A method and system for pressure control of a rocket fuel tank

Abstract

This invention provides a method and system for controlling the pressure of a rocket fuel tank. The method includes: controlling a first check valve and a second check valve of an integrated valve body to be fully open for a first preset time period according to a pressurization command, such that the outlet pressure of the second check valve is less than or equal to the target pressure of the rocket fuel tank; acquiring the real-time outlet pressure of the second check valve; outputting a first control command when the real-time outlet pressure is within a first threshold range; outputting a second control command when the real-time outlet pressure is within a second threshold range; controlling the valve opening of the first check valve to a first opening value and the valve opening of the second check valve to a second opening value according to the first control command; and controlling the valve opening of the first check valve to a third opening value and the valve opening of the second check valve to a fourth opening value according to the second control command. This invention improves the pressurization stability and reliability of the rocket fuel tank.

Description

Technical Field

[0001] This invention relates to the field of rocket tank pressure control technology, and in particular to a method and system for controlling rocket fuel tank pressure. Background Technology

[0002] Before launch, the propellant tank cushions need to be pressurized by a ground-based gas source to maintain a predetermined pressure, ensuring a stable propellant supply and preventing tank instability and deformation. The pressurized gas must be filtered, prevented from backflow, and dissipated before entering the tank, placing extremely high demands on the system's sealing, pressure stability, and reliability.

[0003] Existing ground booster systems use two independent check valves connected in series to achieve dual backflow prevention. The filter and check valve are separate components, connected by multiple pipeline sections and flanges / joints. This results in complex installation of check valves in the ground booster pipeline, numerous sealing points, high leakage risk, and valve response lag in downstream valves due to the dispersed arrangement of check valves. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to provide a method and system for controlling the pressure of rocket fuel tanks, so as to solve the problems of complex installation of one-way valves in ground pressurization pipelines, numerous sealing points, high risk of leakage, and lag in the response of the downstream valves caused by the dispersed installation of one-way valves.

[0005] To solve the above-mentioned technical problems, the technical solution of the present invention is as follows: In a first aspect, embodiments of the present invention provide a method for controlling the pressure of a rocket fuel tank. The air inlet of the rocket fuel tank is connected to an integrated valve body, which includes: a filter element connected to a ground pressurization pipeline of the rocket's first-stage fuel tank; a first one-way valve connected to the filter element; and a second one-way valve connected to the first one-way valve. The outlet of the second one-way valve is connected to the air inlet of the rocket fuel tank. The method includes: According to the pressurization command, the first and second check valves of the integrated valve body are fully open for a first preset time period, so that the outlet pressure of the second check valve is less than or equal to the target pressure of the rocket fuel tank. Obtain the real-time outlet pressure of the second check valve in the integrated valve body; When the real-time outlet pressure is within a first threshold range, a first control command is output; the first threshold range is determined based on the target pressure of the rocket fuel tank. When the real-time outlet pressure is within the second threshold range, a second control command is output; the maximum value of the first threshold range is equal to the minimum value of the second threshold range; the second threshold range is determined based on the target pressure of the rocket fuel tank. According to the first control command, the valve opening of the first one-way valve is controlled to a first opening value and the valve opening of the second one-way valve is controlled to a second opening value; so that the ground pressurization pipeline of the rocket's first-stage fuel tank supplies gas to the rocket fuel tank through the filter element, the first one-way valve and the second one-way valve at a first pressure. According to the second control command, the valve opening of the first one-way valve is controlled to the third opening value and the valve opening of the second one-way valve is controlled to the fourth opening value, so that the ground pressurization pipeline of the rocket's first-stage fuel tank supplies gas to the rocket fuel tank through the filter element, the first one-way valve and the second one-way valve according to the second pressure.

[0006] Optionally, the rocket fuel tank pressure control method also includes: When the real-time outlet pressure is within the third threshold range, a third control command is output; the minimum value of the third threshold range is greater than the maximum value of the second threshold range; the second threshold range is determined based on the target pressure of the rocket fuel tank. According to the third control command, the valve opening of the first one-way valve is controlled to be reduced to the fifth opening value within a second preset time period, and the valve opening of the second one-way valve is controlled to be reduced to the sixth opening value within a second preset time period, so that the ground pressurization pipeline of the rocket's first-stage fuel tank supplies gas to the rocket fuel tank through the filter element, the first one-way valve, and the second one-way valve according to the third pressure.

[0007] Optionally, the rocket fuel tank pressure control method also includes: Obtain the real-time inlet pressure of the integrated valve body; Based on the real-time inlet pressure, the real-time outlet pressure, and the pressure difference between the real-time inlet pressure and the real-time outlet pressure, a fourth control command is output. According to the fourth control command, the first check valve and the second check valve are controlled to close.

[0008] Optionally, controlling the valve opening of the first check valve to a first opening value and controlling the valve opening of the second check valve to a second opening value according to the first control command includes: The first opening value is determined based on the deviation between the real-time outlet pressure and the target pressure; The second opening value is determined based on the first opening value, the outlet pressure, and the target pressure; According to the first control command, the valve opening of the first check valve is controlled to a first opening value, and the valve opening of the second check valve is controlled to a second opening value.

[0009] Optionally, determining the second opening value based on the first opening value, the outlet pressure, and the target pressure includes: The dynamic correction amount is determined based on the first opening value, the outlet pressure, and the target pressure. The second opening value is determined based on the first opening value and the dynamic correction amount.

[0010] Optionally, controlling the valve opening of the first check valve to a third opening value and controlling the valve opening of the second check valve to a fourth opening value according to the second control command includes: The adjustment step size is determined based on the real-time pressure deviation between the real-time outlet pressure and the target pressure. The real-time compensation amount for valve pressure drift is determined based on the flow resistance data, average temperature data, and gas leakage data over a preset time period. The third opening value is determined based on the real-time compensation amount for valve pressure drift, the current opening degree of the first check valve, and the adjustment step size. The fourth opening value is determined based on the third opening value, the dual-valve cooperative coupling coefficient, and the real-time compensation amount for valve pressure drift. According to the second control command, the valve opening of the first check valve is controlled to the third opening value and the valve opening of the second check valve is controlled to the fourth opening value.

[0011] Optionally, according to Determine the adjustment step size; where, Indicates the adjustment step size. This indicates the preset base step size. Represents a symbolic function. This indicates the real-time pressure deviation value. This indicates the target pressure of the storage tank.

