Monopropellant filling system and filling method

Abstract

The present invention provides a monopropellant filling system and filling method, which relate to the technical field of monopropellant filling. The monopropellant filling system includes an air inlet bottle, an air path module, a propellant storage tank, a filling module, and a propellant tank. When a first shut-off valve is open, gas in the air path module is transported to the propellant storage tank to pressurize the propellant tank. When a second shut-off valve is open, gas in the air inlet bottle is transported to the filling module to pressurize the filling pipeline. The filling module is arranged between the propellant storage tank and the propellant tank and is used to fill the propellant in the propellant tank into the propellant tank after the environment meets the airtightness requirements. By pressurizing the propellant storage tank and the filling pipeline to achieve airtightness inspection of the system, the system can be applied to launch sites with high safety requirements, ensuring that there is no leakage of propellant during the filling process at the launch site, avoiding harm to personnel and pollution to satellites, factories, and carrier rockets.

Description

Technical Field

[0001] The present invention relates to the technical field of monopropellant filling, and in particular to a monopropellant filling system and a filling method. Background Art

[0002] With the development of space technology, microsatellites have gained widespread application. Previously, microsatellites were allowed to enter orbit without any deorbiting devices, leaving behind a significant amount of space debris. Therefore, to meet the demands of space technology development, microsatellites need to be able to actively change orbits. Currently, the main orbit change devices used in microsatellites utilize chemical propulsion systems, which can be categorized as monopropellant and bipropellant. Monopropellant chemical propulsion is suitable for applications where satellite size is limited and high thrust output is required. However, the propellant in monopropellant propulsion systems is generally toxic, making refueling difficult. Furthermore, monopropellant refueling requires that the system be completed before the satellite is loaded at the launch site, placing higher safety requirements. Existing propellant refueling methods, lacking safety safeguards, cannot meet the refueling requirements of monopropellant propulsion systems. Summary of the Invention

[0003] The present invention provides a monopropellant filling system and a filling method, which are used to solve the defect that the traditional propellant filling method cannot meet the filling safety requirements of the monopropellant propulsion system.

[0004] The present invention provides a monopropellant filling system, comprising:

[0005] Gas inlet cylinder, gas path module, propellant storage tank, filling module and propellant storage tank;

[0006] The air inlet of the air circuit module is connected to the air inlet bottle;

[0007] A first shut-off valve is provided on the connecting pipeline between the gas outlet of the gas circuit module and the inlet of the propellant tank. When the first shut-off valve is opened, the gas in the gas circuit module is transported to the propellant tank to pressurize the propellant tank.

[0008] A second shut-off valve is provided on the connecting pipeline between the gas inlet bottle and the filling module. When the second shut-off valve is turned on, the gas in the gas inlet bottle is delivered to the filling module to pressurize the filling pipeline.

[0009] The filling module is arranged between the propellant storage tank and the propellant storage tank, and is used to fill the propellant in the propellant storage tank into the propellant storage tank after the environment meets the air tightness requirement; the meeting of the air tightness requirement includes that the pressure of the propellant storage tank reaches a first expected pressure value and the pressure of the filling pipeline reaches a second expected pressure value.

[0010] A monopropellant filling system provided according to the present invention further includes:

[0011] A vacuum pumping module, configured to perform a vacuum operation on the propellant tank;

[0012] The airtightness requirement is also satisfied, and the vacuum degree of the propellant tank is not lower than a preset threshold value after the vacuum operation is completed for a preset time.

[0013] According to a monopropellant filling system provided by the present invention, the vacuum module comprises:

[0014] vacuum pumps, diaphragm valves, vacuum gauges and bellows;

[0015] The bellows is used to connect the vacuum pump and the propellant tank;

[0016] The vacuum pump is used to extract the gas in the propellant tank;

[0017] The vacuum gauge is used to detect whether the propellant tank is vacuum;

[0018] The diaphragm valve is used to isolate the propellant in the propellant tank from the air.

