on-orbit refueling devices. The device includes a gas cylinder, a tank, an engine, and a refueling manager. The gas cylinder and tank are isolated and connected via valves, and the tank and engine are isolated and connected via valves. The tanks are isolated and connected via a refueling circuit. The refueling manager controls the connecting valves and the refueling circuit to achieve automatic on-orbit propellant refueling. This invention utilizes rotating blades inside the tank to achieve active gas-liquid separation based on the density difference between gas and liquid, preventing propellant from prematurely entering the tank's gas path nozzle and causing refueling interruption. This significantly improves adaptability to propellant flow rate and acceleration disturbances during refueling, while also increasing refueling efficiency. It achieves bidirectional on-orbit propellant refueling, improving the spacecraft's adaptability to flight missions and enhancing the reliability of on-orbit refueling of surface tension tanks.

Description

Technical Field

[0001] This invention relates to the field of on-orbit replenishment devices, and more specifically, to a fully automated bidirectional on-orbit replenishment device for spacecraft surface tension tanks based on active gas-liquid separation technology. Background Technology

[0002] Propellant load is a key factor limiting the lifespan of spacecraft. For satellite and manned deep space exploration, ensuring sufficient propellant enters space and is stored long-term is fundamental to achieving these goals. Directly carrying sufficient propellant from the ground into space would inevitably result in enormous launch vehicle and payload sizes, increased launch and control complexity, and high costs. Compared to ground-based launches, on-orbit propellant replenishment offers significant advantages. First, it effectively extends the operational lifespan of spacecraft; second, it significantly expands the scope of human space exploration; and finally, it reduces spacecraft development cycles and costs.

[0003] Surface tension tanks utilize surface tension for liquid transport and gas-liquid separation, providing air-free propellant for engines or thrusters. Due to their advantages such as large volume and light weight, surface tension tanks are widely used in spacecraft propulsion systems. Therefore, on-orbit replenishment technology using surface tension tanks is one of the important development directions for future space propulsion systems. Current research still relies on the surface tension of the fluid itself for gas-liquid separation in the replenished tank. This makes the replenishment efficiency highly sensitive to the installation location of the tank's gas path nozzles, acceleration disturbances during replenishment, and the working fluid velocity, making it difficult to meet the future requirements for on-orbit replenishment under conditions of large volume, high flow rate, and acceleration disturbances. Furthermore, on-orbit replenishment of surface tension tanks is a highly complex process. Existing on-orbit replenishment systems require significant space-to-ground communication resources and substantial ground personnel support, making it difficult to respond promptly to unexpected events during replenishment.

[0004] In summary, existing surface tension tank on-orbit replenishment technologies cannot achieve bidirectional, automated replenishment and active gas-liquid separation. The fully automated bidirectional on-orbit replenishment device for spacecraft surface tension tanks based on active gas-liquid separation technology provided by this invention can largely overcome the shortcomings of existing technologies. Summary of the Invention

[0005] To address the shortcomings of existing technologies, the purpose of this invention is to provide a fully automated bidirectional on-orbit replenishment device for spacecraft surface tension tanks based on active gas-liquid separation technology.

[0006] According to the present invention, a fully automatic bidirectional on-orbit replenishment device for a spacecraft surface tension tank based on active gas-liquid separation technology is provided, comprising a gas cylinder, a tank, an engine, and a replenishment manager. The gas cylinder and the tank are isolated and connected through a self-locking valve, and the tank and the engine are isolated and connected through a self-locking valve.

[0007] The tanks are isolated and connected by replenishment loops. The replenishment manager collects the output signals of the pressure sensor, flow meter and propellant monitoring device on the replenishment loop, and drives the docking device active end, self-locking valve and electric pump to realize automatic on-orbit replenishment of propellant.

[0008] Preferably, the gas cylinder includes a first gas cylinder and a second gas cylinder, the storage tank includes a first surface tension storage tank and a second surface tension storage tank, and the engine includes a first engine and a second engine;

[0009] The first gas cylinder is isolated and connected to the first surface tension storage tank through the first self-locking valve and the first pressure reducing valve. A fifth pressure sensor is provided between the first pressure reducing valve and the first surface tension storage tank. The outlet of the first surface tension storage tank is isolated and connected to the first engine through the tenth self-locking valve.

