A precooling control method and device for a rocket propellant filling system

Abstract

This invention provides a pre-cooling control method for a rocket propellant refueling system, comprising: setting up a return pipe between the refueling pump outlet pipe and the storage tank; starting the refueling pump to operate at a first frequency; opening a first regulating valve in the return pipe; when the propellant gas content in the return pipe is lower than a first set value, closing the regulating valve in the return pipe; opening a second regulating valve between the supercooler and the storage tank; adjusting the refueling pump to operate at a second frequency, wherein the second frequency is greater than the first frequency; real-time acquisition of a first pressure value in the supercooler inlet pipe and a second pressure value in the supercooler outlet pipe; when the difference between the second pressure value and the first pressure value is greater than a second set value, shutting off the refueling pump; opening the first regulating valve in the return pipe; and closing the second regulating valve. This control method can improve the reliability of the rocket propellant refueling pre-cooling process.

Description

Technical Field

[0001] This invention relates to the field of rocket propellant loading systems, and more specifically to a pre-cooling control method and apparatus for rocket propellant loading systems. Background Technology

[0002] In recent years, my country's aerospace industry has made great achievements. Cryogenic propellants (such as liquid oxygen / methane and liquid oxygen / liquid hydrogen) have advantages such as being non-toxic, pollution-free, low-cost, high specific impulse, and high thrust as propellants for launch vehicles, making them the best propellant choice for large launch vehicles.

[0003] Currently, cryogenic liquid propellants are supplied using a combination of vacuum-insulated tanks and self-pressurized delivery to meet the refueling requirements of large launch vehicles. However, this approach has significant limitations: First, the launch site storage area requires the construction of large-scale tank areas, pressurizers, and complex pipelines, valves, and control systems, resulting in high infrastructure construction costs. Second, the large number of equipment pipelines and complex instruments and control systems not only lead to low space utilization but also significantly increase the difficulty of system integration and debugging.

[0004] Therefore, there is an urgent need to design a precooling control method and device for rocket propellant loading systems that is simple in structure, low in cost, and capable of achieving rapid precooling control response. Summary of the Invention

[0005] The purpose of this invention is to overcome the shortcomings of the prior art and provide a pre-cooling control method and device for a rocket propellant refueling system.

[0006] This invention provides a pre-cooling control method for a rocket propellant refueling system. The refueling system includes a storage tank, a refueling pump, a supercooler, and a storage tank connected in sequence. The refueling pump pumps propellant from the storage tank through the supercooler to the storage tank. The control method includes: setting up a return pipe between the refueling pump outlet line and the storage tank; starting the refueling pump to operate at a first frequency; opening a first regulating valve in the return pipe; when the gas content of the propellant in the return pipe is lower than a first set value, closing the regulating valve in the return pipe; opening a second regulating valve between the supercooler and the storage tank; and regulating the refueling process. The pump operates at a second frequency, which is greater than the first frequency. The first pressure value of the subcooler inlet pipe and the second pressure value of the subcooler outlet pipe are collected in real time. When the charging pump is shut down in an emergency, if the difference between the second pressure value and the first pressure value is greater than the second set value, the first regulating valve of the return pipe is opened and the second regulating valve is closed. When the temperature of the charging pump reaches the first set temperature value, the charging pump is restarted and operates at the first frequency. If the difference between the first pressure value and the second pressure value is greater than the third set value, the charging pump is adjusted to operate at the second frequency and the second regulating valve is opened.

[0007] Preferably, the control method further includes: setting a pressure maintaining pipeline outside the storage tank, setting a vaporizer and a first shut-off valve on the pressure maintaining pipeline, monitoring a third pressure value of the storage tank, and when the third pressure value is lower than a fourth set value, opening the first shut-off valve and the vaporizer to pressurize the storage tank through the vaporizer.

[0008] More preferably, the control method further includes: when the third pressure value is higher than the fifth set value, wherein the fifth set value is greater than the fourth set value, closing the first shut-off valve and the vaporizer.