[0019] According to a monopropellant filling system provided by the present invention, the gas path module comprises:

[0020] Pressure reducing valves, pressure sensors and gas filters;

[0021] The pressure reducing valve is used to reduce the pressure of the gas delivered by the gas inlet cylinder;

[0022] The pressure sensor is used to collect the air pressure of the air path module so that the air pressure after decompression meets a preset threshold;

[0023] The gas filter is used to filter the conveying gas of the gas inlet bottle.

[0024] According to a monopropellant filling system provided by the present invention, the gas circuit module further includes:

[0025] a third stop valve disposed between the gas inlet bottle and the propellant tank;

[0026] When the third shut-off valve is turned on, the propellant tank is inflated.

[0027] According to a monopropellant filling system provided by the present invention, the filling module includes:

[0028] A filling pipeline, and an electronic scale, a liquid filter and a regulating valve arranged on the filling pipeline;

[0029] The electronic scale is used to monitor the filling speed of the propellant in real time;

[0030] The regulating valve is used to adjust the injection speed of the propellant;

[0031] The liquid filter is used for filtering the propellant.

[0032] The present invention further provides a monopropellant filling system, which is applicable to the above-mentioned monopropellant filling system, comprising:

[0033] Controlling the first stop valve on the connecting pipeline between the air outlet of the gas circuit module and the inlet of the propellant storage tank to be turned on to pressurize the propellant storage tank;

[0034] Controlling the second stop valve provided on the connecting pipeline between the gas inlet bottle and the filling module to conduct, thereby pressurizing the filling pipeline;

[0035] After the environment meets the airtightness requirement, the propellant in the propellant storage tank is filled into the propellant storage tank; the meeting of the airtightness requirement includes the pressure of the propellant storage tank reaching a first expected pressure value and the pressure of the filling pipeline reaching a second expected pressure value.

[0036] A monopropellant filling method provided by the present invention further includes:

[0037] The propellant storage tank is vacuumed by a vacuum module.

[0038] According to a monopropellant filling method provided by the present invention, before pressurizing the propellant storage tank, the method further comprises:

[0039] Perform an air tightness check on the gas circuit module, connect the gas circuit module to the gas inlet bottle, and if the pressure drop of the gas circuit module does not exceed the preset pressure value within a preset time, the gas circuit module is judged to be airtight;

[0040] as well as,

[0041] The vacuum module is checked for airtightness, and the vacuum pump is operated. If the vacuum degree in the propellant tank increases after the vacuum pump is operated and does not decrease within a preset time, the vacuum module is determined to be qualified.

[0042] According to a monopropellant filling method provided by the present invention, after the propellant in the propellant storage tank is filled into the propellant storage tank, the method comprises:

[0043] controlling a third stop valve disposed between the gas cylinder and the propellant tank to be open to inflate the propellant tank;

[0044] and blowing the propellant in the filling line back into the propellant storage tank.

[0045] The present invention provides a monopropellant filling system and filling method, which includes an air inlet bottle, an air path module, a propellant storage tank, a filling module and a propellant storage tank; the air inlet of the air path module is connected to the air inlet bottle; a first stop valve is provided on the connecting pipeline between the air outlet of the air path module and the inlet of the propellant storage tank, when the first stop valve is turned on, the gas in the air path module is transported to the propellant storage tank to pressurize the propellant storage tank; a second stop valve is provided on the connecting pipeline between the air inlet bottle and the filling module, when the second stop valve is turned on, the gas in the air inlet bottle is transported to the filling module to pressurize the filling pipeline; the filling module is provided between the propellant storage tank and the propellant storage tank, and is used for filling the propellant in the propellant storage tank into the propellant storage tank after the environment meets the air tightness requirements; the meeting of the air tightness requirements includes the pressure of the propellant storage tank reaching a first expected pressure value and the pressure of the filling pipeline reaching a second expected pressure value. The present invention realizes the air tightness inspection of the system by pressurizing the propellant storage tank and the filling pipeline, and the propellant is filled after the air tightness inspection is qualified. It can be applied to launch sites with high safety requirements to ensure that there is no leakage of propellant during the filling process at the launch site, avoid harm to workers, and avoid pollution to satellites, factory buildings and carrier rockets. BRIEF DESCRIPTION OF THE DRAWINGS

