Propellant loading system and method for space diaphragm tanks

Abstract

A propellant filling system according to one embodiment is for filling a diaphragm tank of a satellite with propellant, and the propellant filling system may include: a pressurizing module that provides gas to be supplied to the diaphragm tank; a propellant supply module that stores propellant and provides propellant to be supplied to the diaphragm tank; and an operation module connected to the pressurizing module and the propellant supply module, which supplies pressurized gas and propellant to the diaphragm tank.

Description

Technology Field

[0001] The following description relates to a propellant filling system and method for a space diaphragm tank. Background Technology

[0003] In conventional satellite propellant filling operations, work has been centered around non-movable aspirators fixed to the launch site. While such fixed facilities provide basic ejection and neutralization functions, spatial and operational constraints existed because the pressurization panel, propellant storage containers and scales, service panel, vacuum pump, residual propellant aspirator, and residual propellant scrubber were all confined to a specific location, requiring filling operations to be performed only at that facility.

[0004] In addition, when using a diaphragm tank, the tank must be pressurized by injecting high-pressure helium (GHe) immediately after filling with propellant. At this time, it is required to inject high-purity helium, which is not contaminated by the propellant, through a separate pipe. However, in conventional technology, the gas line and the propellant line are often not provided in a form that is absolutely independent. Consequently, the distinction between the pipes and valves is not intuitive, and there is a problem in that it is difficult to rule out the risk of safety accidents caused by valve misoperation or line contamination.

[0005] Meanwhile, in order to treat toxic residual propellant and vapor after filling, it is necessary to additionally construct hazardous facilities for de-contamination, and this results in facility costs, space burden, and the risk of secondary contamination.

[0006] Therefore, there is a need for a propellant filling system that is safer, offers superior transportability, clearly separates gas and propellant piping, and can effectively decontaminate residual propellant and vapor on-site.

[0007] The aforementioned background technology is one that the inventor possessed or acquired during the process of deriving the present invention, and it cannot be considered as publicly known technology disclosed to the general public prior to the filing of the present invention. The problem to be solved

[0009] The objective according to one embodiment is to provide a propellant filling system and method for a space diaphragm tank. means of solving the problem

[0011] A propellant filling system according to one embodiment is for filling a diaphragm tank of a satellite with propellant, and the propellant filling system may include: a pressurizing module that provides gas to be supplied to the diaphragm tank; a propellant supply module that stores propellant and provides propellant to be supplied to the diaphragm tank; and an operation module connected to the pressurizing module and the propellant supply module, which supplies pressurized gas and propellant to the diaphragm tank.

[0012] The pressurization module comprises: a high-pressure gas source for storing high-pressure gas; a gas supply pipe connected from the high-pressure gas source to the operation module for supplying gas to the operation module; and a pressure regulator installed in the gas supply pipe for regulating the pressure of the gas supplied through the gas supply pipe; and the propellant supply module may comprise: a propellant supply tank for storing liquid propellant; a propellant supply pipe connected from the propellant supply tank to the operation module for supplying propellant to the operation module; and an inlet pipe branched from and connected to the gas supply pipe of the pressurization module to receive pressurized gas for supplying propellant.

[0013] The above-described operation module includes: a pressurizing line that supplies pressurized gas flowing in from the gas supply pipe to the gas-side port of the diaphragm tank; and a filling line that supplies propellant flowing in from the propellant supply pipe to the propellant-side port of the diaphragm tank; wherein the pressurizing line includes a pressurizing control valve installed in the pressurizing line and capable of controlling the flow rate of gas supplied to the diaphragm tank; and the filling line may include a propellant control valve installed in the filling line and capable of controlling the flow rate of propellant supplied to the diaphragm tank.

[0014] The above-described operation module may further include a cross-interlocking part that selectively connects the part of the pressurization line located downstream of the pressurization control valve and the part of the filling line located downstream of the propellant control valve, thereby allowing pressurized gas supplied through the pressurization line to be applied to the gas-side port and the propellant-side port of the diaphragm tank.

[0015] The above-mentioned cross-linking section comprises: a linkage pipe detachably installed between the pressurizing line and the filling line; a first isolation valve installed at the portion where the pressurizing line is connected to the linkage pipe to selectively block the flow path; and a second isolation valve installed at the portion where the filling line is connected to the linkage pipe to selectively block the flow path; and during the process of filling the diaphragm tank with propellant, the first isolation valve and the second isolation valve may be closed, and the linkage pipe may be configured to remain in a detached state.

[0016] The above-described operation module may further include a propellant recovery unit connected to a point adjacent to the end of the section of the filling line where the filling line is connected to the diaphragm tank, for pushing back residual propellant remaining in the filling line toward the propellant supply tank.

[0017] The propellant recovery unit may include: a recovery line branched from the filling line and connected to the inlet pipe of the propellant supply module; and a recovery valve installed in the recovery line that can selectively open and close a flow path communicating with the filling line.

[0018] The end of the recovery line branching off from the filling line can be joined at the point where the inlet pipe branches off from the gas supply pipe.

[0019] A propellant filling system according to one embodiment may further include: a vacuum module having a vacuum pump that forms a vacuum and a vacuum line connected from the vacuum pump to the filling line; and a residual propellant removal module connected to the filling line and for removing the propellant remaining in the filling line through a vacuum applied from the vacuum pump after the propellant filling of the diaphragm tank is completed.

[0020] Each of the above-mentioned pressurization module and the above-mentioned operation module has a movable panel-type configuration in which an internal flow path, a flow path switching configuration, and a flow rate control configuration are integrated, and can be configured to be interconnected and used after being transported to a place where propellant filling operations are performed.

[0021] The above residual propellant removal module may further include: a vacuum recovery vessel that primarily sucks in the liquid propellant remaining in the filling line; and a separator that secondarily sucks in the liquid propellant and residual vapor remaining in the filling line and separates the liquid and gas from the incoming fluid.

[0022] The vacuum recovery vessel comprises a first suction line connected from the filling line to suck residual liquid propellant into the vacuum recovery vessel; and the separator comprises a second suction line connected from the filling line to suck residual liquid propellant and residual vapor; and in the section of the filling line, the connection point of the first suction line may be located at a point closer to the vacuum line than the connection point of the second suction line.

[0023] A method for filling a propellant into a diaphragm tank of a satellite according to one embodiment comprises: a pressurizing module that receives a high-pressure gas source and provides pressurized gas; a propellant supply module that stores and provides propellant; an operation module that supplies the pressurized gas and the propellant to the diaphragm tank; a vacuum module connected to the operation module that applies a vacuum; and a residual propellant removal module that removes residual propellant from the operation module, thereby constructing a ground module system by interconnecting a pressurizing line that supplies the pressurized gas and a filling line that supplies the propellant through the operation module to the gas-side port and the propellant-side port of the diaphragm tank, respectively; a step of vacuuming the interior of the system including the diaphragm tank and the filling line to a predetermined vacuum level using the vacuum module; a step of filling the diaphragm tank with propellant through the filling line; and a step of removing residual propellant remaining in the filling line. and may include the step of pressurizing the diaphragm tank to the final operating pressure and separating it.