[0009] More preferably, the control method further includes: when the pressure at the inlet of the filling pump is lower than the sixth set value, adjusting the filling pump to operate at the first frequency and issuing a fault warning signal.

[0010] Optionally, the control method further includes: when the pressure at the inlet of the filling pump is lower than a sixth set value and remains so for a first duration, shutting down the filling pump and issuing a restart signal.

[0011] This invention also provides a pre-cooling control device for a rocket propellant refueling system, comprising: the refueling system including a storage tank, a refueling pump, a supercooler, and a storage tank connected in sequence; the refueling pump pumps propellant from the storage tank through the supercooler to the storage tank; the control device includes: a start-up module, which sets up a return pipe between the refueling pump outlet pipe and the storage tank, starts the refueling pump to operate at a first frequency, and opens a first regulating valve of the return pipe; and an exhaust module, which closes the regulating valve of the return pipe and opens a second regulating valve between the supercooler and the storage tank when the gas content of the propellant in the return pipe is lower than a first set value, thereby regulating... The charging pump operates at a second frequency, which is greater than the first frequency. The monitoring module collects the first pressure value of the subcooler inlet pipe and the second pressure value of the subcooler outlet pipe in real time. When the charging pump is shut down in an emergency, if the difference between the second pressure value and the first pressure value is greater than a second set value, the first regulating valve of the return pipe is opened and the second regulating valve is closed. The restart module restarts the charging pump when the temperature of the charging pump reaches the first set temperature value, and restarts the charging pump to operate at the first frequency. If the difference between the first pressure value and the second pressure value is greater than a third set value, the charging pump is adjusted to operate at the second frequency, and the second regulating valve is opened.

[0012] Preferably, the control device further includes: a maintenance module, which has a pressure maintenance pipeline installed on the outside of the storage tank, and a vaporizer and a first shut-off valve installed on the pressure maintenance pipeline. The module monitors the third pressure value of the storage tank, and when the third pressure value is lower than a fourth set value, it opens the first shut-off valve and the vaporizer to pressurize the storage tank through the vaporizer.

[0013] More preferably, the control device further includes: a shut-off module that shuts off the first shut-off valve and the vaporizer when the third pressure value is higher than the fifth set value, wherein the fifth set value is greater than the fourth set value.

[0014] More preferably, the control device further includes a fault module, which adjusts the filling pump to operate at a first frequency and issues a fault warning signal when the pressure at the inlet of the filling pump is lower than a sixth set value.

[0015] The present invention also provides a main controller for a rocket propellant refueling system, comprising: a processor and a memory storing computer program instructions; the processor executes the computer program instructions to implement the pre-cooling control method of the rocket propellant refueling system described above.

[0016] The beneficial effects of this invention are as follows: The pre-cooling control method of the rocket propellant loading system in this embodiment, by setting up a return pipe, can push propellant with entrained air back into the storage tank during the starting stage of the loading pump. After the entrained air in the pipe is purged, the rocket tank is loaded, avoiding the risk of cavitation in the loading pump and improving the reliability of the rocket propellant loading process. During the operation of the loading system, if the pressure in the supercooler outlet pipe is greater than the pressure in the supercooler inlet pipe, preventing the loading pump from starting, the pump can be restarted through the return pipe. This function can significantly improve the system's fault tolerance, increase the efficiency of system fault handling, and ensure the safety and stability of the loading system.

[0017] It should be understood that the above general description and the following specific embodiments are merely exemplary and illustrative, and do not limit the scope of the invention. Attached Figure Description

[0018] The accompanying drawings, which are part of the specification of this invention, illustrate exemplary embodiments of the invention. The drawings, together with the description in the specification, serve to illustrate the principles of the invention.