[0046] In order to more clearly illustrate the technical solutions in the present invention or the prior art, a brief introduction is given below to the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0047] Figure 1 This is one of the structural schematic diagrams of the monopropellant filling system provided by the present invention;

[0048] Figure 2 This is the second structural diagram of the monopropellant filling system provided by the present invention;

[0049] Figure 3 This is the third structural diagram of the monopropellant filling system provided by the present invention;

[0050] Figure 4 This is one of the flow charts of the monopropellant filling method provided by the present invention;

[0051] Figure 5 This is the second flow chart of the monopropellant filling method provided by the present invention. DETAILED DESCRIPTION

[0052] To make the objectives, technical solutions, and advantages of the present invention more clear, the technical solutions of the present invention will be clearly and completely described below in conjunction with the accompanying drawings. Obviously, the embodiments described are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts shall fall within the scope of protection of the present invention.

[0053] Figure 1 The structural diagram of the monopropellant filling system provided in the embodiment of the present invention is as follows: Figure 1 As shown, the monopropellant filling system provided by the embodiment of the present invention includes:

[0054] Gas inlet bottle (not shown), gas path module 101, propellant storage tank 102, filling module 103 and propellant storage tank 104;

[0055] The air inlet of the air circuit module 101 is connected to the air inlet bottle;

[0056] A first shut-off valve F3 is provided on the connecting pipe between the gas outlet of the gas circuit module 101 and the inlet of the propellant storage tank 102. When the first shut-off valve F3 is turned on, the gas in the gas circuit module 101 is transported to the propellant storage tank 102 to pressurize the propellant storage tank 102.

[0057] In an embodiment of the present invention, a stainless steel hose is used to connect the filling tank pressurization interface K2 and the gas circuit module outlet K1B; high-purity nitrogen enters the gas circuit module 101 through the K1 air inlet; the pressure reducing valve J1 is adjusted to output 0.05MPa gas after the pressure reducing valve, and the output gas is displayed by a digital pressure gauge; F1 and F3 are opened in sequence to increase the pressure of the propellant storage tank 102 to 0.05MPa.

[0058] A second shut-off valve F6 is provided on the connecting pipeline between the gas inlet bottle and the filling module 103. When the second shut-off valve F6 is turned on, the gas in the gas inlet bottle is delivered to the filling module 103 to pressurize the filling pipeline.

[0059] In an embodiment of the present invention, during the positive pressure airtightness inspection of the filling pipeline, the nitrogen source is connected to F6 through a pressure reducing valve; the outlet pressure of the pressure reducer is adjusted to 0.1 MPa; F5 is opened, F4 is kept closed, and F6 is opened; the pressure reducer is adjusted to increase the pressure in the filling pipeline to 0.1 MPa; soap bubbles are applied to each joint of the pipeline. If no bubbles appear within 30 seconds, it is proved that the pipeline is airtight.

[0060] The filling module 103 is arranged between the propellant storage tank 102 and the propellant storage tank 104, and is used to fill the propellant in the propellant storage tank 102 into the propellant storage tank 104 after the environment meets the airtightness requirements; the meeting of the airtightness requirements includes that the pressure of the propellant storage tank 102 reaches a first expected pressure value and the pressure of the filling pipeline reaches a second expected pressure value.

[0061] In an embodiment of the present invention, the monopropellant filling system is a monopropellant drop pressure type propulsion system, the propellant is anhydrous hydrazine, and the pressurizing gas is high-purity nitrogen.

[0062] Traditional propellant filling methods have no safety measures and therefore cannot meet the safety requirements of a monopropellant propulsion system to complete propellant filling before loading a satellite at the launch site.