[0010] The second gas cylinder is isolated and connected to the second surface tension tank through the second self-locking valve and the second pressure reducing valve. A sixth pressure sensor is installed between the second pressure reducing valve and the second surface tension tank. The outlet of the second surface tension tank is isolated and connected to the second engine through the twelfth self-locking valve.

[0011] Preferably, the first and second surface tension tanks have identical structures, including a tank shell, a liquid inlet with tubing, a gas nozzle, a rotating shaft, a motor, blades, wires, a lead screw, a bubble trap, an outlet A, and an inlet B. A ring of liquid inlet with tubing is provided on the inner wall of the tank shell. The liquid inlet with tubing has an outlet A and an inlet B, which extend out of the tank shell. One end of the gas nozzle extends out of the tank shell, and the other end extends into the hollow rotating shaft to avoid interference. The rotating shaft has blades and is connected to a motor. The motor is connected to the bubble trap, and the bubble trap is connected to the outlet A.

[0012] The motor is connected to the replenishment manager via wires and lead screws, and the lead screws are connected to the tank shell. The motor drives the shaft to rotate, and the shaft drives the blades to rotate, thus realizing gas-liquid separation in a weightless environment.

[0013] Preferably, the tank shell, the liquid inlet with tubing, the gas inlet nozzle, the lead screw plug, the blades, the shaft, the bubble trap, the liquid outlet A, and the liquid inlet B are all made of corrosion-resistant materials, and the motor and the wires are all enclosed in protective shells to achieve compatibility with the propellant;

[0014] Outlet A is used to discharge propellant, and inlet B is used to receive propellant, so as to achieve bidirectional propellant replenishment.

[0015] Preferably, the first surface tension tank and the second surface tension tank gas chamber are isolated and connected in sequence through a third self-locking valve, a propellant monitoring device, an active end of the first docking device, a passive end of the first docking device, and a fourth self-locking valve. The propellant flow between the first surface tension tank and the second surface tension tank gas chamber is monitored by the propellant monitoring device.

[0016] Furthermore, a first pressure sensor, a third self-locking valve, a propellant monitoring device, a second pressure sensor, the active end of the first docking device, the passive end of the first docking device, a third pressure sensor, a fourth self-locking valve, and a fourth pressure sensor are connected in series between the gas chambers of the first and second surface tension tanks.

[0017] Preferably, the outlet A of the first surface tension tank is connected to the inlet B of the second surface tension tank in sequence through the seventh self-locking valve, the electric pump, the flow meter, the eighth self-locking valve, the active end of the second docking device, the passive end of the second docking device, and the sixth self-locking valve.

[0018] An electric pump provides power for the flow of propellant, a flow meter measures the propellant flow rate, and a seventh self-locking valve, an eighth self-locking valve, the active end of the second docking device, the passive end of the second docking device, and a sixth self-locking valve achieve isolation and communication between the liquid chambers of the first and second surface tension tanks.

[0019] Preferably, the outlet A of the second surface tension tank is connected to the inlet B of the first surface tension tank in sequence through the ninth self-locking valve, the passive end of the third docking device, the active end of the third docking device, the eleventh self-locking valve, the electric pump, the flow meter, and the fifth self-locking valve.

[0020] The ninth self-locking valve, the passive end of the third docking device, the active end of the third docking device, the eleventh self-locking valve, and the fifth self-locking valve realize the isolation and connection between the liquid chambers of the first surface tension tank and the second surface tension tank.

[0021] Preferably, the outlet A of the first surface tension tank is connected to the tenth self-locking valve and the seventh self-locking valve via the eleventh pressure sensor; the electric pump is connected to the seventh self-locking valve and the eleventh self-locking valve via the fourteenth pressure sensor; the flow meter is connected to the fifth self-locking valve and the eighth self-locking valve via the eighth pressure sensor; the seventh pressure sensor is provided between the inlet B of the first surface tension tank and the fifth self-locking valve; the twelfth pressure sensor is provided between the eighth self-locking valve and the active end of the second docking device; the ninth pressure sensor is provided between the passive end of the second docking device and the sixth self-locking valve; the tenth pressure sensor is provided between the sixth self-locking valve and the inlet B of the second surface tension tank; the outlet A of the second surface tension tank is connected to the ninth self-locking valve and the twelfth self-locking valve via the thirteenth pressure sensor; the sixteenth pressure sensor is provided between the ninth self-locking valve and the passive end of the third docking device; and the fifteenth pressure sensor is provided between the eleventh self-locking valve and the active end of the third docking device.