[0024] The step of constructing the above ground module system may include a step of verifying the soundness of the ground module system by performing a leakage test by supplying pressurized gas from the pressurizing module to pressurize it to a predetermined pressure, and then performing a vacuum leakage test based on the change in vacuum level after vacuuming it to a predetermined vacuum level using the vacuum module.

[0025] The above-described operation module further includes a cross-interlocking unit that selectively connects the pressurization line and the filling line; and the step of establishing the satellite interface includes the step of supplying pressurized gas from the pressurization module to pressurize the system of the diaphragm tank and ground modules to a pressure corresponding to the maximum operating pressure, and performing an MEOP leak test to determine whether there is a leak based on the amount of pressure change at the pressure state corresponding to the maximum operating pressure; and the step of performing the MEOP leak test may allow the pressurized gas supplied through the pressurization line to be simultaneously supplied to the gas-side port and the propellant-side port of the diaphragm tank while the cross-interlocking unit is installed.

[0026] The above cross-interlocking unit includes an interlocking pipe that is detachably installed to connect the pressurizing line and the filling line, and a first isolation valve and a second isolation valve installed at each end of the interlocking pipe, respectively, and the step of establishing the satellite interface may further include the step of isolating the pressurizing line and the filling line by detaching the interlocking pipe constituting the cross-interlocking unit and closing the first isolation valve and the second isolation valve after the step of performing the MEOP leakage test.

[0027] The step of removing the residual propellant may include the step of recovering the residual propellant by pushing the propellant remaining in the filling line back to the propellant supply module using pressurized gas supplied from the pressurizing module while opening a recovery valve installed in a recovery line that branches off from a point adjacent to the diaphragm tank of the filling line and is connected to the propellant supply module.

[0028] The step of removing the residual propellant may further include: a step of removing the residual liquid propellant through a vacuum recovery vessel that primarily sucks up the liquid propellant remaining in the filling line using a vacuum applied by the vacuum module; and a step of removing the residual vapor remaining in the filling line through a separator that sucks up the liquid propellant and residual vapor remaining in the filling line using the vacuum and separates the liquid and gas from the incoming fluid. Effects of the invention

[0030] According to a propellant filling system and method of one embodiment, ground support equipment centered on a pressurization module and an operation module can be implemented in a movable modular / panel type configuration. Consequently, without relying on fixed facilities, the system can be transported to the site where propellant filling operations are performed, quickly established on-site, and easily dismantled upon completion of the work. As a result, applicability and operational flexibility are enhanced not only at domestic and international remote launch sites but also in operational environments with significant site constraints, such as launch campaigns.

[0031] According to a propellant filling system and method according to one embodiment, pressurized gas can be selectively and simultaneously applied to the gas side and the propellant side during an MEOP leak test by means of a cross-interlocking unit provided in an operating module, thereby enabling efficient leak verification of the integrated system. Furthermore, after the MEOP leak test, the pressurized line and the filling line can be triple-isolated by detaching the interlocking pipe and closing the isolation valves on both sides, thereby ensuring the independence of the gas flow path and the propellant flow path during the filling operation and reducing the risk of safety accidents caused by contamination and abnormal communication.

[0032] According to the propellant filling system and method of one embodiment, after filling is completed, residual liquid in the piping can be preferentially pushed back toward the propellant supply tank for recovery through the recovery of the propellant, thereby reducing the amount of residual propellant without external discharge, thereby reducing the burden of subsequent decontamination and gradually reducing the risk of exposure due to residual propellant.

[0033] According to the propellant filling system and method of one embodiment, residual liquid phase and residual vapor can be removed stepwise using a vacuum recovery vessel and a separator during the residual propellant removal step, thereby improving safety in handling propellants with high vapor toxicity such as hydrazine and preventing the risk of equipment contamination and diffusion into the workspace. Brief explanation of the drawing

[0035] FIG. 1 is a drawing showing the configuration of a propellant filling system according to one embodiment. FIG. 2 is a block diagram of a propellant filling system according to one embodiment. FIG. 3 is a flowchart of a propellant filling method according to one embodiment. FIG. 4 is a flowchart of the steps for constructing a ground module system according to one embodiment. FIG. 5 is a flowchart of the steps for constructing a satellite interface according to one embodiment. FIG. 6 is a diagram showing the configuration of a propellant filling system in the step of constructing a satellite interface according to one embodiment. FIG. 7 is a diagram showing the configuration of a propellant filling system in the step of performing propellant filling according to one embodiment. FIG. 8 is a flowchart of the step of removing residual propellant according to one embodiment. FIG. 9 is a diagram showing the configuration of a propellant filling system in the step of performing final pressurization and separation according to one embodiment. Specific details for implementing the invention

[0036] Hereinafter, embodiments will be described in detail with reference to the attached drawings. The following description is one of several aspects of the embodiments, and the following description constitutes part of the detailed description of the embodiments.

[0037] However, in describing one embodiment, specific descriptions regarding known functions or configurations are omitted to clarify the gist of the present invention.

[0038] In addition, terms or words used in this specification and claims should not be interpreted in their ordinary or dictionary senses, and based on the principle that the inventor can appropriately define the concept of the terms to best describe his invention, they shall have a meaning and concept consistent with the technical idea of ​​the propellant filling system and method for a space diaphragm tank according to one embodiment.

[0039] Therefore, the embodiments described in this specification and the configurations illustrated in the drawings are merely the most preferred embodiment of the propellant filling system and method for a space diaphragm tank according to one embodiment, and do not represent all technical concepts of the propellant filling system and method for a space diaphragm tank according to one embodiment; thus, it should be understood that various equivalents and modifications that can replace them may exist at the time of filing this application.

[0040] FIG. 1 is a diagram showing the configuration of a propellant filling system according to one embodiment, and FIG. 2 is a block diagram of a propellant filling system according to one embodiment.

[0041] A propellant filling system (1) according to one embodiment is an integrated ground operating system for safely and repeatedly filling a toxic or low-toxicity liquid propellant into a diaphragm tank (151) of a satellite propulsion system tank section (15).

[0042] For example, the propellant filling system (1) is not a single integrated unit, but is composed of multiple modules functionally separated for pressurization, propellant supply, fluid operation, residue removal, decontamination, satellite connection and instrumentation control, and each module can be configured in a transportable form.

[0043] For example, the propellant filling system (1) functions as a unit that can be moved and installed at a location where filling work is required, and can be safely linked with the satellite propulsion system tank unit (15) to perform filling, pressurization, residual removal, and decontamination processes in a series of procedures.

[0044] The satellite propulsion system tank section (15) includes a propellant tank mounted on the satellite and valves connected thereto, and forms an interface with the ground system.

[0045] The satellite propulsion system tank section (15) may include a diaphragm tank (151), a filling discharge valve (152), and a filling vent valve (153).

[0046] The diaphragm tank (151) is a tank with a structure in which a diaphragm is installed inside, separating the gas space and the propellant space.

[0047] For example, the diaphragm tank (151) may include a propellant-side port (1511) into which propellant is introduced or discharged, and a gas-side port (1512) into which gas is introduced or discharged.