[0063] The monopropellant filling system provided by an embodiment of the present invention includes an air inlet bottle, an air path module, a propellant storage tank, a filling module and a propellant storage tank; the air inlet of the air path module is connected to the air inlet bottle; a first stop valve is provided on the connecting pipeline between the air outlet of the air path module and the inlet of the propellant storage tank, and when the first stop valve is turned on, the gas in the air path module is transported to the propellant storage tank to pressurize the propellant storage tank; a second stop valve is provided on the connecting pipeline between the air inlet bottle and the filling module, and when the second stop valve is turned on, the gas in the air inlet bottle is transported to the filling module to pressurize the filling pipeline; the filling module is provided between the propellant storage tank and the propellant storage tank, and is used to fill the propellant in the propellant storage tank into the propellant storage tank after the environment meets the air tightness requirements; the meeting of the air tightness requirements includes that the pressure of the propellant storage tank reaches a first expected pressure value and the pressure of the filling pipeline reaches a second expected pressure value. The present invention realizes the air tightness inspection of the system by pressurizing the propellant storage tank and the filling pipeline, and the propellant is filled after the air tightness inspection is qualified. It can be applied to launch sites with high safety requirements to ensure that there is no leakage of propellant during the filling process at the launch site, avoid harm to workers, and avoid pollution to satellites, factory buildings and carrier rockets.

[0064] Based on any of the above embodiments, the monopropellant filling system further includes:

[0065] A vacuum module 105 is used to perform a vacuum operation on the propellant tank 104;

[0066] The airtightness requirement is also satisfied, and the vacuum degree of the propellant tank is not less than a preset threshold value after the vacuum operation is completed for a preset time. The filling module 103 is also used to fill the propellant in the propellant storage tank 102 into the propellant tank 104 after the environment meets the airtightness requirement.

[0067] In an embodiment of the present invention, after the vacuum operation is performed, a period of time will be maintained to observe whether the vacuum degree meets the airtightness requirements. If the pressure of the propellant storage tank 102 reaches the first expected pressure value and the pressure of the filling pipeline reaches the second expected pressure value, and the vacuum degree meets the airtightness requirements, it can be determined that the airtightness of the filling system meets the requirements.

[0068] The vacuum module 105 includes:

[0069] vacuum pumps, diaphragm valves, vacuum gauges and bellows;

[0070] The bellows is used to connect the vacuum pump and the propellant tank;

[0071] The vacuum pump is used to extract the gas from the propellant tank;

[0072] The vacuum gauge is used to detect whether there is a vacuum in the propellant tank;

[0073] Diaphragm valves are used to isolate the propellant in the propellant tank from the atmosphere.

[0074] In an embodiment of the present invention, the bellows is connected to valve F7, and the liquid filling and discharge valve and valves F4, F5, and F6 are checked to see if they are in a closed state; the vacuum gauge JB1 is powered on to observe whether the vacuum gauge reading is correct; the vacuum pump is started, the valve GF1 is opened, and when the vacuum gauge JB1 reading stabilizes, the valve F7 is opened, and the gas filling and discharge valve is opened to start vacuuming the propellant tank; the liquid filling and discharge valve is opened to start vacuuming the filling pipeline; when the vacuum gauge reading stabilizes and is lower than 10Pa, the valve GF1 is closed, and the vacuum degree is checked to see if it is greater than 50Pa within 1 minute. If it is not greater than 50Pa, it indicates that the filling pipeline is airtight. If the vacuum degree cannot be maintained, the leak point is eliminated and the vacuum is re-evacuated; after the vacuum degree of the filling pipeline is qualified, F5 is opened to vacuum the pipeline between F5 and F4 until the vacuum degree is lower than 10Pa, and then F5 is closed.

