Rocket ground refueling control system and control method

Abstract

The application discloses a rocket ground filling control system and a control method. The control system comprises a general command control network, a ground filling workstation, a main control system, a process system and a safety monitoring system. Each device in the main control system and the process system is provided with a general control device. The control device of the process system is connected with each device through an electric connector cable based on an electric connector interface, can save a large amount of work for ground equipment control, collection and data transmission, saves cost and time for space launch and ground equipment filling debugging, is flexible in control, high in reliability, can quickly establish a system platform, is high in expansibility, supports multi-system application and operation, the control method simultaneously monitors each safety index of a filling process system in real time, can timely perform fault alarm when any index is abnormal, is high in safety and reliability, and ensures safe and stable operation of the whole system.

Description

Technical Field

[0001] This invention relates to the field of measurement and control technology, specifically to a rocket ground refueling control system and control method. Background Technology

[0002] During the launch and refueling of carrier rockets, the ground control system is required to provide stable propellant fuel and a reliable gas supply system. However, given the large and complex nature of the ground refueling system, which has high reliability requirements and strict workflow, relying solely on manual observation and operation to complete the workflow of various ground refueling and gas distribution systems increases the risk of personnel operation and hinders rapid emergency response and overall healthy operation and maintenance. Summary of the Invention

[0003] Therefore, the technical problem to be solved by the present invention is to overcome the defect of the rocket ground refueling system in the prior art that cannot respond quickly to emergencies, thereby providing a rocket ground refueling control system and control method.

[0004] To achieve the above objectives, the present invention provides the following technical solution: In a first aspect, embodiments of the present invention provide a rocket ground refueling control system, including: a general command and control network, a ground refueling workstation, a main control system, a process system and a safety monitoring system, wherein the process system includes: a propellant device, a gas distribution device, a vacuum device and a forced removal device, wherein the general command and control network is located in the back-end command and control hall and is used for receiving and sending timing instructions of the process system, monitoring and recording data status. The ground refueling workstation, located in the front-end command and control hall, is used to receive instructions from the central command and control network and send them to the main control system, as well as to monitor and record the data status of the process system and feed it back to the central command and control network. The main control system is used to receive communication commands from the ground refueling workstation and connect to the controller of the process system via an Ethernet interface. It then controls various devices in the process system, collects the status parameters of the process system, stores and records the data, and feeds the data storage records back to the ground refueling workstation. The propellant unit is used to receive instructions from the main control system to execute the propellant loading sequence, control the valves, and collect the flow rate of the loaded fuel. The gas distribution device is used to receive instructions sent by the main control system to execute the working sequence and realize the gas supply function; The forced disconnect device is used to receive instructions sent by the main control system to execute the working sequence and realize the separation of the rocket body from the electrical connector equipment; The evacuation device is used to receive instructions from the main control system to perform the vacuum function of the rocket body, so that the propellant completely fills the rocket body; The safety monitoring system is used to monitor the operating status of the process system and feed it back to the main control system. It will issue an alarm when an abnormality occurs and receive control commands sent by the main control system to intervene and handle the devices included in the process system that are abnormal. Each device in the main control system and process system has a general-purpose control device, which includes: a main controller CPU module, a redundant power supply module, two analog input modules, one analog output module, two digital input modules, two digital output modules, an electrical connector interface, an electrical connector cable, local buttons, and remote buttons. The main controller CPU module has a redundant network interface and dual RS485 communication interfaces. The control device of the process system is connected to each device through an electrical connector cable based on the electrical connector interface.

[0005] In one embodiment, the propellant device, gas distribution device, evacuation device, and forced removal device all include a touch screen. The touch screen is connected to the device via an RS485 communication interface and is used for local single-point testing of the device. After local debugging is completed, remote system integration debugging can be performed via the touch screen or a remote button.

[0006] In one embodiment, the propellant device includes: a fuel storage device, a propellant controller module, a valve system, a flow meter, and an electrical connector cable. The fuel storage device is used to store the propellant fuel required for the rocket body, and the propellant controller module executes the propellant loading sequence, controls the valves, and collects data from the flow meter.