[0048] The fill discharge valve (152) is an FDV (Fill and Drain Valve) valve installed at the propellant-side port of the diaphragm tank (151) to connect or block the propellant supply pipe (1322) of the operation module (13) and the propellant space inside the diaphragm tank.

[0049] The fill vent valve (153) is a Fill and Vent Valve (FVV) installed at the gas-side port of the diaphragm tank (151) and serves to connect or block the gas space of the diaphragm tank with the gas connection line (1312) of the operation module (13).

[0050] For example, the propellant filling system (1) may include a pressurizing module (11), a propellant supply module (12), an operation module (13), a vacuum module (16), a residual propellant removal module (14), and a control unit (17).

[0051] The pressurizing module (11) performs the role of providing pressurized gas required for the propellant filling system (1) and regulating the pressure.

[0052] For example, the pressurizing module (11) is a device that provides pressurized gas to be supplied to the diaphragm tank (151), and can be used to pressurize the propellant supply tank (121) and / or the gas-side port (1512) of the diaphragm tank (151) during the propellant filling process.

[0053] For example, the pressurization module (11) may include a high-pressure gas source (111), a pressure regulator (112), a first pressure gauge (113), a second pressure gauge (114), and a gas supply pipe (115).

[0054] The high-pressure gas source (111) is a container for storing high-pressure gas, and can store, for example, high-purity inert gas (e.g., helium). The gas supplied from the high-pressure gas source (111) can be depressurized and measured through the pressurization module (11) and then transferred to the operation module (13).

[0055] The pressure regulator (112) is a regulator that reduces the pressure of high-pressure gas supplied from the high-pressure gas source (111) to a pressure suitable for operation. Through this, the pressure of the pressurized gas supplied to the pressurization line (131) or the inlet pipe (125) of the propellant supply module (12) can be stably maintained at a set level.

[0056] The first pressure gauge (113) and the second pressure gauge (114) are configured to measure the gas pressure on the side of the pressurizing module (11). The two pressure gauges can be distinguished according to the measurement range / precision or the purpose of operation. Specifically, the first pressure gauge (113) can be configured as a rough gauge to roughly check a relatively wide range of pressure, and the second pressure gauge (114) can be configured as a fine gauge to precisely measure minute pressure changes in tests where the amount of pressure change is very small, such as a leak test.

[0057] The gas supply pipe (115) is a pipe that delivers pressurized gas from the pressurization module (11) to the operation module (13) and / or the propellant supply module (12).

[0058] The gas supply pipe (115) is connected to the pressurization line (131) of the operation module (13) to perform tank pressurization or pressurization for leak testing, and is also branched to the inlet pipe (125) of the propellant supply module (12) to be used for pressurizing the propellant supply tank (121).

[0059] For example, the pressurizing module (11) may have a movable panel-type configuration in which a pressure supply / control configuration including a pressure regulator (112) and a pressure gauge is integrated.

[0060] Accordingly, pressure conditions required at each operational stage, such as leak testing, MEOP pressurization, and final pressurization, can be reproducibly formed regardless of the field environment.

[0061] The propellant supply module (12) stores liquid propellant and supplies the propellant to the operation module (13).

[0062] For example, the propellant supply module (12) may include a propellant supply tank (121), a scale (122), a tank pressure gauge (123), a propellant supply pipe (124), and an inlet pipe (125).

[0063] The propellant supply tank (121) is a container for storing propellant. For example, the propellant supply tank (121) is configured as a mobile storage container, which can be transported to a site where propellant filling operations are performed and then connected to a system to store and supply propellant.

[0064] For example, the propellant supply tank (121) may be equipped with a valve (vapor valve) for opening and closing the gas side and a valve (liquid valve) for opening and closing the liquid outlet, and accordingly, functionally separated flow path control may be possible for each operation mode such as propellant filling, recovery, standby, and gas application.

[0065] For example, the propellant supply tank (121) may be kept separated with the connection port sealed with a cap or plug until the filling procedure of the diaphragm tank (151) is performed as shown in FIG. 6.

[0066] A scale (122) may be installed to measure changes in weight of the propellant supply tank (121). The scale (122) may be used to calculate the amount of propellant to be filled or to determine whether filling is complete.

[0067] The tank pressure gauge (123) is configured to monitor the internal pressure of the propellant supply tank (121) and can contribute to preventing overpressure and stable operation during propellant supply.

[0068] The propellant supply pipe (124) is a pipe that receives pressurized gas from the pressurizing module (11) and delivers propellant from the propellant supply tank (121) to the filling line (132) of the operating module (13).

[0069] The inlet pipe (125) is a pipe for supplying pressurized gas branched from the pressurization module (11) to the propellant supply tank (121).

[0070] For example, the inlet pipe (125) allows the recovery line (1342) of the operation module (13) to be connected to the inlet pipe (125) during residual propellant recovery (Push-back) operation, so that the propellant remaining in the filling line (132) is diverted toward the propellant supply tank (121) and recovered into the propellant supply tank (121).

[0071] The operation module (13) can serve as a hub for integrally controlling fluid flow paths when delivering gas and propellant supplied from the pressurization module (11) and the propellant supply module (12) to the satellite propulsion system tank section (15) and performing tasks such as filling, pressurizing, leak testing, propellant recovery, and removal of residual propellant.

[0072] For example, the operation module (13) may include a pressurization line (131), a filling line (132), a cross-interlocking section (133), a propellant recovery section (134), a propellant discharge line (135), a residual steam discharge line (136), and a panel pressure gauge (137).

[0073] The pressurization line (131) is a line that delivers pressurized gas supplied from the pressurization module (11) to the gas-side port (1512) of the diaphragm tank (151).

[0074] For example, the pressurization line (131) may include a pressurization control valve (1311) and a gas connection line (1312).

[0075] The pressure control valve (1311) is a valve configuration that controls the flow rate or pressure speed of the pressurized gas supplied through the pressure line (131). For example, the pressure control valve (1311) may be a needle valve capable of fine control of the flow path.

[0076] The gas connection line (1312) is a line that extends from the part of the pressurization line (131) to be connected to the gas side port (1512) of the diaphragm tank (151).

[0077] The filling line (132) is a line that delivers the propellant supplied from the propellant supply module (12) to the propellant side port (1511) of the diaphragm tank (151).

[0078] For example, the filling line (132) may include a propellant control valve (1321) and a propellant connection line (1322).

[0079] The propellant control valve (1321) is a valve configuration for controlling the flow rate of propellant supplied through the filling line (132). For example, the propellant control valve (1321) may be a needle valve capable of fine control of the flow path.

[0080] The propellant connection line (1322) is a line that extends from the part of the pressurization line (131) to be connected to the propellant side port (1511) of the diaphragm tank (151).

[0081] As described above, since the pressure control valve (1311) and the propellant control valve (1321) of the operation module (13) are each composed of needle valves, rapid fluctuations in pressure and flow rate during the filling and final pressurization processes can be suppressed and step-by-step operating conditions can be reproducibly implemented, thereby improving operational reliability in operations requiring safety and stability, such as filling toxic / low-toxicity propellants.