[0012] Optionally, according to Determine the dual-valve cooperative coupling coefficient, where, This represents the coupling coefficient of the two valves. Indicates the third opening value; This indicates real-time export pressure; This indicates the maximum pressure that the integrated valve body can withstand.

[0013] Secondly, embodiments of the present invention also provide a rocket fuel tank pressure control system, comprising: An integrated valve body connected to the air inlet of a rocket fuel tank, the integrated valve body comprising: a filter element connected to the ground pressurization pipeline of the rocket's first-stage fuel tank, a first check valve connected to the filter element, and a second check valve connected to the first check valve, the outlet of the second check valve being connected to the air inlet of the rocket fuel tank; and a controller connected to the filter element, the first check valve, and the second check valve respectively. The filter element, the first one-way valve, and the second one-way valve are fixedly connected through the housing; The controller: according to the pressurization command, controls the first and second check valves of the integrated valve body to be fully open for a first preset time period, so that the outlet pressure of the second check valve is less than or equal to the target pressure of the rocket fuel tank. Obtain the real-time outlet pressure of the second check valve; When the real-time outlet pressure is within a first threshold range, a first control command is output; the first threshold range is determined based on the target pressure of the rocket fuel tank. When the real-time outlet pressure is within the second threshold range, a second control command is output; the maximum value of the first threshold range is equal to the minimum value of the second threshold range; the second threshold range is determined based on the target pressure of the rocket fuel tank. According to the first control command, the valve opening of the first one-way valve is controlled to a first opening value and the valve opening of the second one-way valve is controlled to a second opening value; so that the ground pressurization pipeline of the rocket's first-stage fuel tank supplies gas to the rocket fuel tank through the filter element, the first one-way valve and the second one-way valve at a first pressure. According to the second control command, the valve opening of the first one-way valve is controlled to the third opening value and the valve opening of the second one-way valve is controlled to the fourth opening value, so that the ground pressurization pipeline of the rocket's first-stage fuel tank supplies gas to the rocket fuel tank through the filter element, the first one-way valve and the second one-way valve according to the second pressure.

[0014] The above-described solution of the present invention has at least the following beneficial effects: The above-described solution of the present invention, through an integrated valve body connected to the air inlet of the fuel tank, and according to a pressurization command, controls the first and second check valves of the integrated valve body to be fully open for a first preset time period, so that the outlet pressure of the second check valve is less than or equal to the target pressure of the rocket fuel tank; obtains the real-time outlet pressure of the second check valve; when the real-time outlet pressure is within a first threshold range, outputs a first control command; when the real-time outlet pressure is within a second threshold range, outputs a second control command; controls the valve opening of the first check valve to a first opening value and the valve opening of the second check valve to a second opening value according to the first control command; controls the valve opening of the first check valve to a third opening value and the valve opening of the second check valve to a fourth opening value according to the second control command. This reduces pressure fluctuations in the fuel tank, improves the stability and reliability of fuel tank pressurization, and, since the first check valve, the second check valve, and the filter element are integrated into a single valve body, reduces the number of joints and leakage points in the ground pressurization device, is compatible with existing energy dissipator interfaces, and allows the valves of the front and rear check valves to flexibly cooperate with each other, shortening the rocket launch preparation time and improving rocket launch and maintenance efficiency. Attached Figure Description

[0015] Figure 1 This is a flowchart of an embodiment of the rocket fuel tank pressure control method of the present invention; Figure 2 This is a schematic diagram of another embodiment of the rocket fuel tank pressure control method of the present invention; Figure 3 This is a schematic diagram of an embodiment of the integrated valve body in the rocket fuel tank pressure control system of the present invention.

[0016] Explanation of reference numerals in the attached figures: 1: Valve core; 2: Housing; 3: Damping; 4: Sealing gasket; 5: Filter element; 6: First check valve; 7: Second check valve; 8: Energy dissipator; 9: Ground pressurization pipeline of rocket first stage fuel tank; 10: Integrated valve body. Detailed Implementation

[0017] Exemplary embodiments of the invention will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the invention are shown in the drawings, it should be understood that the invention may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this invention will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.

[0018] like Figure 1 As shown, an embodiment of the present invention proposes a method for controlling the pressure of a rocket fuel tank. An integrated valve body 10 is connected to the air inlet of the rocket fuel tank. The integrated valve body 10 includes: a filter element 5 connected to a ground pressurization pipeline 9 of the rocket's first-stage fuel tank; a first one-way valve 6 connected to the filter element 5; and a second one-way valve 7 connected to the first one-way valve 6. The outlet of the second one-way valve 7 is connected to the air inlet of the rocket fuel tank. The method includes: Step 101: According to the pressurization command, control the first check valve 6 and the second check valve 7 of the integrated valve body 10 to be fully open for a first preset time period, so that the outlet pressure of the second check valve 7 is less than or equal to the target pressure of the rocket fuel tank. Step 102: Obtain the real-time outlet pressure of the second check valve 7; Step 103: When the real-time outlet pressure is within a first threshold range, a first control command is output; the first threshold range is determined based on the target pressure of the rocket fuel tank. Step 104: When the real-time outlet pressure is within the second threshold range, a second control command is output; the maximum value of the first threshold range is equal to the minimum value of the second threshold range; the second threshold range is determined based on the target pressure of the rocket fuel tank. Step 105: According to the first control command, control the valve opening of the first one-way valve 6 to the first opening value and control the valve opening of the second one-way valve 7 to the second opening value, so that the ground pressurization pipeline 9 of the rocket's first-stage fuel tank supplies gas to the rocket fuel tank through the filter element 5, the first one-way valve 6 and the second one-way valve 7 at the first pressure. Step 106: According to the second control command, control the valve opening of the first one-way valve 6 to the third opening value and control the valve opening of the second one-way valve 7 to the fourth opening value, so that the ground pressurization pipeline 9 of the rocket's first-stage fuel tank supplies gas to the rocket fuel tank through the filter element 5, the first one-way valve 6 and the second one-way valve 7 according to the second pressure.

[0019] In this embodiment, before the liquid rocket launch, the propellant tank's air cushion needs to be pressurized by a ground-based air source to maintain a predetermined pressure, ensuring a stable propellant supply and preventing tank instability and deformation. (Reference) Figure 2 The integrated valve body 10 is located at the air inlet of the rocket propellant tank and is used to control the gas entering the tank. The target pressure of the propellant tank is the gas pressure that the tank is expected to reach. The inlet of the integrated valve body 10 is connected to the gas supply device, and the outlet of the integrated valve body 10 is connected to the propellant tank. The integrated valve body 10 is a valve body formed by welding the housing 2 of the filter element 5, the first one-way valve 6, and the second one-way valve 7 together.