[0007] In one embodiment, the gas distribution device includes: a gas source storage device, a gas distribution controller module, a pressure reducer device, and an electrical connector cable. The gas source storage device provides control gas, pipeline purging gas, and fire-fighting gas for use in rocket body control. The gas distribution controller module receives instructions from the main control system, executes the gas distribution system's operating sequence, and completes the gas supply function. The pressure reducer device reduces the pressure of the required gas source before supplying it to each gas source device. The electrical connector cable is used for communication with the main control system.

[0008] In one embodiment, the forced disconnect device includes: a forced disconnect controller, a DC motor, and a fixed bracket. The forced disconnect controller is locally debugged via a touch screen, and the DC motor is controlled to rotate.

[0009] In one embodiment, the evacuation device includes: an evacuation tank, an evacuation controller module, a pump motor, valves, and vacuum instrumentation equipment. The evacuation tank is used to store propellant inside the rocket body. The evacuation controller module is used to perform local control of the evacuation system, control the start and stop functions of the pump motor by controlling the AC contactor, evacuate to the corresponding range according to process requirements, and execute the corresponding evacuation function by using the readings of the vacuum sensor acquired by analog signals.

[0010] In one embodiment, the monitoring equipment of the safety monitoring system includes: a pressure sensor, a temperature sensor, a liquid level sensor, an oxygen concentration alarm, a methane concentration alarm, a kerosene concentration alarm, a flame detector, an explosion-proof camera, and an audible and visual alarm.

[0011] Secondly, embodiments of the present invention provide a rocket ground refueling control method, based on the rocket ground refueling control system described in the first aspect, comprising: a main control system controlling the process system and safety monitoring system through control commands, and collecting and storing status parameters in real time, wherein the process system includes: a propellant device, a gas distribution device, a vacuum device, and a forced removal device, wherein: The control process for the propellant device includes: determining whether the main control system has issued a signal to start propellant loading; if so, opening the control valve and the corresponding solenoid valve in sequence; monitoring whether the propellant flow rate reaches the preset threshold; if the preset threshold is reached, maintaining the opening of the solenoid valve; and if a stop loading signal is received during the propellant loading process, directly controlling the solenoid valve to close. The control process of the evacuation device includes: starting the pump motor according to the preset pressure value, and monitoring whether the pump motor is operating normally. If it is normal, further determine whether the vacuum pressure value is normal. If it is normal, shut down the pump motor. If the pump motor or vacuum pressure value is detected to be abnormal, control the pump motor to shut down. The control process of the gas distribution device includes: setting a preset pressure value, determining whether the main control system sends a motor start signal, if so, controlling the opening of the electric pressure reducer and the corresponding solenoid valve to reduce pressure, closing the corresponding solenoid valve when the pressure reaches the preset pressure threshold, and controlling the closing of the corresponding solenoid valve if a gas supply stop signal is received during this period. The control process for the forced disconnect device includes: determining whether the main control system sends a motor start signal; if so, starting the motor to rotate forward and controlling the motor to run stably; if a stop motor rotation signal is received during the motor rotation process, the motor is turned off and the corresponding electrical connector is disconnected. The control process for the safety monitoring device includes: simultaneously monitoring one of the following: propellant flow rate, methane concentration, and kerosene concentration; oxygen concentration; the operating status and pressure of the evacuation unit; the pressure and temperature of the gas supply unit; and whether the status of the video monitoring equipment is abnormal; and issuing an alarm signal when at least one of them is abnormal.

[0012] In one embodiment, before the main control system issues a control command, the method further includes: initializing the system and performing mode discrimination, selecting either a remote automatic mode or a local manual mode; if the remote automatic mode is selected, obtaining the preset planning parameters and generating control commands based on the planning parameters; if the local manual mode is selected, obtaining the parameters manually set by the engineer and generating the corresponding control commands.

[0013] The technical solution of this invention has the following advantages: 1. This invention provides a rocket ground refueling control system and control method. The control system includes a general command and control network, a ground refueling workstation, a main control system, a process system, and a safety monitoring system. The process system includes a propellant device, a gas distribution device, a vacuum device, and a forced removal device. Each device in the main control system and the process system has a universal control device. The control device of the process system is connected to each device through an electrical connector cable based on an electrical connector interface. This can save a lot of work in ground equipment control, data acquisition, and data transmission, saving costs and time for aerospace launches and ground equipment refueling and debugging. It is flexible in control, highly reliable, can quickly establish a system platform, and has strong scalability, supporting the application and operation of multiple systems.