[0075] In an embodiment of the present invention, the gas circuit module 101 includes:

[0076] Pressure reducing valves, pressure sensors and gas filters;

[0077] The pressure reducing valve is used to reduce the pressure of the gas delivered by the gas inlet cylinder;

[0078] The pressure sensor is used to collect the air pressure of the air path module so that the air pressure after decompression meets the preset threshold;

[0079] The gas filter is used to filter the conveying gas of the gas inlet bottle.

[0080] and, a third stop valve F7 provided between the gas inlet bottle and the propellant tank;

[0081] When the third shut-off valve F7 is opened, the propellant tank 104 is inflated.

[0082] like Figure 2 As shown, the inflation process is as follows: remove the vacuum system connected to F7; connect the pipeline system; confirm that F1, F2, F8, F7 and the gas line charging and discharging connector are in the closed state; open the main valve of the gas cylinder; open F1, adjust the pressure reducer to adjust the outlet pressure to 0.2MPa (gauge pressure); open F2 for 5 seconds and then close F2; open F8 for 5 seconds and then close F8; adjust the pressure reducer to adjust the outlet pressure to 2MPa (gauge pressure), close F1, check the air tightness within 20 minutes, and the pressure drop is not more than 0.05 to pass; open F2, close the main valve of the gas cylinder, open F1, and reduce the pressure in the pipeline to normal 1. When the pressure in the tank reaches 1.7 MPa, close F7 and close the valve core of the gas line add-drain connector. Close the main valve of the gas cylinder and open F2 to reduce the pressure in the pipeline to normal pressure. Disconnect the pipeline from F7. Open F7 and disconnect the gas line add-drain connector from the filling port. Install the plug with a tightening torque of 30 N·m.

[0083] In an embodiment of the present invention, the filling module 103 includes:

[0084] A filling pipeline, and an electronic scale, a liquid filter and a regulating valve arranged on the filling pipeline;

[0085] An electronic scale is used to monitor the propellant filling rate in real time;

[0086] The regulating valve is used to adjust the filling speed of the propellant;

[0087] Liquid filters are used to filter propellants.

[0088] Figure 1 The models and specifications of the equipment in the monopropellant filling system are shown in Table 1.

[0089] Table 1 Equipment models and specifications of monopropellant filling system

[0090]

[0091]

[0092] In an embodiment of the present invention, the liquid and gas line filling and discharge valves are closed, and valve F7 is closed; valves F4 and F5 are opened in sequence to fill the filling pipeline; when the electronic scale reading stabilizes, filling is completed and the electronic scale reading is recorded. For propellant filling, the electronic scale reading m0 is recorded after filling is completed, and the electronic scale reading m1 when filling is completed is calculated; the liquid line filling and discharge valves are slowly opened one turn to begin propellant filling. When the filling amount is greater than 50g, the liquid line filling and discharge valves are opened two turns to continue filling; when the filling amount is 50g away from the rated filling amount, the filling and discharge valves are closed one turn to reduce the filling speed. When the filling amount is 10g away from the rated filling amount, the filling and discharge valves are closed again half a turn. When the rated filling amount is reached, the filling and discharge valves are quickly closed; when the electronic scale reading is m1, the liquid line filling and discharge valves are quickly closed, and valves F5, F4, and F3 are closed, completing the filling process.

[0093] In some embodiments of the present invention, before performing the air tightness test, it also includes: propellant inspection and pressurized gas inspection. After the propellant inspection is qualified, the status of the propellant tank is inspected and recorded after the propellant arrives at the site. The inspection items include: propellant leakage, propellant tank appearance, valve status, pressure gauge status, and pressure inside the propellant tank.

[0094] The use of pressurized gas during the propellant filling process complies with relevant standards. Inspection items include: appearance of the gas cylinder, valve status, gas cylinder pressure, and whether the sealing film is intact.