[0020] For step 101, according to the pressurization command, the first check valve 6 and the second check valve 7 of the integrated valve body 10 are controlled to be fully open for a first preset time period. ,in, This ensures that the outlet pressure of the second check valve 7 is less than or equal to the target pressure of the rocket fuel tank, even if This process is the rapid pressurization phase, in which... This indicates the outlet pressure of the second check valve 7. This indicates the target pressure of the rocket fuel tank. Indicates the maximum permissible time for rapid boost. This represents the first preset coefficient.

[0021] When the boost time is greater than or equal to the preset maximum boost time, the rapid boost phase is forcibly exited, current is limited and voltage is stabilized, and a fault is reported.

[0022] Among them, the first preset coefficient according to ,in, The time (in seconds) for pressurization operation is indicated by the timer starting from the fully open state of the first check valve 6 and the second check valve 7 of the control integrated valve body 10, and continuously increasing as the pressurization process progresses. Indicates the maximum permissible time for rapid boost. Indicates the gas flow rate during the rapid pressurization phase. The real-time detection value when both valves are fully open fluctuates slightly with the gas supply pressure. Indicates the maximum permissible gas flow rate during the rapid pressurization phase. The preset fixed value is determined by the gas supply system design parameters to prevent excessive flow rate from damaging the valve body. The core is to dynamically reflect the progress of the rapid boost phase: the closer the boost time t is to... Rapidly pressurized flow rate The closer , The closer the value is to 0.96, the closer the rapid boost phase is to its end; when... The rapid boost phase has officially begun. The range of values ​​is Preferred, .

[0023] For step 102, the real-time outlet pressure of the second check valve 7 is the real-time pressure of the fuel tank.

[0024] For step 103, the first threshold range is: ,in, Indicates real-time export pressure. Indicates target pressure. Indicates the maximum permissible time for rapid boost. This represents the first preset coefficient. This indicates the second preset coefficient. This stage transitions from the rapid pressurization stage to the precise pressure stabilization stage, where the pressure smoothly approaches the target pressure, suppressing overshoot, reducing impact, and minimizing pressure fluctuations.

[0025] Among them, the second preset coefficient is based on It is confirmed that, among them, This indicates the current tank pressure (MPa), meaning the real-time outlet pressure at the outlet of integrated valve body 10 is equivalent to the tank air cushion pressure, and is updated in real time. Indicates target pressure. Indicates the current gas flow rate Real-time monitoring, dynamically changing with the boost phase (rapid boost phase approaches...) (The voltage gradually decreases during the precise voltage stabilization phase). Indicates the maximum permissible gas flow rate during the rapid pressurization phase. The preset fixed value is determined by the gas supply system design parameters to prevent excessive flow rate from damaging the valve body. Indicates the maximum permissible time for rapid boost. It represents the boost operation time (s), which is timed in real time from the start of the rapid boost phase and continues to increase as the boost process progresses. Dynamically reflects the current pressurization status: current tank pressure The closer The lower the current flow velocity v, the closer the pressurization time t is to... , The closer the value is to 1.0, the better; conversely, the closer the value is to 1.0, the better The value approaches 0.93. The range of values ​​is This ensures a clear distinction between the precise voltage stabilization and voltage maintenance phases, with no overlapping intervals. Preferably, .

[0026] In this embodiment, the first stage of injecting gas into the rocket's propellant tank before launch is the rapid pressurization stage. The first one-way valve 6 and the second one-way valve 7 are immediately and fully opened to allow gas to quickly enter the tank, saving time. During this period, data such as the inlet and outlet pressures of the integrated valve body 10 are monitored in real time to quickly switch to the next stage, the precise pressure stabilization stage.

[0027] For step 104, the range of the second threshold is: ,in, This indicates export pressure. Indicates target pressure. This indicates the second preset coefficient. This stage transitions from the precise pressure stabilization stage to the pressure maintenance stage, where pressure deviations caused by temperature drift, leakage, and inlet fluctuations are offset in real time.

[0028] In an optional embodiment of the present invention, step 105 involves controlling the valve opening of the first one-way valve 6 to a first opening value and controlling the valve opening of the second one-way valve 7 to a second opening value according to the first control command, so that the ground pressurization pipeline 9 of the rocket's first-stage fuel tank supplies gas to the rocket fuel tank through the filter element 5, the first one-way valve 6, and the second one-way valve 7 at a first pressure, including: Step 1051: Determine the first opening value based on the deviation between the real-time outlet pressure and the target pressure; Step 1052: Determine the second opening value based on the first opening value, the outlet pressure, and the target pressure; Step 1053: According to the first control command, control the valve opening of the first one-way valve 6 to the first opening value and control the valve opening of the second one-way valve 7 to the second opening value, so that the ground pressurization pipeline 9 of the rocket's first-stage fuel tank supplies gas to the rocket fuel tank through the filter element 5, the first one-way valve 6 and the second one-way valve 7 at the first pressure.

[0029] In this embodiment, in step 1051, according to Determine the first opening value of the valve after adjustment by the first check valve 6; in, ,in, This indicates the first opening value of the valve after adjustment by the first check valve 6; This indicates the maximum opening degree of the first check valve 6. A preset fixed value is used to prevent excessive gas flow caused by excessive opening, which could lead to pressure overshoot. This value is typically set to... (below the rapid boost stage) Fully open, demonstrating precise voltage regulation and current limiting characteristics; This indicates the minimum opening degree of the first check valve 6. A preset fixed value is used to prevent insufficient gas flow caused by an excessively small opening, which would prevent the pressure from remaining stable and approaching the target value. This value is typically set to... ; Indicates the initial opening degree of the first one-way valve 6 The initial valve position when entering the precise pressure stabilization stage directly inherits the opening degree at the end of the rapid pressure boosting stage (during the rapid pressure boosting stage, both valves are fully open, so the initial opening degree is usually close to the opening degree of the valve at the end of the rapid pressure boosting stage). ); This indicates the proportional adjustment coefficient of the first one-way valve 6. A preset fixed value is determined by the structural and flow characteristics of the first check valve 6, for example, taking... That is, for every 1 MPa pressure deviation, the opening is adjusted accordingly. ; This indicates the deviation between export pressure and target pressure.

[0030] In an optional embodiment of the present invention, step 1052, determining the second opening value based on the first opening value, the outlet pressure, and the target pressure, includes: Step 10521: Determine the dynamic correction amount based on the first opening value, the outlet pressure, and the target pressure; Step 10522: Determine the second opening value based on the first opening value and the dynamic correction amount.