[0019] Figure 1 This is a schematic diagram of a precooling control method for a rocket propellant loading system according to an embodiment of the present invention;

[0020] Figure 2 This is a schematic diagram of a rocket propellant loading system according to an embodiment of the present invention;

[0021] Figure 3 This is a schematic diagram of a rocket propellant loading system according to another embodiment of the present invention;

[0022] Figure 4 This is a schematic diagram of a precooling control device for a rocket propellant loading system according to an embodiment of the present invention.

[0023] Figure label:

[0024] 101-Storage tank, 102-Addition pump, 103-Subcooler, 104-Storage tank, 105-First regulating valve, 106-Second regulating valve, 107-Vaporizer, 108-First shut-off valve. Detailed Implementation

[0025] The features and exemplary embodiments of various aspects of the present invention will now be described in detail. To make the objectives, technical solutions, and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only configured to explain the present invention and to exemplify the principles of the present invention, and are not configured to limit the present invention. In addition, the structural components in the drawings are not necessarily drawn to scale. For example, the dimensions of some structural components or regions in the drawings may be enlarged for other structural components or regions to aid in the understanding of the embodiments of the present invention.

[0026] The directional terms used in the following description refer to the directions shown in the figures and are not intended to limit the specific structure of the embodiments of the present invention. In the description of the present invention, it should be noted that, unless otherwise stated, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in the present invention according to the specific circumstances.

[0027] Furthermore, the terms "comprising," "including," "having," or any other variations thereof are intended to cover non-exclusive inclusion, such that a structure or component that includes a list of elements includes not only those elements but also other structural elements that are not expressly listed or inherent to the structure or component. Without further limitations, an element defined by the phrase "comprising..." does not exclude the presence of other identical elements in the article or apparatus that includes the element.

[0028] Spatial relation terms such as "below," "under," "under," "low," "above," "on," and "high" are used for descriptive convenience to explain the positioning of one element relative to a second element, indicating that these terms are intended to cover different orientations of the device, in addition to those different from those shown in the figure. Furthermore, phrases such as "one element on / below another element" can indicate that two elements are in direct contact, or that there are other elements between the two elements. In addition, terms such as "first" and "second" are also used to describe individual elements, areas, parts, etc., and should not be considered limiting. Similar terms are used throughout the description to refer to similar elements.

[0029] It will be apparent to those skilled in the art that the present invention can be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention.

[0030] Figure 1 This is a schematic diagram of a precooling control method for a rocket propellant loading system according to an embodiment of the present invention; Figure 2 This is a schematic diagram of a rocket propellant loading system according to an embodiment of the present invention; Figure 3 This is a schematic diagram of a rocket propellant loading system according to another embodiment of the present invention; Figure 4 This is a schematic diagram of a precooling control device for a rocket propellant loading system according to an embodiment of the present invention. Example

[0031] like Figure 1 and Figure 2 As shown, this embodiment provides a precooling control method for a rocket propellant refueling system. The refueling system includes a storage tank 101, a refueling pump 102, a supercooler 103, and a storage tank 104 connected in sequence. The refueling pump 102 pumps the propellant from the storage tank 101 through the supercooler 103 to the storage tank 104.

[0032] The control method includes the following steps:

[0033] S100: A return pipe is set between the liquid outlet line of the filling pump 102 and the storage tank 101. The filling pump 102 is started to run at the first frequency, and the first regulating valve 105 of the return pipe is opened.

[0034] S200: When the gas content of propellant in the return pipeline is lower than the first set value, close the regulating valve of the return pipeline, open the second regulating valve 106 between the subcooler 103 and the storage tank 104, and adjust the injection pump 102 to operate at the second frequency, wherein the second frequency is greater than the first frequency.

[0035] S300: Real-time acquisition of the first pressure value of the liquid inlet pipe of the subcooler 103 and the second pressure value of the liquid outlet pipe of the subcooler 103. When the injection pump 102 is shut down in an emergency, if the difference between the second pressure value and the first pressure value is greater than the second set value, the first regulating valve 105 of the return pipe is opened and the second regulating valve 106 is closed.