[0022] Preferably, the replenishment manager is used to collect the output signals of the first pressure sensor, second pressure sensor, third pressure sensor, fourth pressure sensor, fifth pressure sensor, sixth pressure sensor, seventh pressure sensor, eighth pressure sensor, ninth pressure sensor, tenth pressure sensor, eleventh pressure sensor, twelfth pressure sensor, thirteenth pressure sensor, fourteenth pressure sensor, fifteenth pressure sensor, sixteenth pressure sensor, flow meter, and propellant monitoring device. The replenishment manager monitors the propellant replenishment amount and the health status of the replenishment system. The replenishment manager drives the first docking device active end, second docking device active end, third docking device active end, third docking device passive end, first self-locking valve, second self-locking valve, third self-locking valve, fourth self-locking valve, fifth self-locking valve, sixth self-locking valve, seventh self-locking valve, eighth self-locking valve, ninth self-locking valve, tenth self-locking valve, eleventh self-locking valve, twelfth self-locking valve, and electric pump through the built-in replenishment program.

[0023] Preferably, the propellant monitoring device includes a light emitter and a photoelectric sensor, which are installed in a fixed position;

[0024] When the propellant is not flowing, the photoelectric sensor can receive light emitted from the light emitter;

[0025] When propellant flows through, the photoelectric sensor cannot receive the light emitted from the light emitter because the refractive index of the propellant is different from that of the gas. The photoelectric sensor changes its output signal to monitor whether propellant is flowing through.

[0026] Compared with the prior art, the present invention has the following beneficial effects:

[0027] (1) The present invention achieves active gas-liquid separation by using the density difference between gas and liquid through rotating blades inside the tank, preventing propellant from entering the gas pipeline nozzle of the tank in advance and causing the replenishment to stop. This greatly improves the adaptability to propellant flow rate and acceleration disturbances during replenishment and also improves replenishment efficiency.

[0028] (2) By setting both an outlet and an inlet in the storage tank, the present invention enables bidirectional on-orbit replenishment of propellant. The spacecraft can flexibly set the replenishment direction according to mission requirements, thereby improving the spacecraft's adaptability to flight missions.

[0029] (3) This invention realizes fully automatic on-orbit replenishment of surface tension tanks, reduces the demand for space-to-ground communication resources and the workload of ground personnel for on-orbit replenishment, and improves the reliability of on-orbit replenishment of surface tension tanks. Attached Figure Description

[0030] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0031] Figure 1 A schematic diagram of a fully automated bidirectional on-orbit replenishment device for a spacecraft surface tension tank based on active gas-liquid separation technology, provided for this invention.

[0032] Figure 2 This is a schematic diagram of the surface tension tank structure including an active gas-liquid separation device provided by the present invention.

[0033] Numbered in the diagram: 1. First gas cylinder; 2. Second gas cylinder; 3. First self-locking valve; 4. Second self-locking valve; 5. First pressure reducing valve; 6. Second pressure reducing valve; 7. First surface tension tank; 7. Tank housing; 71. Liquid inlet with tubing; 72. Gas nozzle; 73. Lead screw plug; 74. Blade; 75. Shaft; 76. Motor; 77. Wire; 78. Bubble trap; 79. Liquid outlet; 7A. Liquid inlet; 7B. Second surface tension tank; 8. First pressure sensor; 9. Second pressure sensor; 10. Third pressure sensor; 11. Fourth pressure sensor; 12. Third self-locking valve; 13. Propellant monitoring device; 14. First docking device active end; 15. First docking device passive end; 16. Fourth self-locking valve; 17. Fifth pressure sensor; 18. Sixth pressure sensor; 19. Replenishment manager; 20. 21. Seventh pressure sensor; 22. Eighth pressure sensor; 23. Ninth pressure sensor; 24. Tenth pressure sensor; 25. Fifth self-locking valve; 26. Sixth self-locking valve; 27. Eleventh pressure sensor; 28. Twelfth pressure sensor; 29. ​​Seventh self-locking valve; 30. Electric pump; 31. Flow meter; 32. Eighth self-locking valve; 33. Second docking device active end; 34. Second docking device passive end; 35. Ninth self-locking valve; 36. Tenth self-locking valve; 37. Eleventh self-locking valve; 38. Third docking device active end; 39. Third docking device passive end; 40. Thirteenth pressure sensor; 41. Twelfth self-locking valve; 42. Fourteenth pressure sensor; 43. Fifteenth pressure sensor; 44. Sixteenth pressure sensor; 45. First engine; 46. Second engine. Detailed Implementation