[0082] The cross-linking section (133) can selectively connect the pressurizing line (131) and the filling line (132) in a specific operating mode, such as a leak test under conditions of Maximum Operating Pressure (MOP) or Maximum Expected Operating Pressure (MEOP), so that pressurized gas is applied to the filling line (132) side as well, thereby allowing the gas side and the propellant side of the diaphragm tank (151) to be pressurized simultaneously.

[0083] For example, the cross-linkage section (133) can selectively control communication between the gas connection line (1312) located downstream of the pressure control valve (1311) in the pressure line (131) and the propellant connection line (1322) located downstream of the propellant control valve (1321) in the filling line (132).

[0084] For example, the cross-interlocking section (133) may include an interlocking pipe (1333), a first isolation valve (1331), and a second isolation valve (1332).

[0085] The interlocking pipe (1333) is a pipe that is detachably installed between the pressurization line (131) and the filling line (132).

[0086] For example, the interlocking pipe (1333) can be installed when cross-connection is required, such as for a leak test under maximum operating pressure (MOP) or maximum expected operating pressure (MEOP) conditions, and can be removed (detached) during normal filling operation to maintain a physically separated state.

[0087] The first isolation valve (1331) is a valve installed at the part where the pressurized line (131) is connected to the interlocking pipe (1333) to selectively block the flow path.

[0088] The second isolation valve (1332) is a valve installed at the part where the filling line (132) is connected to the interlocking pipe (1333) to selectively block the flow path.

[0089] In the process of performing a leak test under MEOP conditions, as shown in FIG. 6, the interlocking pipe (1333) is installed between the pressurizing line (131) and the filling line (132), and the first and second isolation valves (1331, 1332) are opened so that the interlocking circuit between the pressurizing line (131) and the filling line (132) can be interconnected.

[0090] After the MEOP leak test or during normal filling operation, as shown in FIG. 7, the first isolation valve (1331) and the second isolation valve (1332) are closed and the interlocking pipe (1333) is removed to maintain a physically separated state, thereby triple isolating the pressurizing line (131) and the filling line (132), which can reduce contamination and safety risks during normal filling operation.

[0091] The propellant recovery unit (134) can recover the propellant remaining in the filling line (132) after filling is complete by pushing it back toward the propellant supply tank (121).

[0092] For example, the propellant recovery unit (134) may include a recovery line (1342) and a recovery valve (1341).

[0093] The recovery line (1342) can be branched off from the diaphragm tank (151) in the propellant connection line (1322) and connected to the inlet pipe (125) on the propellant supply module (12).

[0094] For example, the recovery line (1342) may have a structure in which it joins at an intersection point where the inlet pipe (125) branches off from the gas supply pipe (115).

[0095] The recovery valve (1341) is a valve installed at the point where the recovery line (1342) is connected from the propellant connection line (1322) to selectively open and close the flow path.

[0096] The propellant discharge line (135) is a line that transfers liquid residual propellant to the residual propellant removal module (14). For example, the propellant discharge line (135) can be branched from the filling line (132) and connected to a vacuum recovery container (141).

[0097] For example, the propellant discharge line (135) may include a first discharge valve (1351) that can selectively open and close the flow path.

[0098] The residual steam discharge line (136) is a line for guiding steam components generated or remaining during the residual propellant removal process toward the residual propellant removal module (14). For example, the residual steam discharge line (136) can be branched from the filling line (132) and connected to the separator (142).

[0099] For example, the residual steam discharge line (136) may include a second discharge valve (1352) that can selectively open and close the flow path.

[0100] For example, in the section of the filling line (132), the connection point of the propellant discharge line (135) may be located closer to the vacuum line (162) than the connection point of the residual steam discharge line (136).

[0101] In other words, by positioning the vacuum recovery container (141) in a suction path closer to the vacuum pump (161) than to the separator (142), the majority of the residual propellant can be preferentially sucked in through the vacuum recovery container (141) first, and then the small amount of droplets and vaporized vapor of the propellant remaining in the filling line (132) can be sucked in through the separator (142).

[0102] The panel pressure gauge (137) is a measuring instrument for monitoring the pressure / vacuum status of an area of ​​the operation module (13) or a specific line (pressurization line, filling line, etc.), and can be used to determine leak testing, vacuuming, and residual removal operation.

[0103] For example, the operation module (13) may have a movable panel-type configuration that includes a pressurization line (131) and a filling line (132), with integrated flow switching and flow control functions, and can be transported to the site where propellant filling is performed and quickly connected to other modules via piping to establish an operation system, and simplifies the switching of operation modes, including flow control, during leak testing and the process of removing residue after filling, thereby enabling safe and intuitive operation while maintaining the independence of the gas flow path and the propellant flow path.

[0104] The vacuum module (16) creates a vacuum within the system, enabling vacuum leakage testing, tank vacuuming, and removal of residual propellant.

[0105] For example, the vacuum module (16) may include a vacuum pump (161) and a vacuum line (162).

[0106] The vacuum pump (161) is a vacuum source that vacuums the filling line (132) and the inside of the related system to a predetermined vacuum level.

[0107] The vacuum line (162) is a line connecting the vacuum pump (161) to the filling line (132).

[0108] The residual propellant removal module (14) is configured to remove liquid propellant and residual vapor remaining in the filling line (132) and associated piping.

[0109] For example, the residual propellant removal module (14) may be configured to suck and transport residual fluid using a vacuum (or a pre-vacuumed state) applied from a vacuum module (16), and to first collect the liquid phase in a vacuum recovery container (141), and then perform liquid-gas separation and subsequent processing of the gaseous component in a separator (142).

[0110] For example, the residual propellant removal module (14) may include a vacuum recovery vessel (141), a separator (142), and a decontamination unit (143).

[0111] The vacuum recovery container (141) can suck in and receive the liquid propellant remaining in the filling line (132). For example, the vacuum recovery container (141) can perform the function of a vacuum recovery container (aspirator) that primarily collects (receives) the residual liquid flowing into the filling line (132).

[0112] For example, the vacuum recovery container (141) may include a first suction line (1411) that branches off from the filling line (132) and connects to the vacuum recovery container (141).

[0113] For example, the vacuum recovery container (141) may be vacuumed during operation by a vacuum pump (161) or maintained in a vacuumed state in advance, and residual fluid may be guided to the container (141) side when the first suction line (1411) is opened.

[0114] The separator (142) can draw in residual liquid propellant and residual vapor from the filling line (132) during residual removal operation and can separate the liquid and gas (vapor) from the incoming fluid.

[0115] For example, the separator (142) may be configured to separate residual vapor that may be introduced along with residual liquid propellant, so that the liquid phase is guided to a recovery or safe treatment path and the gaseous component is delivered to a decontamination unit (143).

[0116] For example, the separator (142) may include a liquid separator or scrubber function that captures droplets or absorbs and removes gaseous components.

[0117] For example, the separator (142) may include a second suction line (1421) that branches off from the filling line (132) and connects to the separator (142).

[0118] For example, among the filling lines (132), the connection point of the first suction line (1411) may be positioned closer to the vacuum application point (the connection point of the vacuum line (162)) compared to the connection point of the second suction line (1421).