[0036] S400: When the temperature of the filling pump 102 reaches the first set temperature value, the filling pump 102 is restarted and runs at the first frequency. When the difference between the first pressure value and the second pressure value is greater than the third set value, the filling pump 102 is adjusted to run at the second frequency and the second regulating valve 106 is opened.

[0037] Specifically, step S100 enables the propellant to circulate within the system, facilitating system pre-cooling and removing gas from the pipelines. This prevents gas in the pipelines from causing propellant temperature and pressure fluctuations, ensuring stable propellant delivery within the refueling pipeline. Step S200, while ensuring a sufficiently low gas content in the pipelines, improves refueling efficiency and accelerates propellant delivery to the storage tank 104. Step S300 can promptly stop the refueling process in case of abnormal pressure difference in the supercooler 103, preventing equipment damage or refueling anomalies. Step S400's phased restart ensures a smooth restart of the refueling process after the system returns to normal. The pre-cooling control method in this embodiment maximizes the utilization of propellant cooling capacity, significantly shortens pre-cooling time, and improves overall system efficiency.

[0038] Among them, the use of cryogenic pumps as pressurization equipment in the refueling system enables rapid response to pressure and frequency, significantly improving the pressurization capacity of the refueling system. Furthermore, the refueling flow rate and temperature can be controlled by adjusting the frequency and regulating valve opening, meeting the dynamic requirements of refueling parameters at different stages, optimizing propellant refueling time, and improving the controllability of the rocket refueling process.

[0039] In one alternative embodiment, storage tank 101 is selected as a large-capacity atmospheric pressure flat-bottomed tank. Compared with the complex systems of multiple tanks connected in series in this embodiment, the construction cost is lower, and it has significant advantages in operation and maintenance. The number of equipment and valves that need to be operated during the task is greatly reduced, effectively reducing the preparation time for filling. The atmospheric pressure flat-bottomed tank has a simple structure and is easy to maintain. The cryogenic pump has stable performance and fewer daily maintenance points, which greatly reduces equipment maintenance costs and technical barriers.

[0040] In this embodiment, by setting up a return pipeline, propellant with trapped air can be pushed back into the storage tank 101 during the startup phase of the refueling pump 102. The rocket propellant tank 104 is then refueled only after the trapped air in the pipeline has been expelled, thus avoiding the risk of cavitation in the refueling pump 102 and improving the reliability of the rocket propellant refueling process. During the operation of the refueling system, if the pressure in the outlet pipeline of the supercooler 103 is greater than the pressure in the inlet pipeline of the supercooler 103, preventing the refueling pump 102 from starting, the refueling pump 102 can be restarted via the return pipeline. This function significantly improves the system's fault tolerance, increases the efficiency of system fault handling, and ensures the safety and stability of the refueling system.

[0041] like Figure 3As shown, in a preferred embodiment, the control method further includes: installing a pressure maintaining pipeline outside the storage tank 101, with a vaporizer 107 and a first shut-off valve 108 installed on the pressure maintaining pipeline; monitoring a third pressure value of the storage tank 101; and opening the first shut-off valve 108 and the vaporizer 107 when the third pressure value is lower than a fourth set value, thereby pressurizing the storage tank 101 through the vaporizer 107. This method can prevent the pressure of the storage tank 101 from becoming too low, ensuring the safe operation of the system. This solution can greatly reduce equipment risks and provide a guarantee for the stable operation of the pre-cooling and filling of the entire filling system.

[0042] In another preferred embodiment, the control method further includes: closing the first shut-off valve 108 and the vaporizer 107 when the third pressure value is higher than the fifth set value, wherein the fifth set value is greater than the fourth set value. This ensures that the pressure inside the storage tank 101 remains stable within a safe pressure range, providing power for the normal delivery of propellant. This method ensures that the propellant pressure is neither too low, affecting the normal supply of propellant, nor too high, causing safety hazards.