[0031] In this embodiment, according to Determine the dynamic correction amount, where, Indicates dynamic correction amount It is used to fine-tune the opening of the second check valve 7 to achieve coordinated matching of the two valves. This represents the correction coefficient (dimensionless) for the second check valve 7, a preset fixed value determined by the dual-valve synergy characteristics and flow matching relationship. It is used to control the adjustment range of the dynamic correction amount and is typically set to a value that is not specified in the original text. , This represents the pressure deviation (MPa), as defined in step 141. Taking the absolute value ensures that the correction amount is always positive, avoiding reverse adjustment. This represents the target pressure of the storage tank (MPa), used to standardize the correction amount, eliminate the influence of target pressure differences on the correction range, and ensure that the correction logic is consistent under different target pressures.

[0032] according to The second opening value after adjustment by the second one-way valve 7, wherein... This indicates the second opening value (%). This indicates the maximum opening degree of the second check valve 7. A fixed value is preset to prevent excessive flow caused by excessive opening, which could lead to pressure overshoot. This value is typically set to a fixed value. (Lower than the maximum opening of the first check valve 6, to achieve graded flow matching of the two valves); This indicates the minimum opening degree of the second check valve 7. A preset fixed value is used to prevent insufficient flow due to an excessively small opening, which would prevent the first check valve 6 from achieving precise pressure stabilization. This value is typically set to... (Slightly lower than the minimum opening of the first check valve 6); This indicates the first opening value after adjustment of the first one-way valve 6. This serves as the benchmark for calculating the opening degree of the second check valve 7.

[0033] In this embodiment, the valve opening of the first one-way valve 6 is controlled to a first opening value and the valve opening of the second one-way valve 7 is controlled to a second opening value according to the first control command, so that the ground pressurization pipeline 9 of the rocket's first-stage fuel tank supplies gas to the rocket fuel tank through the filter element 5, the first one-way valve 6 and the second one-way valve 7 at a first pressure. Here, the first pressure is the pressure of the gas flowing through the filter element 5, the first one-way valve 6 and the second one-way valve 7 when the first one-way valve 6 is at the first opening and the second one-way valve 7 is at the second opening.

[0034] In an optional embodiment of the present invention, step 106, controlling the valve opening of the first check valve 6 to a third opening value and controlling the valve opening of the second check valve 7 to a fourth opening value according to the second control command, includes: Step 1061: Determine the adjustment step size based on the real-time pressure deviation between the real-time outlet pressure and the target pressure; Step 1062: Determine the real-time compensation amount for valve pressure drift based on the flow resistance data, average temperature data, and gas leakage data over a preset time period. Step 1063: Determine the third opening value based on the real-time compensation amount for valve pressure drift, the current valve opening of the first check valve 6, and the adjustment step size; Step 1064: Determine the fourth opening value based on the third opening value, the dual-valve cooperative coupling coefficient, and the real-time compensation amount for valve pressure drift; Step 1065: Control the valve opening of the first check valve 6 to the third opening value and control the valve opening of the second check valve 7 to the fourth opening value according to the second control command.

[0035] In an optional embodiment of the present invention, for step 1061, according to Determine the adjustment step size; where, Indicates the adjustment step size. This indicates the preset base step size. Represents a symbolic function. This indicates the real-time pressure deviation value. This indicates the target pressure of the storage tank.

[0036] when (When the tank pressure is lower than the target pressure, the input pressure needs to be increased) , When the value is positive, the adjustment step is positive, and the valve opening increases (opening the valve wider increases the gas supply flow to achieve pressure compensation). when (When the tank pressure is higher than the target pressure, the input pressure needs to be reduced) , If the value is negative, the adjustment step is negative, the valve opening decreases (closing the valve to reduce the gas supply flow and prevent the pressure from continuing to rise), until the valve opening drops to a certain level. (Completely closed), at this point stop adjusting the valve and keep it closed without performing any pressure relief operations; when When (pressure reaches the target), Stop adjusting, maintain the current valve position, and ensure that the pressure remains stable near the target value.

[0037] In one application scenario: Target pressure of storage tank (The rocket propellant tank's standard target pressure range conforms to the context parameter specifications); preset basic step size (range of values) The intermediate value, balancing adjustment accuracy and response speed); valve opening limit: (All closed) (Full Open), as in the previous text The opening range is consistent.

[0038] Calculated (The tank pressure is too low; the valve needs to be opened wider to replenish the pressure.) Substituting into the formula, we get:

[0039] That is, ΔK is a positive value ( The valve opening is increased by 0.031%, gradually increasing the air supply flow to achieve precise pressure replenishment. The adjustment step is small, avoiding pressure overshoot and meeting the fine-tuning requirements of the pressure holding stage. The adjustment step is controlled between 0.02% and 0.04%, which is within the fine-tuning range of the pressure holding stage.

[0040] For step 1062, according to Determine the real-time compensation amount for valve pressure drift, whereby... This indicates the real-time compensation amount (MPa) for valve pressure drift. A positive value indicates that pressure compensation is required (to offset pressure drop drift), and a negative value indicates that flow reduction compensation is required (to offset pressure rise drift). There is no pressure relief operation throughout the process; compensation is achieved solely through input flow rate adjustment. This represents a temperature correction factor (dimensionless), a preset fixed value, used to correct the effect of temperature changes on pressure drift. Its value range is... The thermal characteristics of the storage tank determine the specific thermal properties. This parameter represents the average temperature data (K), which is the average temperature of the tank during a preset time period (e.g., 10s) in the pressure holding phase. It is monitored and updated in real time. An increase in temperature will cause the gas in the tank to expand and the pressure to rise, while a decrease in temperature will cause the pressure to drop. This parameter quantifies the effect of temperature on drift. Indicates flow resistance data for a preset time period The average flow resistance during the preset time period of the pressure holding stage is updated in real time. When the flow resistance increases, it will cause the gas supply flow rate to decrease and the pressure to drop, which needs to be adjusted by compensation. Indicates gas leak data The average gas leakage rate during the preset time period of the pressure holding phase is detected and obtained in real time. Leakage will cause the tank pressure to drop. This parameter is used to quantify the impact of leakage on drift and ensure accurate compensation.

[0041] Real-time compensation for valve pressure drift It achieves real-time compensation for pressure drift caused by temperature, flow resistance, and leakage, and avoids pressure deviation from the target value caused by drift.