[0119] According to the above structure, the liquid propellant is first collected in the vacuum recovery container (141) through the first suction line (1411), and then the residual gaseous component is processed in the separator (142) through the second suction line (1421), thereby ensuring operational stability.

[0120] The decontamination unit (143) is connected to safely process the gaseous component (residual vapor) separated from the separator (142), and is a device for decontaminating or safely treating contaminated or toxic vapor.

[0121] For example, as shown in FIG. 6, the vacuum recovery container (141) and separator (142) of the residual propellant removal module (14) can be separated from the operation module (13) until the propellant is filled into the diaphragm tank (151), and for example, the port ends of the vacuum recovery container (141) and separator (142) can be sealed with a cap or plug to prevent external contamination from entering.

[0122] According to the residual propellant removal module (14) of one embodiment, considering the characteristics of a propellant with high vapor toxicity such as hydrazine, the residual propellant can be removed not only by simply inhaling it but also by including the vaporized parts.

[0123] Specifically, the residual propellant removal module (14) can first actively remove the liquid residue remaining in the filling line (132) when the filling of the propellant into the diaphragm tank (151) is complete, and then additionally vacuum suction the remaining residual vapor and trace amounts, and finally capture and detoxify the toxic vapor through liquid / gas separation. Compared to the method of suctioning only with an aspirator as in the prior art, the removal target and stage are clearly demarcated, so the risk reduction path is clear and safety can be enhanced.

[0124] For example, a pressurization module (11), a propellant supply module (12), an operation module (13), a residual propellant removal module (14), and a vacuum module (16) are each provided in a transportable modular configuration and can be moved to a location where propellant filling work is performed and then interconnected for use.

[0125] For example, modules (11, 12, 13, 14, 16) spaced apart from each other upon arrival at the site can be quickly connected via separate piping to form a system, and any piping or ports not used for operation can be sealed by a cap or plug to reduce the risk of contamination ingress and leakage.

[0126] For example, the pressurization module (11) and the operation module (13) have a movable panel-type configuration so that they can be transported to the site where propellant filling work is performed without relying on fixed facilities, and then interconnected to quickly establish a system.

[0127] In other words, the pressurizing module (11) and the operating module (13) may have a movable panel-type configuration in which internal flow paths, flow path switching configurations, and flow control configurations are integrated. In other words, the pressurizing module (11) and the operating module (13) may each be implemented in a form in which multiple pipes, manifolds (distribution flow paths), valves, and measuring instruments are mounted on a movable panel frame, and during field operation, they may be connected to other modules via pipes through the connection ports of the panel.

[0128] According to the above structure, the inter-module system can be rapidly constructed and dismantled on-site without relying on fixed facilities, and operation procedures (leakage testing, vacuuming, filling, residue removal, etc.) can be consistently performed within the same device configuration.

[0129] The control unit (17) can perform a propellant filling procedure for the satellite propulsion system tank unit (15) by monitoring and controlling the operation procedure of each module (11, 12, 13, 14, 16) of the propellant filling system (1).

[0130] For example, the control unit (17) may be installed by connecting it to the operation module (13) via a wired or wireless method, and according to one embodiment, it may be formed integrally with the operation module (13) and placed inside the panel or within the same housing.

[0131] In addition, according to another embodiment, the control unit (17) may be configured as an independent module separated from the pressurization module (11) and the operation module (13), thereby having a modular structure that is easy to move and install. In this case, the control unit (17) may be selectively positioned according to field conditions and operating environment and interconnected with each module via signal lines or communication interfaces, so as to perform measurement, control, and operation status monitoring functions for the entire propellant filling system.

[0132] A specific method for filling the propellant through the control unit (17) is described later through FIGS. 3 to 8.

[0133] According to the propellant filling system (1) of one embodiment, ground support equipment centered on a pressurizing module and an operation module can be implemented in a movable module / panel type configuration. Therefore, without relying on fixed facilities, the system can be transported to a location where propellant filling work is performed, quickly established on-site, and easily dismantled upon completion of the work. Accordingly, applicability and operational flexibility are improved not only at domestic and international remote launch sites but also in operational environments with significant site constraints, such as launch campaigns.

[0135] FIG. 3 is a flowchart of a propellant filling method according to one embodiment, FIG. 4 is a flowchart of a step of constructing a ground module system according to one embodiment, FIG. 5 is a flowchart of a step of constructing a satellite interface according to one embodiment, FIG. 6 is a diagram showing the configuration of a propellant filling system in the step of constructing a satellite interface according to one embodiment, FIG. 7 is a diagram showing the configuration of a propellant filling system in the step of performing propellant filling according to one embodiment, FIG. 8 is a flowchart of a step of removing residual propellant according to one embodiment, and FIG. 9 is a diagram showing the configuration of a propellant filling system in the step of performing final pressurization and separation according to one embodiment.

[0136] Referring to FIGS. 3 to 9, the configuration of a propellant filling method according to one embodiment can be seen.

[0137] A propellant filling method according to one embodiment is a method of procedurally performing the processes of propellant filling, pressurization, residual removal, decontamination, and final pressurization for a satellite body propellant system tank part (15) through a propellant filling system (1) according to the embodiment shown in FIG. 1 and FIG. 2.

[0138] For example, the propellant filling method can be performed under the control of the control unit (17) of the propellant filling system (1) according to one embodiment.

[0139] A propellant filling method according to one embodiment may include a step of constructing a ground module system (21), a step of constructing a satellite interface (22), a step of vacuuming a tank (23), a step of performing filling (24), a step of removing residual propellant (25), and a step of performing final pressurization and separation (26).

[0140] The step (21) of constructing a ground module system is to place ground modules, consisting of a pressurizing module (11), a propellant supply module (12), an operation module (13), a vacuum module (16), and a residual propellant removal module (14), at a location where propellant filling operations are performed, and then connect each module with pipes to form a single ground filling system so that gas, propellant, and vacuum passages are continuously formed.

[0141] For example, the step of constructing a ground module system (21) may include a step of connecting modules (211) and a step of verifying the soundness of the ground module system (212).

[0142] In the step (211) of connecting the modules, a ground module system can be constructed by interconnecting the pressurizing module (11), the operation module (13), and the vacuum module (16) at the work site with piping.

[0143] For example, in the step (211) of connecting the modules, the propellant supply module (12) and the residual propellant removal module (14) may be connected and installed to the operation module (13), but the propellant supply tank (121) of the propellant supply module (12) and the vacuum recovery vessel (141) and separator (142) of the residual propellant removal module (14) may be kept separated until the step (24) of performing the filling.

[0144] The step (212) of verifying the soundness of the ground module system is a procedure to verify the soundness of the ground module system after the ground module system is constructed and before the satellite is connected.

[0145] For example, in the step (212) of verifying the soundness of the ground module system, pressurized gas can be supplied from the pressurizing module (11) to pressurize the piping and connections inside the operation module (13), including the ground piping, to a predetermined pressure, and a pressure leakage test can be performed to determine whether there is a leak based on the amount of pressure change over a certain period of time.

[0146] For example, in the step (212) of verifying the soundness of the ground module system, the vacuum pump (161) of the vacuum module (16) is driven to vacuum the piping and connections inside the operation module (13), including the ground piping, to a predetermined vacuum level, and then a vacuum leak test can be performed to determine whether there is a leak based on the change in vacuum level.