[0043] In a preferred embodiment, the control method further includes: when the inlet pressure of the filling pump 102 is lower than a sixth preset value, adjusting the filling pump 102 to operate at a first frequency and issuing a fault warning signal. This emergency handling mechanism ensures that the filling pump 102 can adjust its frequency according to the inlet pressure value, guaranteeing that the filling pump 102 can operate in a safe environment.

[0044] In another preferred embodiment, the control method further includes: when the pressure at the inlet of the filling pump 102 is lower than a sixth preset value and remains below it for a first duration, shutting down the filling pump 102 and issuing a restart signal. This design can shut down the filling pump 102 to avoid equipment failure and restart the filling pump 102 when a fault warning occurs and the pump cannot be restored to normal operation.

[0045] This control method achieves effective pre-cooling of the rocket propellant refueling system by precisely controlling the operating frequency of the refueling pump 102 and the on / off states of each regulating valve, ensuring that the temperature and pressure of the propellant remain within an appropriate range during the refueling process. Simultaneously, the method also possesses a comprehensive anomaly handling mechanism, capable of responding to emergencies such as emergency shutdown of the refueling pump 102, thereby improving the safety and reliability of the entire refueling system.

[0046] For example, the first frequency can be set to 10Hz, the second frequency can be set to 20Hz, the first setting value can be set to 2%ppm, the second setting value can be set to 0.4MPa, the third setting value can be set to 0.05MPa, the fourth setting value can be set to 10kPa, the fifth setting value can be set to 18kPa, the sixth setting value can be set to 0.06MPa, and the first setting temperature value can be set to 95K.

[0047] This solution simplifies the propellant loading system structure and optimizes the loading process through the integrated design of storage tank 101 and loading pump 102. Compared with the traditional vacuum insulated tank group solution for storing propellant, the pre-cooling control method of the loading system proposed in this invention can greatly reduce space occupancy, optimize the loading process to shorten loading time, reduce system construction and operation and maintenance costs, and reduce the need for manual operation, providing reliable support for unattended loading and high-frequency flight-based launch requirements. Example

[0048] This embodiment provides a rocket propellant pre-cooling control device.

[0049] The device includes a fueling system comprising a storage tank 101, a fueling pump 102, a subcooler 103, and a storage tank 104 connected in sequence. The fueling pump 102 pumps propellant from the storage tank 101 through the subcooler 103 and into the storage tank 104.

[0050] like Figure 4 As shown, the rocket propellant refueling precooling control device also includes a start-up module, an exhaust module, a monitoring module, and a restart module.

[0051] The start-up module is designed with a return pipe between the outlet line of the refueling pump 102 and the storage tank 101. The start-up module controls the refueling pump 102 to operate at a first frequency, while simultaneously opening the first regulating valve 105 of the return pipe. This design allows the propellant to circulate within the system, which is beneficial for system pre-cooling and removing gas from the pipeline.

[0052] The venting module works in conjunction with the start-up module. When the propellant gas content in the return pipeline is lower than a first set value, the venting module closes the regulating valve of the return pipeline, opens the second regulating valve 106 between the subcooler 103 and the storage tank 104, and controls the fueling pump 102 to operate at a second frequency, which is greater than the first frequency. This design can improve fueling efficiency and accelerate the delivery of propellant to the storage tank 104 while ensuring that the gas content in the pipeline is sufficiently low.

[0053] The monitoring module collects the first pressure value of the liquid inlet pipe of the subcooler 103 and the second pressure value of the liquid outlet pipe of the subcooler 103 in real time. When the filling pump 102 is shut down in an emergency, if the difference between the second pressure value and the first pressure value is greater than a second set value, the first regulating valve 105 of the return pipe is opened and the second regulating valve 106 is closed. This design can stop the filling process in time when the pressure difference of the subcooler 103 is abnormal, preventing equipment damage or abnormal filling.