[0034] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0035] Example

[0036] According to the present invention, a fully automated bidirectional on-orbit replenishment device for spacecraft surface tension tanks based on active gas-liquid separation technology is provided, such as... Figure 1As shown, the system includes gas cylinders, storage tanks, an engine, and a refueling manager 20. The gas cylinders include a first gas cylinder 1 and a second gas cylinder 2; the storage tanks include a first surface tension storage tank 7 and a second surface tension storage tank 8; and the engine includes a first engine 45 and a second engine 46. The first gas cylinder 1 is isolated from and connected to the first surface tension storage tank 7 via a first self-locking valve 3 and a first pressure reducing valve 5. A fifth pressure sensor 18 is installed between the first pressure reducing valve 5 and the first surface tension storage tank 7. The outlet of the first surface tension storage tank 7 is isolated from and connected to the first engine 45 via a tenth self-locking valve 36. The second gas cylinder 2 is isolated from and connected to the second surface tension storage tank 8 via a second self-locking valve 4 and a second pressure reducing valve 6. A sixth pressure sensor 19 is installed between the second pressure reducing valve 6 and the second surface tension storage tank 8. The outlet of the second surface tension storage tank 8 is isolated from and connected to the second engine 46 via a twelfth self-locking valve 41.

[0037] like Figure 2 As shown, the first surface tension tank 7 and the second surface tension tank 8 have the same structure, including a tank shell 71, a liquid inlet 72 with a tube, a gas nozzle 73, a rotating shaft 76, a motor 77, a bubble trap 79, a liquid outlet 7A, and a liquid inlet 7B. A ring of liquid inlets 72 is provided on the inner wall of the tank shell 71. The liquid inlets 72 have a liquid outlet 7A and a liquid inlet 7B, and the liquid outlet 7A and the liquid inlet 7B extend out of the tank shell 71. One end of the gas nozzle 73 extends out of the tank shell 71. Externally, the other end of the gas pipe nozzle 73 is connected to the rotating shaft 76 inside the storage tank housing 71. The rotating shaft 76 is equipped with blades 75. The rotating shaft 76 is connected to the motor 77, the motor 77 is connected to the bubble trap 79, and the bubble trap 79 is connected to the liquid outlet 7A. The motor 77 is connected to the replenishment manager 20 through the wire 78 and the lead screw plug 74, and the lead screw plug 74 is connected to the storage tank housing 71. The motor 77 drives the rotating shaft 76 to rotate, and the rotating shaft 76 drives the blades 75 to rotate, realizing gas-liquid separation in a weightless environment. The tank shell 71, the liquid inlet with tubing 72, the gas nozzle 73, the lead screw plug 74, the blade 75, the rotating shaft 76, the bubble trap 79, the liquid outlet 7A, and the liquid inlet 7B are all made of corrosion-resistant materials. The motor 77 and the wire 78 are all enclosed in protective shells to ensure compatibility with the propellant. The liquid outlet 7A is used to discharge the propellant, and the liquid inlet 7B is used to receive the propellant to achieve bidirectional replenishment of the propellant. In actual orbit, the replenishment direction can be flexibly selected according to mission requirements.

[0038] The propellant monitoring device 14 includes a light emitter and a photoelectric sensor, which are installed in a fixed position. When no propellant is flowing, the photoelectric sensor can receive light emitted from the light emitter. When propellant is flowing, the photoelectric sensor cannot receive light emitted from the light emitter because the refractive index of the propellant is different from that of the gas. The photoelectric sensor changes its output signal to monitor whether propellant is flowing.