[0042] For step 1063, The third opening value after adjustment of the first one-way valve 6 during the pressure holding phase, wherein... This indicates the third opening value after the first check valve 6 is adjusted during the pressure holding stage. ), which serves as the final valve position during the pressure-holding stage of the first one-way valve 6; This indicates the maximum opening degree of the first check valve 6 ( ), same as the definition of the precise voltage stabilization stage ( This prevents excessive opening from causing pressure overshoot; Indicates the current opening degree of the first check valve 6 ( ), from the previous adjustment cycle Inherited, updated in real time, to meet the continuous adjustment needs of the pressure holding stage; Indicates the adjustment step size ( ), used to fine-tune the opening based on the real-time pressure deviation (e(k)), with positive values ​​increasing the opening and negative values ​​decreasing the opening; This indicates the proportional adjustment coefficient of the first one-way valve 6 ( ), defined in the same way as the precise pressure stabilization stage, is used to compensate for pressure drift ( This is converted into opening compensation amount to ensure accurate compensation. This indicates the real-time compensation amount for valve pressure drift.

[0043] For step 1064, Determine the fourth opening value of the second check valve 7 after adjustment during the pressure holding phase, wherein... This indicates the fourth opening value of the second check valve 7 after adjustment during the pressure holding phase. This indicates the maximum opening degree of the second check valve 7 ( ), same as the definition of the precise voltage stabilization stage ( This ensures that the flow rates of the two valves are matched in stages to avoid overshoot; Indicates the current opening degree of the second check valve 7 ( ), from the previous adjustment cycle Inheritance, real-time updates, and adaptation to continuous adjustment needs; Indicates the adjustment step size ( Step 151 outputs the value to achieve coordinated step size adjustment of the second one-way valve 7; This represents the dual-valve cooperative coupling coefficient (dimensionless), used to control the degree of matching between the opening of the second check valve 7 and the first check valve 6; This represents the correction factor (dimensionless) for the second one-way valve 7, as defined in the precise pressure stabilization stage. ), used to convert the pressure drift compensation amount into the opening compensation amount of the second check valve 7; This indicates the real-time compensation amount for valve pressure drift.

[0044] In an optional embodiment of the present invention, for step 1064, according to Determine the dual-valve cooperative coupling coefficient, where, This represents the coupling coefficient of the two valves. This indicates the third opening value after the first check valve 6 is adjusted during the pressure holding stage. ); This indicates the current tank pressure (MPa), which is the real-time outlet pressure of the integrated valve body 10, used to quantify the impact of the current pressure state on the dual-valve coordination. This indicates the maximum pressure (MPa) that the integrated valve body 10 can withstand; it is a fixed parameter.

[0045] According to the second control command, the valve opening of the first one-way valve 6 is controlled to the third opening value and the valve opening of the second one-way valve 7 is controlled to the fourth opening value, so that the ground pressurization pipeline 9 of the rocket's first-stage fuel tank supplies gas to the rocket fuel tank through the filter element 5, the first one-way valve 6 and the second one-way valve 7 at the second pressure. Here, the second pressure is the pressure of the gas flowing through the filter element 5, the first one-way valve 6 and the second one-way valve 7 when the first one-way valve 6 is at the third opening value and the second one-way valve 7 is at the fourth opening value.

[0046] In an optional embodiment of the present invention, the rocket fuel tank pressure control method may further include: Step 107: When the real-time outlet pressure is within the third threshold range, a third control command is output; the minimum value of the third threshold range is greater than the maximum value of the second threshold range; the second threshold range is determined based on the target pressure of the rocket fuel tank. Step 108: According to the third control command, control the valve opening of the first one-way valve 6 to close to the fifth opening value within the second preset time period, and control the valve opening of the second one-way valve 7 to close to the sixth opening value within the second preset time period, so that the ground pressurization pipeline 9 of the rocket's first-stage fuel tank supplies gas to the rocket fuel tank through the filter element 5, the first one-way valve 6 and the second one-way valve 7 according to the third pressure.

[0047] In this embodiment, the range of the third threshold is: At this point, the pressure control phase of the rocket propellant tank has entered the fault protection phase. This indicates the outlet pressure (approximately equal to the current tank pressure). Indicates target pressure. Indicates inlet pressure, This represents the third preset coefficient.

[0048] Among them, the third preset coefficient according to ,in, This represents the historical tank failure pressure threshold (MPa). It is calculated by statistically analyzing the lowest overpressure / underpressure threshold values ​​that led to damage or abnormality in historical tank failures, and taking the average value as the calculation benchmark. This indicates the tank's pressure resistance parameter (MPa), the maximum design pressure of the tank, a fixed parameter determined by the tank's structural design. Indicates the target pressure of the tank (MPa), used for standardization. The value is selected to eliminate the influence of target pressure on the fault determination threshold. The core principle is to dynamically determine the pressure threshold for fault protection by combining historical fault experience with the tank's own pressure resistance: historical fault threshold. Larger tanks have higher pressure resistance. The higher, The larger the value, the higher the fault protection threshold ( The higher the value, the better; conversely, the lower the value, the better. The smaller the value, the earlier the fault protection is triggered. The range of values ​​is always 1 This avoids damage to the storage tank due to overpressure and also prevents misdiagnosis of faults.

[0049] according to Determine the fifth opening value of the valve after adjustment by the first one-way valve 6. Among them, This represents the fifth degree value. This indicates the minimum opening degree required for fault protection of the first check valve. This indicates the current opening degree of the first check valve at the moment the fault is triggered. This represents the basic valve-closing coefficient for fault descent, dimensionless, with values ​​ranging from [value missing]. , (1- ), This represents the overpressure correction factor. This indicates the duration of the fault phase. This indicates the second preset time period for the fault protection slow-down mechanism to close. Indicates the third coefficient. Indicates the target pressure of the storage tank. This indicates the real-time outlet pressure of the integrated valve body 10.

[0050] according to Determine the sixth opening value of the valve after adjustment by the second check valve 7. Among them, This indicates the minimum opening degree for fault protection of the second check valve. This represents the fifth degree value. This represents the sixth degree value. This indicates the dynamic deviation correction amount of the dual valves under fault conditions. The greater the overpressure, the greater the reduction in the closing range of the second valve relative to the first valve. , This represents the correction factor for the second check valve. Indicates the target pressure of the storage tank. This indicates the real-time outlet pressure of the integrated valve body 10.