[0147] The step (22) of establishing a satellite interface is to connect the pressurization line (131) and the filling line (132) of the ground system to the gas-side port (1512) and the propellant-side port (1511) of the satellite propulsion system tank section (15), respectively, so as to form an integrated system in which the ground module system and the satellite tank system are fluidly combined.

[0148] For example, the step of establishing a satellite interface (22) may include the step of performing a MEOP leakage test (221) and the step of isolating between the pressurization line and the filling line (222).

[0149] The step (221) of performing an MEOP leakage test is a step of performing a leakage test under maximum operating pressure conditions to determine whether there is leakage under maximum operating pressure (MOP) or maximum expected operating pressure (MEOP) conditions after satellite interlocking.

[0150] At this time, the pressurizing line (131) and the filling line (132) can be configured to be selectively connected through the cross-linking part (133) of the operating module (13). Specifically, the interlocking pipe (1333) is installed between the pressurizing line (131) and the filling line (132), and the first and second isolation valves (1331, 1332) are opened so that the mutual circuit between the pressurizing line (131) and the filling line (132) can be interconnected.

[0151] Accordingly, under conditions where pressurized gas is supplied from the pressurization module (11) to simultaneously apply a pressure corresponding to the maximum operating pressure to both the gas side and the propellant side of the diaphragm tank (151), the integrity of the integrated system including the satellite propulsion system tank section (15) and the ground system can be verified by determining whether there is a leak based on the measured amount of pressure change.

[0152] For example, in the step (221) of performing the MEOP leakage test, when pressurizing the diaphragm tank (151), fine adjustment can be performed through the pressurization control valve (1311) and the propellant control valve (1321) to control / maintain the pressurization / depressurization speed below a specific value according to the internal diaphragm characteristics of the diaphragm tank.

[0153] The step (222) of isolating the pressurization line and the filling line is performed after the step (221) of performing the MEOP leakage test is completed, and the first isolation valve (1331) and the second isolation valve (1332) of the cross-interlocking section (133) are closed, and the interlocking pipe (1333) is removed (detach) to physically disconnect the pressurization line (131) and the filling line (132).

[0154] According to the above structure, a triple isolation structure can be implemented by blocking the flow path through the first isolation valve (1331) and the second isolation valve (1332) and simultaneously removing the interlocking pipe (1333) which is the passage between them. Through this, the independence of the flow paths of the pressurization line (131) and the filling line (132) is secured during the subsequent propellant filling stage, and the risk of contamination and abnormal mixing of high-purity gas injection can be blocked.

[0155] The step (23) of vacuuming the tank can remove residual gas and impurities before filling or fix the physical initial conditions of filling / pressurization by using a vacuum module (16) to reduce the pressure inside the diaphragm tank (151) to a predetermined vacuum level.

[0156] The step (24) of performing filling is to apply driving pressure to the propellant supply tank (121) or propellant supply pipe (124) using pressurized gas, and to transfer and inject liquid propellant into the satellite diaphragm tank (151) through the propellant supply pipe (124) and the filling line (132).

[0157] As illustrated in FIGS. 6 and 7, if the connection port of the propellant supply tank (121) is blocked or sealed prior to the step (24) of performing the filling, the blockage or sealing of the connection port of the propellant supply tank (121) may be released during the step (24) of performing the filling.

[0158] In the step (24) of performing the filling, pressure can be applied to the propellant supply module (12) using a pressure regulator (112) to continuously inject the required amount of propellant into the diaphragm tank (151) at a constant flow rate, and additionally, if fine control of the propellant flow rate is required on the filling line (132), the filling speed can be controlled through the propellant control valve (1321).

[0159] The step (25) of removing residual propellant is a step of ensuring safety by removing residual liquid propellant and residual steam that may remain in the piping and connections inside the fluid operation module (13), including the filling line (132), after filling is completed.

[0160] For example, the step (25) of removing residual propellant may include a step (251) of recovering residual propellant, a step (252) of inhaling liquid residual propellant, and a step (253) of removing residual vapor.

[0161] As illustrated in FIGS. 6 and 7, if the port ends of the vacuum recovery vessel (141) and separator (142) are blocked or sealed prior to the step (25) of removing residual propellant, the blocking or sealing of the connection ports of the vacuum recovery vessel (141) and separator (142) may be released during the step (25) of removing residual propellant.

[0162] The step of recovering residual propellant (251) is a step of recovering the liquid propellant remaining in the filling line (132) after the filling of the satellite body is completed, into the propellant supply tank (121) first without external discharge.

[0163] For example, in the step (251) of recovering residual propellant, after the injection of the target propellant is completed, the filling discharge valve (152, FDV) can be closed and the recovery valve (1341) can be opened. Accordingly, residual propellant inside the piping, including the filling line (132), can be diverted along the recovery line (1342) toward the inlet pipe (125) and recovered back into the propellant supply tank (121).

[0164] According to the above structure, a significant portion of the residual propellant can be recovered first into the propellant supply tank (121), thereby reducing the amount of residual propellant that needs to be processed in the subsequent vacuum-based removal step.

[0165] The step (252) of sucking in the liquid residual propellant is a step of sucking in the liquid propellant remaining in the internal piping of the operation module (13), including the filling line (132), after the recovery step (251) through the vacuum recovery container (141).

[0166] For example, in the step (252) of sucking in the liquid residual propellant, the liquid residual propellant remaining in the filling line (132) can be guided to the vacuum recovery container (141) through the first suction line (1411) so that the liquid residual propellant can be collected first.

[0167] The step of removing residual vapor (253) is to use a vacuum to suck up the liquid propellant and residual vapor remaining in the filling line (132) through the separator (142) and to separate the liquid and gas from the incoming fluid.

[0168] The step (253) of removing residual steam can ensure safety by finally removing trace amounts of propellant droplets and steam that may remain inside the piping system, including the filling line (132), even after the step (252) of inhaling residual liquid propellant.

[0169] For example, in the step (253) of removing residual vapor, the vacuum of the vacuum module (16) can be used to guide the trace amount of propellant droplets and vapor remaining in the filling line (132) to flow into the separator (142) through the second suction line (1421), and the fluid flowing into the separator (142) is separated into liquid and gas, so that the separated gaseous components (such as residual vapor) can be guided to the decontamination unit (143) for decontamination or safe treatment.

[0170] The step (26) of performing final pressurization and separation is to stably pressurize the satellite tank to the final operating pressure condition after filling and residual removal are completed to confirm the ready state for operation, and then close the satellite-side valve and disconnect the connection between the propellant filling system (1) and the satellite system to separate them.

[0171] For example, in the step (26) of performing final pressurization and separation, an initial pressure can be formed through the pressure regulator (112) of the pressurization module (11) and the first and second pressure gauges (113, 114) at the same level as the system pressure confirmed by the panel pressure gauge (137) after filling.

[0172] Afterwards, the pressure control valve (1311) is opened in a limited manner to gradually eliminate the differential pressure that may exist between module areas, and then the target (source) pressure level is set macroscopically through the pressure regulator (112), and the pressure of the diaphragm tank (151) can be raised to the final operating pressure while finely controlling the pressurization speed through the pressure control valve (1311).