[0039] The first surface tension tank 7 and the second surface tension tank 8 are isolated and connected sequentially through a third self-locking valve 13, a propellant monitoring device 14, an active end of the first docking device 15, a passive end of the first docking device 16, and a fourth self-locking valve 17. At the same time, the system monitors whether propellant flows between the gas chambers of the first surface tension tank 7 and the second surface tension tank 8 during the replenishment process. Furthermore, the gas chambers of the first surface tension tank 7 and the second surface tension tank 8 are connected in series with a first pressure sensor 9, a third self-locking valve 13, a propellant monitoring device 14, a second pressure sensor 10, an active end of the first docking device 15, a passive end of the first docking device 16, a third pressure sensor 11, a fourth self-locking valve 17, and a fourth pressure sensor 12.

[0040] The outlet 7A of the first surface tension tank 7 is connected to the inlet 7B of the second surface tension tank 8 via the seventh self-locking valve 29, the electric pump 30, the flow meter 31, the eighth self-locking valve 32, the active end 33 of the second docking device, the passive end 34 of the second docking device, and the sixth self-locking valve 26 in sequence. The electric pump 30 provides power for the flow of propellant, the flow meter 31 measures the propellant flow rate, and the seventh self-locking valve 29, the eighth self-locking valve 32, the active end 33 of the second docking device, the passive end 34 of the second docking device, and the sixth self-locking valve 26 realize the isolation and communication between the liquid chambers of the first surface tension tank 7 and the second surface tension tank 8.

[0041] The outlet 7A of the second surface tension tank 8 is connected to the inlet 7B of the first surface tension tank 7 in sequence through the ninth self-locking valve 35, the passive end 39 of the third docking device, the active end 38 of the third docking device, the eleventh self-locking valve 37, the electric pump 30, the flow meter 31, and the fifth self-locking valve 25. The ninth self-locking valve 35, the passive end 39 of the third docking device, the active end 38 of the third docking device, the eleventh self-locking valve 37, and the fifth self-locking valve 25 realize the isolation and communication between the liquid chambers of the first surface tension tank 7 and the second surface tension tank 8.

[0042] The outlet 7A of the first surface tension tank 7 is connected to the tenth self-locking valve 36 and the seventh self-locking valve 29 via the eleventh pressure sensor 27. The electric pump 30 is connected to the seventh self-locking valve 29 and the eleventh self-locking valve 37 via the fourteenth pressure sensor 42. The flow meter 31 is connected to the fifth self-locking valve 25 and the eighth self-locking valve 32 via the eighth pressure sensor 22. The seventh pressure sensor 21 is provided between the inlet 7B of the first surface tension tank 7 and the fifth self-locking valve 25. The twelfth pressure sensor is provided between the eighth self-locking valve 32 and the active end 33 of the second docking device. 28. A ninth pressure sensor 23 is provided between the passive end 34 of the second docking device and the sixth self-locking valve 26. A tenth pressure sensor 24 is provided between the sixth self-locking valve 26 and the inlet 7B of the second surface tension tank 8. The outlet 7A of the second surface tension tank 8 is connected to the ninth self-locking valve 35 and the twelfth self-locking valve 41 respectively through the thirteenth pressure sensor 40. A sixteenth pressure sensor 44 is provided between the ninth self-locking valve 35 and the passive end 39 of the third docking device. A fifteenth pressure sensor 43 is provided between the eleventh self-locking valve 37 and the active end 38 of the third docking device.

[0043] The replenishment manager 20 is used to acquire the output signals of the first pressure sensor 9, the second pressure sensor 10, the third pressure sensor 11, the fourth pressure sensor 12, the fifth pressure sensor 18, the sixth pressure sensor 19, the seventh pressure sensor 21, the eighth pressure sensor 22, the ninth pressure sensor 23, the tenth pressure sensor 24, the eleventh pressure sensor 27, the twelfth pressure sensor 28, the thirteenth pressure sensor 40, the fourteenth pressure sensor 42, the fifteenth pressure sensor 43, the sixteenth pressure sensor 44, the flow meter 31, and the propellant monitoring device 14. The replenishment manager 20 monitors the propellant replenishment amount and the health status of the replenishment system. The replenishment manager 20 drives the first docking device active end 15, the second docking device active end 33, the third docking device active end 38, the third docking device passive end 39, the first self-locking valve 3, the second self-locking valve 4, the third self-locking valve 13, the fourth self-locking valve 17, the fifth self-locking valve 25, the sixth self-locking valve 26, the seventh self-locking valve 29, the eighth self-locking valve 32, the ninth self-locking valve 35, the tenth self-locking valve 36, the eleventh self-locking valve 37, the twelfth self-locking valve 41, and the electric pump 30 through the built-in replenishment program.