[0051] The valve opening of the first one-way valve 6 is controlled to be reduced to the fifth opening value within a second preset time period, and the valve opening of the second one-way valve 7 is controlled to be reduced to the sixth opening value within a second preset time period. This allows the ground pressurization pipeline 9 of the rocket's first-stage fuel tank to supply gas to the rocket fuel tank through the filter element 5, the first one-way valve 6, and the second one-way valve 7 at a third pressure. Here, the third pressure is the pressure of the gas flowing through the filter element 5, the first one-way valve 6, and the second one-way valve 7 when the first one-way valve 6 is reduced to the fifth opening value and the second one-way valve 7 is reduced to the sixth opening value.

[0052] In an optional embodiment of the present invention, the rocket fuel tank pressure control method further includes: Step 109: Obtain the real-time inlet pressure of the integrated valve body 10; Step 110: Output a fourth control command based on the real-time inlet pressure, the real-time outlet pressure, and the pressure difference between the real-time inlet pressure and the real-time outlet pressure. Step 111: According to the fourth control command, control the first one-way valve 6 and the second one-way valve 7 to close.

[0053] In this embodiment, when and A preset threshold is set, a fourth control command is output, and based on the fourth control command, the first one-way valve 6 and the second one-way valve 7 are controlled to close. This indicates the real-time inlet pressure of the integrated valve body 10. This indicates the real-time inlet pressure of the integrated valve body 10.

[0054] In some applications, when the pressure rises too quickly or too slowly, the integrated valve body 10 can automatically correct the valve position and stabilize the flow rate.

[0055] The above embodiments of the present invention rely on the pressure monitoring interface reserved in the integrated valve body 10 to collect the inlet and outlet pressure signals of the integrated valve body 10 in real time. Using the target pressure of the tank air cushion as the control benchmark, a segmented closed-loop regulation logic is adopted. When the outlet pressure is lower than 90% of the target pressure, the algorithm controls the double check valves to fully open, achieving rapid pressurization with a large flow rate. When the outlet pressure is in the range of 90% to 98% of the target pressure, the double check valves are driven to cooperate with a small opening for throttling, approximating the target pressure with a stable flow rate and suppressing pressure overshoot and shock. When the outlet pressure of the integrated valve body 10 reaches above 98% of the target pressure, it enters a fine-tuning pressure-maintaining mode to maintain stable air cushion pressure. Simultaneously, the present invention has real-time fault protection logic. When a reverse pressure difference, abnormal pressure overshoot, or sudden flow change is detected, the double check valves are immediately controlled to close rapidly, achieving dual backflow prevention and overpressure protection, further improving the stability, safety, and automation level of the pressurization process.

[0056] like Figure 2 As shown, an embodiment of the present invention also provides a rocket fuel tank pressure control system, comprising: an integrated valve body 10 connected to the air inlet of the rocket fuel tank. Figure 3 An example of an integrated valve body structure diagram is provided. The integrated valve body 10 includes: a filter element 5 connected to the ground pressurization pipeline 9 of the rocket's first stage fuel tank, a first one-way valve 6 connected to the filter element 5, and a second one-way valve 7 connected to the first one-way valve 6. The outlet of the second one-way valve 7 is connected to the air inlet of the rocket fuel tank. A controller connected to the filter element 5, the first check valve 6, and the second check valve 7; The filter element 5, the first one-way valve 6, and the second one-way valve 7 are fixedly connected by the housing 2. The controller is used to control the first and second check valves of the integrated valve body to be fully open for a first preset time period according to the pressurization command, so that the outlet pressure of the second check valve is less than or equal to the target pressure of the rocket fuel tank; to acquire the real-time outlet pressure of the second check valve of the integrated valve body; when the real-time outlet pressure is within a first threshold range, to output a first control command; the first threshold range is determined according to the target pressure of the rocket fuel tank; when the real-time outlet pressure is within a second threshold range, to output a second control command; the maximum value of the first threshold range is equal to the minimum value of the second threshold range; the second threshold range is determined according to the target pressure of the rocket fuel tank. The target pressure of the rocket fuel tank is determined; according to the first control command, the valve opening of the first one-way valve is controlled to a first opening value and the valve opening of the second one-way valve is controlled to a second opening value; so that the ground pressurization pipeline of the rocket's first-stage fuel tank supplies gas to the rocket fuel tank at a first pressure through the filter element, the first one-way valve, and the second one-way valve; according to the second control command, the valve opening of the first one-way valve is controlled to a third opening value and the valve opening of the second one-way valve is controlled to a fourth opening value, so that the ground pressurization pipeline of the rocket's first-stage fuel tank supplies gas to the rocket fuel tank at a second pressure through the filter element, the first one-way valve, and the second one-way valve.

[0057] The filter element 5, the first one-way valve 6, and the second one-way valve 7 are coaxial and connected in the same direction.

[0058] In this embodiment, the integrated valve body 10 is a one-piece valve body, internally comprising an inlet chamber, a filter chamber, a first one-way valve chamber, a second one-way valve chamber, and an outlet chamber. The filter assembly is installed within the filter chamber on the inlet side to filter particulate impurities. The first one-way valve 6 and the second one-way valve 7 are coaxially / in the same direction connected in series within the valve body, forming a double anti-backflow system. The internal flow path of the integrated valve body 10 is integrated: gas enters from the inlet, passes sequentially through the filter element 5, the first one-way valve 6, and the second one-way valve 7, and is then transported to the storage tank from the outlet of the second one-way valve 7. The entire flow occurs within the valve body without external transfer pipelines. The outlet of the integrated valve body 10 directly connects to the inlet of the storage tank pressurization pipeline / energy dissipator 8, achieving integrated output.

[0059] When the ground gas source is turned on and the pressure detection is normal, the gas enters the integrated booster device and enters the storage tank through the integrated valve body 10. During the period of gas input to the storage tank, the opening and closing of the valve of the integrated valve body 10 is controlled by the above method to ensure stable, safe and efficient boosting.

[0060] In this embodiment, the first one-way valve 6 includes a housing 2 and a valve core 1 disposed within the housing 2. A damper 3 is provided between the valve core 1 and the housing 2, and the valve core 1 abuts against the damper 3. The housing and the valve core 1 are fixedly connected. The valve core 1 is U-shaped, and a spring is fixedly connected inside the valve core 1. The other end of the spring is located at the air inlet of the second one-way valve 7, allowing the valve core 1 to slide horizontally relative to the housing 2. The internal interfaces of the first one-way valve 6 and the second one-way valve 7 are the same. A sealing gasket 4 is disposed at the outlet of the second one-way valve 7.