[0095] like Figure 3 As shown, the monopropellant filling system also includes components such as gas filling and discharge valves and liquid filling and discharge valves. The monopropellant filling system uses a surface tension tank with a capacity of (0.62±0.02)L and an initial propellant filling ratio of 75%. The initial filling pressure of the extrusion gas nitrogen is 1.7MPa, with a drop pressure ratio of 4. The pressure after the propellant is discharged is approximately 0.425MPa. The filling and discharge system consists of two filling and discharge valves. Both the gas filling and discharge valve and the liquid filling and discharge valve have one-way shutoff functions, allowing for the filling and discharge of gas and liquid.

[0096] Figure 4 A flow chart of a method for filling a monopropellant provided in an embodiment of the present invention is shown in FIG. Figure 4 As shown, the monopropellant filling method provided by the embodiment of the present invention includes:

[0097] Step 401: Control the first shut-off valve on the connecting pipeline between the gas outlet of the gas circuit module and the inlet of the propellant tank to be turned on to pressurize the propellant tank;

[0098] Step 402: Control the second shut-off valve provided on the connecting pipeline between the gas inlet bottle and the filling module to conduct, thereby pressurizing the filling pipeline;

[0099] Step 403: After the environment meets the airtightness requirement, the propellant in the propellant storage tank is filled into the propellant storage tank; the meeting of the airtightness requirement includes the pressure of the propellant storage tank reaching a first expected pressure value and the pressure of the filling pipeline reaching a second expected pressure value.

[0100] In an embodiment of the present invention, the monopropellant filling method further includes:

[0101] The propellant storage tank is vacuumed by a vacuum module.

[0102] In an embodiment of the present invention, before pressurizing the propellant storage tank, the method further includes:

[0103] Perform an air tightness check on the gas circuit module, connect the gas circuit module to the gas inlet bottle, and if the pressure drop of the gas circuit module does not exceed the preset pressure value within a preset time, the gas circuit module is judged to be airtight;

[0104] In an embodiment of the present invention, the external gas source of the gas circuit module is 14.5MPa nitrogen. After two-stage decompression and filtration, it can output a clean gas working medium with an adjustable pressure of 0-10MPa and stability, meeting the requirements of pipeline air tightness inspection, propellant tank pressurization and propellant blowing. A 5μ gas filter is used to ensure the cleanliness of the gas. The pipeline material is 06Cr19Ni10 stainless steel pipe, which is compatible with the working medium at one level and meets the equipment requirements. The inspection items of the gas circuit module include equipment appearance inspection, air tightness inspection, and gas supply capacity inspection. When performing an air tightness inspection on the gas circuit module, connect the gas inlet bottle to K1, seal K1B with a plug, adjust the output pressure to 0.5MPa, close the main valve of the gas inlet bottle, observe the pressure change, and the pressure drop within 5 minutes does not exceed 0.05MPa to be qualified.

[0105] The vacuum module is checked for airtightness, and the vacuum pump is operated. If the vacuum degree in the propellant tank increases after the vacuum pump is operated and does not decrease within a preset time, the vacuum module is determined to be qualified.

[0106] When inspecting the vacuum module, first check whether the oil volume in the vacuum pump meets the requirements, then assemble the vacuum module. After assembly, seal the end of the pipeline with a plug, run the vacuum pump to observe whether the vacuum degree can rise normally, close valve GF1, and observe whether the vacuum degree of the pipeline can be maintained.

[0107] In this embodiment of the present invention, the refueling module piping primarily consists of an electronic scale, a liquid filter, a shutoff valve, and a regulating valve to facilitate propellant refueling. The system utilizes 06Cr19Ni10 stainless steel piping with a diameter of 4mm, and the refueling time is approximately 30 minutes. During the refueling process, the propellant level is monitored in real time using an electronic scale, and the refueling rate is adjusted using a regulating valve. A 10μ filter is used in the liquid circuit. Inspection of the refueling module includes checking the integrity and compatibility of the piping connectors, as well as the status of the electronic scale. The scale is powered on to check the weighing function.

[0108] In an embodiment of the present invention, after the propellant in the propellant storage tank is filled into the propellant storage tank, the process includes:

[0109] controlling a third stop valve disposed between the gas cylinder and the propellant tank to be open to inflate the propellant tank;

[0110] and, blowing the propellant in the filling line back into the propellant storage tank.