[0054] The restart module is responsible for restarting the system after an interruption during the refueling process. When the temperature of the refueling pump 102 reaches the first set temperature value, the restart module controls the refueling pump 102 to restart and operate at the first frequency. Subsequently, when the difference between the first pressure value and the second pressure value is greater than the third set value, the restart module controls the refueling pump 102 to start operating at the second frequency and opens the second regulating valve 106. This staged restart design ensures that the system smoothly restarts the refueling process after returning to normal.

[0055] The rocket propellant refueling precooling control device also includes a pressure maintenance device for the storage tank 101. This device includes a maintenance module, a pressure maintenance pipeline installed outside the storage tank 101, and a vaporizer 107 and a first shut-off valve 108 installed on the pressure maintenance pipeline. The maintenance module monitors a third pressure value of the storage tank 101. When the third pressure value is lower than a fourth preset value, the first shut-off valve 108 and the vaporizer 107 are opened, pressurizing the storage tank 101 through the vaporizer 107. This design prevents the pressure in the storage tank 101 from becoming too low, ensuring the safe operation of the system.

[0056] The rocket propellant loading precooling control device also includes a pressure control device for the storage tank 101. This device includes a shut-off module that controls the closure of the first shut-off valve 108 and the vaporizer 107 when a third pressure value exceeds a fifth set value (where the fifth set value is greater than a fourth set value). This design ensures that a stable pressure is maintained within the storage tank 101, providing power for the normal delivery of propellant.

[0057] The rocket propellant refueling precooling control device also includes a fault handling device for the refueling pump 102. This device includes a fault module that, when the inlet pressure of the refueling pump 102 falls below a sixth preset value, adjusts the pump to operate at a first frequency and issues a fault warning signal. This design allows for safe fault handling and system restoration in the event of a refueling pump 102 malfunction.

[0058] Through the coordinated operation of the above modules, the rocket propellant loading and precooling control device can achieve safe and efficient propellant loading and precooling, effectively control the pressure of storage tank 101, and promptly handle various abnormal situations that may occur during the loading process. Example

[0059] The rocket propellant loading main controller includes a processor and a memory storing computer program instructions. This main controller is the core control component of the rocket propellant loading system, responsible for executing pre-cooling control methods to ensure the safety and reliability of the rocket propellant loading pre-cooling process.

[0060] The main controller's processor can be a high-performance industrial-grade CPU, possessing fast data processing capabilities and strong anti-interference capabilities, enabling stable operation in complex rocket launch environments. The memory consists of two parts: ROM and RAM. The ROM stores the system firmware and basic control programs, while the RAM is used for runtime data processing and temporary storage.

[0061] The processor and memory are connected via a high-speed bus to ensure real-time and reliable data transmission. The main controller has multiple external interfaces, including analog input interfaces, digital input / output interfaces, and communication interfaces, for connecting various sensors, actuators, and other control devices. When the processor executes the computer program instructions in memory, it implements the pre-cooling control method for the rocket propellant refueling system.

[0062] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A precooling control method for a rocket propellant loading system, characterized in that, The refueling system includes a storage tank, a refueling pump, a subcooler, and a storage tank connected in sequence. The refueling pump pumps the propellant from the storage tank through the subcooler and into the storage tank. The control method includes: A return pipeline is installed between the liquid outlet line of the filling pump and the storage tank. The filling pump is started and runs at the first frequency. The first regulating valve of the return pipeline is opened. When the propellant gas content in the return pipeline is lower than the first set value, the regulating valve of the return pipeline is closed, the second regulating valve between the subcooler and the storage tank is opened, and the injection pump is adjusted to operate at the second frequency, wherein the second frequency is greater than the first frequency. The first pressure value of the subcooler inlet pipe and the second pressure value of the subcooler outlet pipe are collected in real time. When the injection pump is shut down in an emergency, if the difference between the second pressure value and the first pressure value is greater than the second set value, the first regulating valve of the return pipe is opened and the second regulating valve is closed. When the temperature of the filling pump reaches the first set temperature value, the filling pump is restarted and runs at the first frequency. When the difference between the first pressure value and the second pressure value is greater than the third set value, the filling pump is adjusted to run at the second frequency and the second regulating valve is opened.