[0044] Working principle: After receiving the replenishment start command, the replenishment manager 20 first determines the replenishment direction and executes the following replenishment process according to different replenishment directions:

[0045] If the propellant replenishment direction is from the first surface tension tank 7 to the second surface tension tank 8, the replenishment manager 20 drives the first docking device active end 15 and the second docking device active end 33 to connect with the first docking device passive end 16 and the second docking device passive end 34, respectively, and closes the first self-locking valve 3, the second self-locking valve 4, the fifth self-locking valve 25, the eleventh self-locking valve 37, the ninth self-locking valve 35, the tenth self-locking valve 36, and the twelfth self-locking valve 41, and opens the third self-locking valve 13, the fourth self-locking valve 17, the seventh self-locking valve 29, the eighth self-locking valve 32, and the sixth self-locking valve 26. Then, it drives the motor 77 in the second surface tension tank 8 to rotate. After completing the above steps, the replenishment manager 20 drives the electric pump 30 to rotate, and the propellant begins to flow between the tanks. The replenishment manager 20 determines the propellant replenishment amount according to the flow meter 31 and monitors whether propellant is flowing through the gas pipeline according to the propellant monitoring device 14. When the flow meter 31 shows that the propellant replenishment amount meets the set value or the propellant measuring device 14 shows that there is propellant flowing through the gas pipeline, the electric pump 30, the motor in the second surface tension tank 8, and the third self-locking valve 13, the fourth self-locking valve 17, the seventh self-locking valve 29, the eighth self-locking valve 32, and the sixth self-locking valve 26 are turned off, the active end 15 and the passive end 16 of the first docking device, as well as the active end 33 and the passive end 34 of the second docking device are separated, and the on-orbit propellant replenishment is completed.

[0046] If the propellant replenishment direction is from the second surface tension tank 8 to the first surface tension tank 7, the replenishment manager 20 drives the first docking device active end 15 and the third docking device active end 38 to connect with the first docking device passive end 16 and the third docking device passive end 39, respectively, and closes the first self-locking valve 3, the second self-locking valve 4, the seventh self-locking valve 29, the eighth self-locking valve 32, the sixth self-locking valve 26, the tenth self-locking valve 36, and the twelfth self-locking valve 41, and opens the third self-locking valve 13, the fourth self-locking valve 17, the ninth self-locking valve 35, the eleventh self-locking valve 37, and the fifth self-locking valve 25. Then, it drives the motor 77 in the first surface tension tank 7 to rotate. After completing the above steps, the replenishment manager 20 drives the electric pump 30 to rotate, and the propellant begins to flow between the tanks. The replenishment manager 20 determines the propellant replenishment amount according to the flow meter 31 and monitors whether propellant is flowing through the gas pipeline according to the propellant monitoring device 14. When the flow meter 31 shows that the propellant replenishment amount meets the set value or the propellant measuring device 14 shows that there is propellant flowing through the gas pipeline, the electric pump 30, the motor 77 in the first surface tension tank 7, and the third self-locking valve 13, the fourth self-locking valve 17, the ninth self-locking valve 35, the eleventh self-locking valve 37, and the fifth self-locking valve 25 are shut down, the active end 15 and the passive end 16 of the first docking device, and the active end 38 and the passive end 39 of the third docking device are separated, and the on-orbit propellant replenishment is completed.