[0173] When pressurization is complete, the filling vent valve (FVV, 153) is closed, and finally, the connection between the satellite propulsion system tank section (15) and the propellant filling system (1) is released and disconnected to end the operation.

[0174] According to a propellant filling system and method according to one embodiment, pressurized gas can be selectively and simultaneously applied to the gas side and the propellant side during an MEOP leak test by means of a cross-interlocking unit provided in an operating module, thereby enabling efficient leak verification of the integrated system. Furthermore, after the MEOP leak test, the pressurized line and the filling line can be triple-isolated by detaching the interlocking pipe and closing the isolation valves on both sides, thereby ensuring the independence of the gas flow path and the propellant flow path during the filling operation and reducing the risk of safety accidents caused by contamination and abnormal communication.

[0175] According to the propellant filling system and method of one embodiment, after filling is completed, residual liquid in the piping can be preferentially pushed back toward the propellant supply tank for recovery through the recovery of the propellant, thereby reducing the amount of residual propellant without external discharge, thereby reducing the burden of subsequent decontamination and gradually reducing the risk of exposure due to residual propellant.

[0176] According to the propellant filling system and method of one embodiment, residual liquid phase and residual vapor can be removed stepwise using a vacuum recovery vessel and a separator during the residual propellant removal step, thereby improving safety in handling propellants with high vapor toxicity such as hydrazine and preventing the risk of equipment contamination and diffusion into the workspace.

[0177] Although embodiments have been described with reference to limited drawings as described above, those skilled in the art can make various modifications and variations from the description above. For example, appropriate results can be achieved even if the described techniques are performed in a different order than described, and / or components such as the described structure or device are combined or assembled in a form different from described, or replaced or substituted by other components or equivalents.