[0061] The process of adjusting the opening of the first check valve 6 is as follows: When the spring is in the extended state, the valve core 1 of the first check valve 6 is in the initial state. When the controller controls the valve core 1 to move slightly in the direction of gas flow, the valve core 1 overcomes the spring pressure and the resistance of the damper 3 and moves in the direction of gas flow. At this time, the first check valve 6 opens slightly. As the valve core 1 continues to move in the direction of gas flow, the opening of the first check valve 6 increases. Similarly, the opening of the second check valve 7 can be adjusted.

[0062] In one application scenario, the opening and closing control of the integrated valve body 10 is as follows: 1. Initialization Phase The system powers on and reads the target pressure. Maximum permissible time for rapid boost

[0063] Inlet pressure Export pressure ; The dual check valves remain closed, and the self-test sensors and valve position status are monitored.

[0064] 2. Rapid boost phase Judgment conditions:

[0065] Integrated valve operation: Dual check valves maintain maximum opening; simultaneously, a real-time timer is activated, and if the required time is reached... Before entering the next stage, it is forced to exit the rapid boost phase and enter the precise voltage stabilization phase, triggering an early warning.

[0066] This stage rapidly increases the pressure of the tank's air cushion using maximum flow rate, shortening the pressurization time. A time threshold is used to prevent overshoot or abnormalities caused by prolonged high-flow-rate pressurization.

[0067] 3. Precision voltage stabilization stage Judgment conditions:

[0068] Integrated valve operation: according to The opening of the dual valves is adjusted in real time to compensate for the deviation from the target value. Control logic: The larger the deviation, the larger the opening; the smaller the deviation, the smaller the opening. This phase involves a smooth approach to the target pressure, suppressing overshoot, reducing shocks, and minimizing pressure fluctuations.

[0069] 4. Pressure Holding Stage Judgment conditions:

[0070] Integrated valve operation: Enters micro-flow closed-loop regulation, the valve port maintains a small opening or intermittent fine adjustment; performs small opening or intermittent fine adjustment of the double check valve with a fixed step size, and adds real-time pressure deviation compensation; executes opening step advance and retreat according to the difference between real-time pressure and target pressure, if the pressure is too low, the opening step size is increased to compensate, and if the pressure is too high, the opening step size is decreased to compensate, thus offsetting the pressure deviation caused by temperature drift, leakage, and inlet fluctuation in real time; This phase will stabilize the pressure. Within the specified range, constant pressure is maintained.

[0071] 5. Fault Protection Phase (Real-time Trigger) Reverse differential pressure protection: And the difference A preset threshold is set, and both valves immediately close; the difference is [value missing]. , The difference; Overvoltage protection: The dual valves quickly close, forcibly limiting the flow; Flow abnormality protection: If the pressure rise rate is too fast or too slow, the valve position will be automatically corrected to stabilize the flow rate.

[0072] Rapid boost timeout protection: Forcefully exit rapid boost, limit current and stabilize voltage, and report the fault.

[0073] It should be noted that this system is the system corresponding to the above method. All implementation methods in the above method embodiments are applicable to the embodiments of this system and can achieve the same technical effect.

[0074] The integrated valve body described in the above embodiments of the present invention integrates the filter, the first booster check valve, and the second booster check valve into the same valve body, with an integrated internal flow channel. The dual check valve series integrated structure arranges two check valves in series within the valve body, providing double backflow prevention. The integrated module for filtration, boosting, and backflow prevention forms a standard integrated module that can directly replace existing discrete pipelines. The low-disturbance stable flow channel incorporates a diffuser / guide structure within the valve body to reduce pressure fluctuations. The integrated booster device with a reserved monitoring interface allows for online monitoring of inlet / outlet pressure. The tank booster dual-valve collaborative intelligent pressure stabilization algorithm, based on segmented closed-loop control, achieves integrated rapid boosting, precise pressure stabilization, and fault protection.

[0075] Meanwhile, integration is significantly improved: multiple components are combined into one, resulting in a smaller size and simpler layout. Sealing points are significantly reduced: eliminating multiple pipe joints lowers the risk of leakage. Installation and maintenance are faster: overall disassembly and assembly significantly shortens replacement time. Flow channels are smoother: pressure fluctuations are smaller, and pressurization is more stable. Reliability is higher: the dual one-way valves have better coaxiality, resulting in superior opening and closing synchronization and sealing performance. Versatility is strong: the interface is compatible with existing ground gas distribution platforms and storage tank energy dissipators, allowing for direct replacement and upgrades. The pressurization process is more intelligent: adopting a dual-valve collaborative intelligent pressure stabilization algorithm, it automatically achieves rapid pressurization, precise pressure stabilization, and overpressure protection, reducing manual intervention and improving the accuracy of air cushion pressure control and the level of system automation.

[0076] The integrated valve body in the above embodiments of the present invention can also employ a three-way valve integration to enhance redundancy, while the remaining structure and flow channels remain unchanged. The filter assembly is positioned downstream of the dual one-way valves, forming an integrated layout of "pressurization before filtration." The valve body uses a split-type welding / bolt combination instead of integral machining, achieving low-cost manufacturing. The one-way valves use interchangeable conical seals / flat seals / lip seals to meet different pressure levels.

[0077] Through the above description of the embodiments, those skilled in the art can clearly understand that each embodiment can be implemented by means of software plus necessary general-purpose hardware platforms, and of course, it can also be implemented by hardware. Based on this understanding, the above technical solutions, in essence or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, magnetic disk, optical disk, etc., including several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute the methods of various embodiments or some parts of embodiments.