[0047] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0048] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A fully automated bidirectional on-orbit replenishment device for spacecraft surface tension tanks based on active gas-liquid separation, characterized in that, Includes a gas cylinder, a storage tank, an engine, and a replenishment manager (20). The gas cylinder and the storage tank are isolated and connected through a self-locking valve, and the storage tank and the engine are isolated and connected through a self-locking valve. The tanks are isolated and connected by a replenishment circuit. The replenishment manager (20) collects the output signals of the pressure sensor, flow meter (31) and propellant monitoring device (14) on the replenishment circuit. The replenishment manager (20) drives the docking device active end, self-locking valve and electric pump (30) to realize automatic on-orbit replenishment of propellant. The gas cylinder includes a first gas cylinder (1) and a second gas cylinder (2), the storage tank includes a first surface tension storage tank (7) and a second surface tension storage tank (8), and the engine includes a first engine (45) and a second engine (46). The first gas cylinder (1) is isolated and connected to the first surface tension tank (7) through the first self-locking valve (3) and the first pressure reducing valve (5). A fifth pressure sensor (18) is provided between the first pressure reducing valve (5) and the first surface tension tank (7). The liquid outlet of the first surface tension tank (7) is isolated and connected to the first engine (45) through the tenth self-locking valve (36). The second gas cylinder (2) is isolated and connected to the second surface tension tank (8) through the second self-locking valve (4) and the second pressure reducing valve (6). A sixth pressure sensor (19) is provided between the second pressure reducing valve (6) and the second surface tension tank (8). The outlet of the second surface tension tank (8) is isolated and connected to the second engine (46) through the twelfth self-locking valve (41). The first surface tension tank (7) and the second surface tension tank (8) have the same structure, including a tank shell (71), a liquid inlet with tubing (72), a gas nozzle (73), a lead screw plug (74), a blade (75), a rotating shaft (76), a motor (77), a wire (78), a bubble trap (79), a liquid outlet (7A), and a liquid inlet (7B). The inner wall of the tank shell (71) is provided with a ring of the liquid inlet with tubing (72), and the liquid inlet (7A) and the liquid inlet (7B) are provided on the liquid inlet with tubing (72). The liquid outlet (7A) and the liquid inlet (7B) extend out of the outside of the storage tank housing (71), and one end of the gas pipe nozzle (73) extends out of the outside of the storage tank housing (71). The other end of the gas pipe nozzle (73) is connected to the rotating shaft (76) inside the storage tank housing (71). The rotating shaft (76) is provided with the blade (75). The rotating shaft (76) is connected to the motor (77). The motor (77) is connected to the bubble trap (79). The bubble trap (79) is connected to the liquid outlet (7A). The motor (77) is connected to the replenishment manager (20) through the wire (78) and the lead screw (74), and the lead screw (74) is connected to the storage tank shell (71). The motor (77) drives the rotating shaft (76) to rotate, and the rotating shaft (76) drives the blade (75) to rotate, thereby realizing gas-liquid separation in a weightless environment.

2. The fully automated bidirectional on-orbit replenishment device for spacecraft surface tension tanks based on active gas-liquid separation as described in claim 1, characterized in that, The tank shell (71), the liquid inlet with tubing (72), the gas inlet (73), the lead screw plug (74), the blade (75), the rotating shaft (76), the bubble trap (79), the liquid outlet (7A), and the liquid inlet (7B) are all made of corrosion-resistant materials. The motor (77) and the wire (78) are both equipped with protective housings to ensure compatibility with the propellant. The outlet (7A) is used to discharge propellant, and the inlet (7B) is used to receive propellant, so as to realize bidirectional replenishment of propellant.

3. The fully automated bidirectional on-orbit replenishment device for spacecraft surface tension tanks based on active gas-liquid separation according to claim 2, characterized in that, The first surface tension tank (7) and the second surface tension tank (8) are isolated and connected in sequence through the third self-locking valve (13), the propellant monitoring device (14), the active end of the first docking device (15), the passive end of the first docking device (16) and the fourth self-locking valve (17). The propellant flow between the first surface tension tank (7) and the second surface tension tank (8) is monitored by the propellant monitoring device (14). Furthermore, the first surface tension tank (7) and the second surface tension tank (8) are connected in series with the first pressure sensor (9), the third self-locking valve (13), the propellant monitoring device (14), the second pressure sensor (10), the first docking device active end (15), the first docking device passive end (16), the third pressure sensor (11), the fourth self-locking valve (17), and the fourth pressure sensor (12).

4. The fully automated bidirectional on-orbit replenishment device for spacecraft surface tension tanks based on active gas-liquid separation according to claim 3, characterized in that, The outlet (7A) of the first surface tension tank (7) is connected to the inlet (7B) of the second surface tension tank (8) in sequence through the seventh self-locking valve (29), electric pump (30), flow meter (31), eighth self-locking valve (32), active end of the second docking device (33), passive end of the second docking device (34) and sixth self-locking valve (26); The electric pump (30) provides power for the flow of propellant, the flow meter (31) measures the propellant flow rate, and the seventh self-locking valve (29), the eighth self-locking valve (32), the active end (33) of the second docking device, the passive end (34) of the second docking device, and the sixth self-locking valve (26) realize the isolation and communication between the liquid chambers of the first surface tension tank (7) and the second surface tension tank (8).