2. The precooling control method for a rocket propellant loading system according to claim 1, characterized in that, Also includes: A pressure maintaining pipeline is installed on the outside of the storage tank. A vaporizer and a first shut-off valve are installed on the pressure maintaining pipeline to monitor the third pressure value of the storage tank. When the third pressure value is lower than the fourth set value, the first shut-off valve and the vaporizer are opened to pressurize the storage tank through the vaporizer.

3. The precooling control method for a rocket propellant loading system according to claim 2, characterized in that, Also includes: When the third pressure value is higher than the fifth setting value, where the fifth setting value is greater than the fourth setting value, the first shut-off valve and the vaporizer are closed.

4. The precooling control method for a rocket propellant loading system according to claim 1, characterized in that, Also includes: When the pressure at the inlet of the filling pump is lower than the sixth set value, the filling pump is adjusted to operate at the first frequency, and a fault warning signal is issued.

5. The precooling control method for a rocket propellant loading system according to claim 4, characterized in that, Also includes: When the pressure at the inlet of the filling pump is lower than the sixth set value and remains below the first set value for a certain duration, the filling pump will be shut down and a restart signal will be sent.

6. A precooling control device for a rocket propellant loading system, characterized in that, include: The refueling system includes a storage tank, a refueling pump, a subcooler, and a storage tank connected in sequence. The refueling pump pumps the propellant from the storage tank through the subcooler and into the storage tank. The control device includes: Start the module, set up a return pipe between the liquid outlet line of the filling pump and the storage tank, start the filling pump to run at the first frequency, and open the first regulating valve of the return pipe; The exhaust module closes the regulating valve of the return pipeline and opens the second regulating valve between the subcooler and the storage tank when the propellant gas content in the return pipeline is lower than the first set value. The charging pump is then adjusted to operate at a second frequency, which is greater than the first frequency. The monitoring module collects the first pressure value of the subcooler inlet pipe and the second pressure value of the subcooler outlet pipe in real time. When the injection pump is shut down in an emergency, if the difference between the second pressure value and the first pressure value is greater than the second set value, the first regulating valve of the return pipe is opened and the second regulating valve is closed. The module is restarted. When the temperature of the filling pump reaches the first set temperature value, the filling pump is restarted and runs at the first frequency. When the difference between the first pressure value and the second pressure value is greater than the third set value, the filling pump is adjusted to run at the second frequency and the second regulating valve is opened.

7. The precooling control device for the rocket propellant loading system according to claim 6, characterized in that, Also includes: The maintenance module has a pressure maintenance pipeline installed on the outside of the storage tank. A vaporizer and a first shut-off valve are installed on the pressure maintenance pipeline to monitor the third pressure value of the storage tank. When the third pressure value is lower than the fourth set value, the first shut-off valve and the vaporizer are opened to pressurize the storage tank through the vaporizer.

8. The precooling control device for the rocket propellant loading system according to claim 7, characterized in that, Also includes: When the module is shut down, if the third pressure value is higher than the fifth set value, where the fifth set value is greater than the fourth set value, the first shut-off valve and the vaporizer will be shut down.

9. The precooling control device for the rocket propellant loading system according to claim 6, characterized in that, Also includes: The fault module adjusts the filling pump to operate at the first frequency and issues a fault warning signal when the pressure at the inlet of the filling pump is lower than the sixth set value.

10. A main controller for a rocket propellant loading system, characterized in that, include: Processor and memory storing computer program instructions; When the processor executes the computer program instructions, it implements the precooling control method for the rocket propellant refueling system as described in any one of claims 1 to 5.

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