[0078] The above description represents the preferred embodiments of the present invention. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principles of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A method for controlling the pressure of a rocket fuel tank, characterized in that, An integrated valve body (10) is connected to the air inlet of the rocket fuel tank. The integrated valve body (10) includes: a filter element (5) connected to the ground pressurization pipeline (9) of the rocket's first-stage fuel tank; a first check valve (6) connected to the filter element (5); and a second check valve (7) connected to the first check valve (6). The outlet of the second check valve (7) is connected to the air inlet of the rocket fuel tank. The method includes: According to the pressurization command, the first check valve (6) and the second check valve (7) of the integrated valve body (10) are fully open for a first preset time period, so that the outlet pressure of the second check valve (7) is less than or equal to the target pressure of the rocket fuel tank. Obtain the real-time outlet pressure of the second check valve (7) of the integrated valve body (10); When the real-time outlet pressure is within a first threshold range, a first control command is output; the first threshold range is determined based on the target pressure of the rocket fuel tank. When the real-time outlet pressure is within the second threshold range, a second control command is output; the maximum value of the first threshold range is equal to the minimum value of the second threshold range; the second threshold range is determined based on the target pressure of the rocket fuel tank. According to the first control command, the valve opening of the first one-way valve (6) is controlled to be the first opening value and the valve opening of the second one-way valve (7) is controlled to be the second opening value, so that the ground pressurization pipeline (9) of the rocket first stage fuel tank supplies gas to the rocket fuel tank at the first pressure through the filter element (5), the first one-way valve (6) and the second one-way valve (7); According to the second control command, the valve opening of the first one-way valve (6) is controlled to the third opening value and the valve opening of the second one-way valve (7) is controlled to the fourth opening value, so that the ground pressurization pipeline (9) of the rocket's first-stage fuel tank supplies gas to the rocket fuel tank at the second pressure through the filter element (5), the first one-way valve (6) and the second one-way valve (7).

2. The rocket fuel tank pressure control method according to claim 1, characterized in that, Also includes: When the real-time outlet pressure is within the third threshold range, a third control command is output; the minimum value of the third threshold range is greater than the maximum value of the second threshold range. The second threshold range is determined based on the target pressure of the rocket fuel tank; According to the third control command, the valve opening of the first one-way valve (6) is controlled to be reduced to the fifth opening value within the second preset time period, and the valve opening of the second one-way valve (7) is controlled to be reduced to the sixth opening value within the second preset time period, so that the ground pressurization pipeline (9) of the rocket first stage fuel tank supplies gas to the rocket fuel tank according to the third pressure through the filter element (5), the first one-way valve (6) and the second one-way valve (7).

3. The rocket fuel tank pressure control method according to claim 1, characterized in that, Also includes: Obtain the real-time inlet pressure of the integrated valve body (10); Based on the real-time inlet pressure, the real-time outlet pressure, and the pressure difference between the real-time inlet pressure and the real-time outlet pressure, a fourth control command is output. According to the fourth control command, the first check valve (6) and the second check valve (7) are controlled to close.

4. The rocket fuel tank pressure control method according to claim 1, characterized in that, Controlling the opening degree of the first check valve (6) to a first opening value and controlling the opening degree of the second check valve (7) to a second opening value according to the first control command includes: The first opening value is determined based on the deviation between the real-time outlet pressure and the target pressure; The second opening value is determined based on the first opening value, the outlet pressure, and the target pressure; According to the first control command, the valve opening of the first check valve (6) is controlled to be the first opening value and the valve opening of the second check valve (7) is controlled to be the second opening value.

5. The rocket fuel tank pressure control method according to claim 4, characterized in that, Determining the second opening value based on the first opening value, the outlet pressure, and the target pressure includes: The dynamic correction amount is determined based on the first opening value, the outlet pressure, and the target pressure. The second opening value is determined based on the first opening value and the dynamic correction amount.

6. The rocket fuel tank pressure control method according to claim 1, characterized in that, According to the second control command, the valve opening of the first check valve (6) is controlled to a third opening value and the valve opening of the second check valve (7) is controlled to a fourth opening value, including: The adjustment step size is determined based on the real-time pressure deviation between the real-time outlet pressure and the target pressure. The real-time compensation amount for valve pressure drift is determined based on the flow resistance data, average temperature data, and gas leakage data over a preset time period. The third opening value is determined based on the real-time compensation amount for valve pressure drift, the current opening degree of the first check valve (6), and the adjustment step size; The fourth opening value is determined based on the third opening value, the dual-valve cooperative coupling coefficient, and the real-time compensation amount for valve pressure drift. According to the second control command, the valve opening of the first check valve (6) is controlled to the third opening value and the valve opening of the second check valve (7) is controlled to the fourth opening value.

7. The rocket fuel tank pressure control method according to claim 6, characterized in that, according to Determine the adjustment step size; where, Indicates the adjustment step size. This indicates the preset base step size. Represents a symbolic function. This indicates the real-time pressure deviation value. This indicates the target pressure of the storage tank.

8. The rocket fuel tank pressure control method according to claim 6, characterized in that, according to Determine the dual-valve cooperative coupling coefficient, where, This represents the coupling coefficient of the two valves. Indicates the third opening value; This indicates real-time export pressure; This indicates the maximum pressure that the integrated valve body (10) can withstand.

9. A rocket fuel tank pressure control system, characterized in that, include: An integrated valve body (10) connected to the air inlet of the rocket fuel tank includes: a filter element (5) connected to the ground pressurization pipeline (9) of the rocket's first-stage fuel tank; a first check valve (6) connected to the filter element (5); and a second check valve (7) connected to the first check valve (6), the outlet of which is connected to the air inlet of the rocket fuel tank; and a controller connected to the filter element (5), the first check valve (6), and the second check valve (7), respectively. The filter element (5), the first check valve (6), and the second check valve (7) are fixedly connected through the housing (2); The controller: according to the pressurization command, controls the first check valve (6) and the second check valve (7) of the integrated valve body (10) to be fully open for a first preset time period, so that the outlet pressure of the second check valve (7) is less than or equal to the target pressure of the rocket fuel tank; Obtain the real-time outlet pressure of the second check valve (7); When the real-time outlet pressure is within a first threshold range, a first control command is output; the first threshold range is determined based on the target pressure of the rocket fuel tank. When the real-time outlet pressure is within the second threshold range, a second control command is output; the maximum value of the first threshold range is equal to the minimum value of the second threshold range. The second threshold range is determined based on the target pressure of the rocket fuel tank; According to the first control command, the valve opening of the first one-way valve (6) is controlled to be the first opening value and the valve opening of the second one-way valve (7) is controlled to be the second opening value; so that the ground pressurization pipeline (9) of the rocket first stage fuel tank supplies gas to the rocket fuel tank at the first pressure through the filter element (5), the first one-way valve (6) and the second one-way valve (7); According to the second control command, the valve opening of the first one-way valve (6) is controlled to the third opening value and the valve opening of the second one-way valve (7) is controlled to the fourth opening value, so that the ground pressurization pipeline (9) of the rocket's first-stage fuel tank supplies gas to the rocket fuel tank at the second pressure through the filter element (5), the first one-way valve (6) and the second one-way valve (7).

10. The rocket fuel tank pressure control system according to claim 9, characterized in that, The filter element (5), the first check valve (6), and the second check valve (7) are coaxial and connected in the same direction.

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