5. The fully automated bidirectional on-orbit replenishment device for spacecraft surface tension tanks based on active gas-liquid separation according to claim 4, characterized in that, The outlet (7A) of the second surface tension tank (8) is connected to the inlet (7B) of the first surface tension tank (7) in sequence through the ninth self-locking valve (35), the passive end (39) of the third docking device, the active end (38) of the third docking device, the eleventh self-locking valve (37), the electric pump (30), the flow meter (31) and the fifth self-locking valve (25); The ninth self-locking valve (35), the passive end (39) of the third docking device, the active end (38) of the third docking device, the eleventh self-locking valve (37) and the fifth self-locking valve (25) realize the isolation and communication between the liquid chambers of the first surface tension tank (7) and the second surface tension tank (8).

6. The fully automated bidirectional on-orbit replenishment device for spacecraft surface tension tanks based on active gas-liquid separation according to claim 5, characterized in that, The outlet (7A) of the first surface tension tank (7) is connected to the tenth self-locking valve (36) and the seventh self-locking valve (29) respectively through the eleventh pressure sensor (27). The electric pump (30) is connected to the seventh self-locking valve (29) and the eleventh self-locking valve (37) respectively through the fourteenth pressure sensor (42). The flow meter (31) is connected to the fifth self-locking valve (25) and the eighth self-locking valve (32) respectively through the eighth pressure sensor (22). A seventh pressure sensor (21) is provided between the inlet (7B) of the first surface tension tank (7) and the fifth self-locking valve (25). A twelfth pressure sensor is provided between the eighth self-locking valve (32) and the active end (33) of the second docking device. The device (28) is provided with a ninth pressure sensor (23) between the passive end (34) of the second docking device and the sixth self-locking valve (26), a tenth pressure sensor (24) between the sixth self-locking valve (26) and the inlet (7B) of the second surface tension tank (8), the outlet (7A) of the second surface tension tank (8) is connected to the ninth self-locking valve (35) and the twelfth self-locking valve (41) respectively through the thirteenth pressure sensor (40), a sixteenth pressure sensor (44) between the ninth self-locking valve (35) and the passive end (39) of the third docking device, and a fifteenth pressure sensor (43) between the eleventh self-locking valve (37) and the active end (38) of the third docking device.

7. The fully automated bidirectional on-orbit replenishment device for spacecraft surface tension tanks based on active gas-liquid separation according to claim 6, characterized in that, The replenishment manager (20) is used to collect the output signals of the first pressure sensor (9), the second pressure sensor (10), the third pressure sensor (11), the fourth pressure sensor (12), the fifth pressure sensor (18), the sixth pressure sensor (19), the seventh pressure sensor (21), the eighth pressure sensor (22), the ninth pressure sensor (23), the tenth pressure sensor (24), the eleventh pressure sensor (27), the twelfth pressure sensor (28), the thirteenth pressure sensor (40), the fourteenth pressure sensor (42), the fifteenth pressure sensor (43), the sixteenth pressure sensor (44), the flow meter (31), and the propellant monitoring device (14). The replenishment manager (20) monitors the propellant replenishment amount and the health status of the replenishment system, and the replenishment manager (20) drives the first docking device active end (15), the second docking device active end (33), the third docking device active end (38), the third docking device passive end (39), the first self-locking valve (3), the second self-locking valve (4), the third self-locking valve (13), the fourth self-locking valve (17), the fifth self-locking valve (25), the sixth self-locking valve (26), the seventh self-locking valve (29), the eighth self-locking valve (32), the ninth self-locking valve (35), the tenth self-locking valve (36), the eleventh self-locking valve (37), the twelfth self-locking valve (41), and the electric pump (30) through the built-in replenishment program.

8. The fully automated bidirectional on-orbit replenishment device for spacecraft surface tension tanks based on active gas-liquid separation according to claim 3, characterized in that, The propellant monitoring device (14) includes a light emitter and a photoelectric sensor, which are installed in a fixed position; When the propellant is not flowing, the photoelectric sensor can receive light emitted from the light emitter; When propellant flows through, the photoelectric sensor cannot receive the light emitted from the light emitter because the refractive index of the propellant is different from that of the gas. The photoelectric sensor changes its output signal to monitor whether propellant is flowing through.

Images