Claims

Claim 1 A propellant filling system for filling a diaphragm tank of a satellite comprises: a pressurizing module having a high-pressure gas source that stores high-pressure gas and provides gas to be supplied to the diaphragm tank, a gas supply pipe connected from the high-pressure gas source to an operation module to supply gas to the operation module, and a pressure regulator installed in the gas supply pipe to regulate the pressure of the gas supplied through the gas supply pipe; a propellant supply module that stores propellant and provides propellant to be supplied to the diaphragm tank; and an operation module connected to the pressurizing module and the propellant supply module to supply pressurized gas and propellant to the diaphragm tank; wherein the propellant supply module comprises: a propellant supply tank that stores liquid propellant; and a propellant supply pipe connected from the propellant supply tank to the operation module to supply propellant to the operation module. and an inlet pipe branched from and connected to the gas supply pipe of the pressurization module and for receiving pressurized gas to supply propellant; wherein the operation module comprises: a pressurization line having a pressurization control valve capable of controlling the flow rate of the gas supplied to the diaphragm tank and supplying pressurized gas flowing in from the gas supply pipe to the gas-side port of the diaphragm tank; and a filling line having a propellant control valve capable of controlling the flow rate of the propellant supplied to the diaphragm tank and supplying propellant flowing in from the propellant supply pipe to the propellant-side port of the diaphragm tank. and a cross-interlocking unit that selectively connects a portion of the pressurizing line located downstream of the pressurizing control valve and a portion of the filling line located downstream of the propellant control valve to apply pressurized gas supplied through the pressurizing line to the gas-side port and the propellant-side port of the diaphragm tank; wherein the cross-interlocking unit comprises an interlocking pipe detachably installed between the pressurizing line and the filling line;A propellant filling system comprising: a first isolation valve installed at the portion where the pressurizing line is connected to the interlocking pipe to selectively block the flow path; and a second isolation valve installed at the portion where the filling line is connected to the interlocking pipe to selectively block the flow path; wherein, during the process of filling the propellant into the diaphragm tank, the first isolation valve and the second isolation valve are closed and the interlocking pipe is maintained in a detached state. Claim 2 delete Claim 3 delete Claim 4 delete Claim 5 delete Claim 6 delete Claim 7 A propellant filling system for filling a diaphragm tank of a satellite comprises: a pressurizing module having a high-pressure gas source that stores high-pressure gas and provides gas to be supplied to the diaphragm tank, a gas supply pipe connected from the high-pressure gas source to an operation module to supply gas to the operation module, and a pressure regulator installed in the gas supply pipe to regulate the pressure of the gas supplied through the gas supply pipe; a propellant supply module that stores propellant and provides propellant to be supplied to the diaphragm tank; and an operation module connected to the pressurizing module and the propellant supply module to supply pressurized gas and propellant to the diaphragm tank; wherein the propellant supply module comprises: a propellant supply tank that stores liquid propellant; and a propellant supply pipe connected from the propellant supply tank to the operation module to supply propellant to the operation module. and an inlet pipe branched from and connected to the gas supply pipe of the pressurization module and for receiving pressurized gas to supply propellant; wherein the operation module comprises: a pressurization line having a pressurization control valve capable of controlling the flow rate of gas supplied to the diaphragm tank and supplying pressurized gas flowing in from the gas supply pipe to the gas-side port of the diaphragm tank; a filling line having a propellant control valve capable of controlling the flow rate of propellant supplied to the diaphragm tank and supplying propellant flowing in from the propellant supply pipe to the propellant-side port of the diaphragm tank; and a propellant recovery unit connected to a point adjacent to the end of the filling line connected to the diaphragm tank in the section of the filling line, for pushing back residual propellant remaining in the filling line toward the propellant supply tank; wherein the propellant recovery unit comprises a recovery line branched from the filling line and connected to the inlet pipe of the propellant supply module;A propellant filling system comprising: a recovery valve installed in the recovery line and capable of selectively opening and closing a flow path communicating with the filling line. Claim 8 A propellant filling system according to claim 7, wherein the end of the recovery line branched from and extended from the filling line is joined at the point where the inlet pipe branches from the gas supply pipe. Claim 9 delete Claim 10 A propellant filling system for filling a diaphragm tank of a satellite comprises: a pressurizing module having a high-pressure gas source that stores high-pressure gas and provides gas to be supplied to the diaphragm tank, a gas supply pipe connected from the high-pressure gas source to an operation module to supply gas to the operation module, and a pressure regulator installed in the gas supply pipe to regulate the pressure of the gas supplied through the gas supply pipe; a propellant supply module that stores propellant and provides propellant to be supplied to the diaphragm tank; and an operation module connected to the pressurizing module and the propellant supply module to supply pressurized gas and propellant to the diaphragm tank; wherein the propellant supply module comprises: a propellant supply tank that stores liquid propellant; and a propellant supply pipe connected from the propellant supply tank to the operation module to supply propellant to the operation module. and an inlet pipe branched from and connected to the gas supply pipe of the pressurization module and for receiving pressurized gas for supplying propellant; wherein the operation module comprises: a pressurization line having a pressurization control valve capable of controlling the flow rate of gas supplied to the diaphragm tank and supplying pressurized gas flowing in from the gas supply pipe to the gas-side port of the diaphragm tank; and a filling line having a propellant control valve capable of controlling the flow rate of propellant supplied to the diaphragm tank and supplying propellant flowing in from the propellant supply pipe to the propellant-side port of the diaphragm tank; and wherein the propellant filling system comprises: a vacuum module having a vacuum pump for forming a vacuum and a vacuum line connected from the vacuum pump to the filling line; and a residual propellant removal module connected to the filling line and for removing propellant remaining in the filling line through a vacuum applied from the vacuum pump after the propellant filling of the diaphragm tank is completed.A propellant filling system further comprising, wherein each of the pressurizing module and the operating module has a movable panel-type configuration in which an internal flow path, a flow path switching configuration, and a flow rate control configuration are integrated, and is configured to be interconnected and used after being transported to a place where propellant filling operations are performed.; Claim 11 A propellant filling system for filling a diaphragm tank of a satellite comprises: a pressurizing module having a high-pressure gas source that stores high-pressure gas and provides gas to be supplied to the diaphragm tank, a gas supply pipe connected from the high-pressure gas source to an operation module to supply gas to the operation module, and a pressure regulator installed in the gas supply pipe to regulate the pressure of the gas supplied through the gas supply pipe; a propellant supply module that stores propellant and provides propellant to be supplied to the diaphragm tank; and an operation module connected to the pressurizing module and the propellant supply module to supply pressurized gas and propellant to the diaphragm tank; wherein the propellant supply module comprises: a propellant supply tank that stores liquid propellant; and a propellant supply pipe connected from the propellant supply tank to the operation module to supply propellant to the operation module. and an inlet pipe branched from and connected to the gas supply pipe of the pressurization module and for receiving pressurized gas for supplying propellant; wherein the operation module comprises: a pressurization line having a pressurization control valve capable of controlling the flow rate of gas supplied to the diaphragm tank and supplying pressurized gas flowing in from the gas supply pipe to the gas-side port of the diaphragm tank; and a filling line having a propellant control valve capable of controlling the flow rate of propellant supplied to the diaphragm tank and supplying propellant flowing in from the propellant supply pipe to the propellant-side port of the diaphragm tank; and wherein the propellant filling system comprises: a vacuum module having a vacuum pump for forming a vacuum and a vacuum line connected from the vacuum pump to the filling line; and a residual propellant removal module connected to the filling line and for removing propellant remaining in the filling line through a vacuum applied from the vacuum pump after the propellant filling of the diaphragm tank is completed.A propellant filling system further comprising, wherein the residual propellant removal module comprises: a vacuum recovery vessel that primarily sucks in liquid propellant remaining in the filling line; and a separator that secondarily sucks in liquid propellant and residual vapor remaining in the filling line and separates liquid and gas from the incoming fluid. Claim 12 A propellant filling system according to claim 11, wherein the vacuum recovery vessel comprises a first suction line connected from the filling line to suck residual liquid propellant into the vacuum recovery vessel, and the separator comprises a second suction line connected from the filling line to suck residual liquid propellant and residual vapor, and wherein, in the section of the filling line, the connection point of the first suction line is located at a point closer to the vacuum line than the connection point of the second suction line. Claim 13 A method for filling a diaphragm tank of a satellite with propellant comprises: a pressurizing module that accommodates a high-pressure gas source and provides pressurized gas; a propellant supply module that stores and provides propellant; an operation module that supplies the pressurized gas and the propellant to the diaphragm tank; a vacuum module connected to the operation module that applies a vacuum; and a residual propellant removal module that removes residual propellant from the operation module, thereby constructing a ground module system; a pressurizing line that supplies the pressurized gas and a filling line that supplies the propellant through the operation module, respectively, connected to the gas-side port and the propellant-side port of the diaphragm tank to construct a satellite interface; a step of vacuuming the interior of the system including the diaphragm tank and the filling line to a predetermined vacuum level using the vacuum module; a step of filling the diaphragm tank with propellant through the filling line; and a step of removing residual propellant remaining in the filling line. A propellant filling method comprising: a step of pressurizing the diaphragm tank to a final operating pressure and separating it; wherein the operating module further comprises a cross-linking part that selectively connects the pressurizing line and the filling line; and the step of establishing the satellite interface comprises: a step of supplying pressurizing gas from the pressurizing module to pressurize the system of the diaphragm tank and ground modules to a pressure corresponding to the maximum operating pressure, and performing an MEOP leak test to determine whether there is a leak based on the amount of pressure change at the pressure state corresponding to the maximum operating pressure; and wherein the step of performing the MEOP leak test is characterized in that the pressurizing gas supplied through the pressurizing line is simultaneously supplied to the gas-side port and the propellant-side port of the diaphragm tank while the cross-linking part is installed. Claim 14 A propellant filling method according to claim 13, wherein the step of constructing the ground module system comprises: a step of performing a leak test by supplying pressurized gas from the pressurizing module to pressurize to a predetermined pressure, and verifying the soundness of the ground module system by vacuuming to a predetermined vacuum degree using the vacuum module and then performing a vacuum leak test based on the change in vacuum degree. Claim 15 delete Claim 16 In claim 13, the cross-interlocking section comprises an interlocking pipe that is detachably installed to connect the pressurizing line and the filling line, and a first isolation valve and a second isolation valve installed at each end of the interlocking pipe, and the step of establishing the satellite interface further comprises the step of isolating the pressurizing line and the filling line by detaching the interlocking pipe constituting the cross-interlocking section and closing the first isolation valve and the second isolation valve after the step of performing the MEOP leakage test. Claim 17 A method for filling a diaphragm tank of a satellite with propellant comprises: a pressurizing module that accommodates a high-pressure gas source and provides pressurized gas; a propellant supply module that stores and provides propellant; an operation module that supplies the pressurized gas and the propellant to the diaphragm tank; a vacuum module connected to the operation module that applies a vacuum; and a residual propellant removal module that removes residual propellant from the operation module, thereby constructing a ground module system; a pressurizing line that supplies the pressurized gas and a filling line that supplies the propellant through the operation module, respectively, connected to the gas-side port and the propellant-side port of the diaphragm tank to construct a satellite interface; a step of vacuuming the interior of the system including the diaphragm tank and the filling line to a predetermined vacuum level using the vacuum module; a step of filling the diaphragm tank with propellant through the filling line; and a step of removing residual propellant remaining in the filling line. A propellant filling method comprising: a step of pressurizing the diaphragm tank to a final operating pressure and separating it; and a step of removing the residual propellant comprising: a step of recovering the residual propellant by pushing the propellant remaining in the filling line back to the propellant supply module using pressurized gas supplied from the pressurizing module while opening a recovery valve installed in a recovery line that branches off from a point adjacent to the diaphragm tank of the filling line and is connected to the propellant supply module. Claim 18 In claim 17, the step of removing the residual propellant further comprises: a step of removing the residual liquid propellant through a vacuum recovery vessel that primarily sucks in the residual liquid propellant remaining in the filling line using a vacuum applied by the vacuum module; and a step of removing the residual vapor remaining in the filling line through a separator that sucks in the residual liquid propellant and residual vapor remaining in the filling line using the vacuum and separates the liquid and gas from the incoming fluid.

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