[0111] In the embodiment of the present invention, the gas source of the gas circuit module is turned off, valves F1 and F3 are closed, valve F2 is opened to release the pressure of the boosting pipeline, and the connecting pipelines of K1B and K2 are removed;

[0112] Connect K2 to the exhaust gas treatment device, open F3, F4, and F5 in sequence to reduce the pressure in the storage tank to normal pressure, and close F3;

[0113] Use a metal hose to connect valve F6 to the gas module outlet K1B;

[0114] Adjust the outlet pressure of the pressure reducer J1 to 0.1 MPa, open F3 and F6 in sequence, and blow the propellant in the pipeline back into the tank until the personnel hear the sound of air coming out;

[0115] Close valves F6, F5, F6 and F3 in sequence, and the liquid pipeline is blown off.

[0116] After the purge is complete, on-site staff can remove the piping connected to the gas line valve, remove the valve, and use a clean white silk cloth to clean any remaining propellant from the injection and discharge outlet. A plug can then be installed using a dedicated tool. The piping connected to the liquid line valve should also be removed. The area around the valve should be cleaned with a clean silk cloth to prevent liquid propellant from contaminating the gas components during valve removal. The valve should then be removed, and any remaining propellant inside the valve core should be wiped with a clean silk cloth. The plug can then be installed using a dedicated tool to complete the filling process. After the propellant filling is complete, propellant leakage monitoring should be conducted twice daily, before work begins in the morning and afternoon. The monitoring location should be the working hole near the tank. An anhydrous hydrazine concentration monitor should be used for a 1-minute monitoring period. The results of each monitoring session should be recorded.

[0117] like Figure 5 As shown in the figure, the refueling process begins with pressurizing the propellant tank, checking the positive pressure airtightness of the refueling pipeline, and then evacuating the system. This is a leak-proof inspection of the entire refueling pipeline to ensure that there are no leaks after refueling at the launch site, preventing harm to personnel and contamination of the satellite, plant, and launch vehicle. Once the leak-proof inspection is passed, the refueling pipeline is filled. Once the filling is complete, the propellant and pressurized gas filling begins. The remaining propellant in the pipeline is then blown back into the tank. Finally, the refueling pipeline is removed, completing the refueling process.

[0118] The device embodiments described above are merely illustrative. The units described as separate components may or may not be physically separate, and the components shown as units may or may not be physical units, i.e., they may be located in one location or distributed across multiple network units. Some or all of the modules may be selected based on actual needs to achieve the objectives of the present embodiment. Persons of ordinary skill in the art will be able to understand and implement the present invention without inventive effort.

[0119] Through the description of the above embodiments, those skilled in the art can clearly understand that each embodiment can be implemented by means of software plus a necessary general hardware platform, or of course, by hardware. Based on this understanding, the essence of the above technical solution or the part that contributes to the existing technology can be embodied in the form of a software product. The computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, a magnetic disk, an optical disk, etc., and includes a number of instructions for enabling a computer device (which can be a personal computer, a server, or a network device, etc.) to execute the methods described in each embodiment or certain parts of the embodiments.

[0120] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims

1. A monopropellant filling system, characterized in that: include: Gas inlet cylinder, gas path module, propellant storage tank, filling module and propellant storage tank; The air inlet of the air circuit module is connected to the air inlet bottle; A first shut-off valve is provided on the connecting pipeline between the gas outlet of the gas circuit module and the inlet of the propellant tank. When the first shut-off valve is opened, the gas in the gas circuit module is transported to the propellant tank to pressurize the propellant tank. A second shut-off valve is provided on the connecting pipeline between the gas inlet bottle and the filling module. When the second shut-off valve is turned on, the gas in the gas inlet bottle is delivered to the filling module to pressurize the filling pipeline. The filling module is disposed between the propellant storage tank and the propellant storage tank, and is used to fill the propellant in the propellant storage tank into the propellant storage tank after the environment meets the airtightness requirement; the airtightness requirement being met includes the pressure of the propellant storage tank reaching a first expected pressure value and the pressure of the filling pipeline reaching a second expected pressure value; A vacuum pumping module, the vacuum pumping module being used to perform a vacuum pumping operation on the propellant tank; the airtightness requirement being satisfied further comprising the vacuum degree of the propellant tank being not less than a preset threshold value after the vacuum pumping operation is completed for a preset time; During the filling process, the propellant tank is first pressurized, the filling pipeline is checked for positive pressure and airtightness, and vacuum is drawn. The airtightness of the entire filling pipeline is checked to ensure that there is no leakage of propellant after filling at the launch site. After the airtightness inspection is passed, the propellant filling pipeline is filled. After the filling is completed, the propellant filling and pressurized gas filling are started, and then the remaining propellant in the pipeline is blown back into the tank. Finally, the filling pipeline is removed to complete the filling work.

2. The monopropellant filling system according to claim 1, characterized in that: The vacuum module comprises: vacuum pumps, diaphragm valves, vacuum gauges and bellows; The bellows is used to connect the vacuum pump and the propellant tank; The vacuum pump is used to extract the gas in the propellant tank; The vacuum gauge is used to detect whether the propellant tank is vacuum; The diaphragm valve is used to isolate the propellant in the propellant tank from the air.

3. The monopropellant filling system according to claim 1, characterized in that: The gas path module comprises: Pressure reducing valves, pressure sensors and gas filters; The pressure reducing valve is used to reduce the pressure of the gas delivered by the gas inlet cylinder; The pressure sensor is used to collect the air pressure of the air path module so that the air pressure after decompression meets a preset threshold; The gas filter is used to filter the conveying gas of the gas inlet bottle.

4. The monopropellant filling system according to claim 1, characterized in that: The gas circuit module further includes: a third stop valve disposed between the gas inlet bottle and the propellant tank; When the third shut-off valve is turned on, the propellant tank is inflated.

5. The monopropellant filling system according to claim 1, characterized in that: The filling module includes: A filling pipeline, and an electronic scale, a liquid filter and a regulating valve arranged on the filling pipeline; The electronic scale is used to monitor the filling speed of the propellant in real time; The regulating valve is used to adjust the injection speed of the propellant; The liquid filter is used for filtering the propellant.

6. A method for filling a monopropellant, characterized in that: A monopropellant filling system applicable to any one of claims 1 to 5, comprising: Controlling the first stop valve on the connecting pipeline between the air outlet of the gas circuit module and the inlet of the propellant storage tank to be turned on to pressurize the propellant storage tank; Controlling the second stop valve provided on the connecting pipeline between the gas inlet bottle and the filling module to conduct, thereby pressurizing the filling pipeline; After the environment meets the airtightness requirement, the propellant in the propellant storage tank is filled into the propellant storage tank; the meeting of the airtightness requirement includes the pressure of the propellant storage tank reaching a first expected pressure value and the pressure of the filling pipeline reaching a second expected pressure value; Performing a vacuum operation on the propellant storage tank by using a vacuum module; Before pressurizing the propellant storage tank, the method further comprises: Perform an air tightness check on the gas circuit module, connect the gas circuit module to the gas inlet bottle, and if the pressure drop of the gas circuit module does not exceed the preset pressure value within a preset time, the gas circuit module is judged to be airtight; as well as, Performing an airtightness check on the vacuum pump module and operating the vacuum pump. If the vacuum degree in the propellant tank increases after the vacuum pump is operated and does not decrease within a preset time, the vacuum pump module is determined to be qualified. After the propellant in the propellant storage tank is filled into the propellant storage tank, the method includes: controlling a third stop valve disposed between the gas cylinder and the propellant tank to be open to inflate the propellant tank; and blowing the propellant in the filling line back into the propellant storage tank.

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