[0014] 2. The rocket ground refueling control method provided by this invention can monitor various safety indicators of the refueling process system in real time. When any indicator is abnormal, it can promptly issue a fault alarm, which has high safety and reliability and ensures the safe and stable operation of the entire system. Attached Figure Description

[0015] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0016] Figure 1 This is a framework diagram of the rocket ground refueling control system in an embodiment of the present invention; Figure 2 This is a process flow diagram of the rocket ground refueling control system provided in an embodiment of the present invention; Figure 3 This is a schematic diagram of a general-purpose control device provided in an embodiment of the present invention; Figure 4 This is a schematic diagram showing the side of the general-purpose control device provided in this embodiment of the invention, which has an electrical connector interface, a local button, and a remote button. Figure 5 This invention provides a communication connection diagram for the rocket ground refueling control system in an embodiment of the invention; Figure 6 This is a flowchart of a rocket ground refueling control method provided in an embodiment of the present invention. Detailed Implementation

[0017] The technical solution of the present invention will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0018] Furthermore, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0019] Example 1 This invention provides a rocket ground refueling control system, such as... Figure 1 As shown, it specifically includes: a central command and control network, a ground refueling workstation, a main control system, a process system, and a safety monitoring system. The process system includes: a propellant unit, a gas distribution unit, a vacuum unit, and a forced removal unit. A schematic diagram of the process flow in this embodiment is shown below. Figure 2 As shown. Each unit in the main control system and process system has a set of general-purpose control devices (such as...). Figure 3 As shown), the device includes: a main controller CPU module CRIO-9045NI9208, a redundant power supply module, two analog input modules, one analog output module NI9266, two digital input modules NI9426, two digital output modules NI9472, and an electrical connector interface ( Figure 4 Devices indicated by number 1), electrical connector cables, local pushbuttons ( Figure 4 The device indicated by the number 2) and the remote button ( Figure 4 The device indicated by reference numeral 3), wherein the main controller CPU module contains redundant network interfaces (via Ethernet interface, communication mode Modbus Tcp) and dual communication RS485 interfaces, and the process system control device is connected to various devices via electrical connector cables based on electrical connector interfaces. Figure 5 The diagram illustrates the communication connections between various devices in the rocket ground propellant control system via corresponding interface connections. This communication method significantly reduces workload in ground equipment control, data acquisition, and data transmission, saving costs and time for space launches and ground equipment propellant commissioning. It offers flexible control, high reliability, rapid system platform establishment, and strong scalability, supporting the application and operation of multiple systems.

[0020] In this embodiment, the propellant device, gas distribution device, evacuation device, and forced removal device all include touch screens. The touch screens are connected to the devices via an RS485 communication interface and are used for local single-point testing of the devices. After local debugging is completed, remote system integration debugging can be performed via the touch screen or remote buttons.

[0021] The functional modules of the rocket ground propellant control system are as follows: The central command and control network, located in the back-end command and control hall, includes data servers and operator stations, and is used to manage the sending and receiving of timing instructions for the process system, as well as to monitor and record data in real time. The ground refueling workstation is located in the front-end command and control hall and includes an engineer station, an operator station, and a data server. It is used to receive instructions from the central command and control network and send them to the main control system, as well as to monitor and record the data status of the process system and feed it back to the central command and control network.

[0022] The main control system is used to receive communication commands from the ground refueling workstation and connects to the controller of the process system via an Ethernet interface. It then controls the devices in the process system, collects the status parameters of the process system, stores and records the data, and feeds the data storage records back to the ground refueling workstation. The propellant unit is used to receive instructions (including propellant flow parameters and refueling time parameters) sent by the main control system to execute the propellant refueling sequence, control the valves, and collect the flow rate of the refueling fuel. The propellant system includes: a refueling fuel storage device, a propellant controller module, a valve system, a flow meter, and electrical connector cables. The refueling fuel storage device is used to store the propellant fuel required for the rocket body. The propellant controller executes the propellant refueling sequence, controls the valves, and collects data from the flow meter.

[0023] The gas distribution device is used to receive instructions (including gas distribution system pressure parameters) sent by the main control system to execute the working sequence and realize the gas supply function. The gas distribution device includes: a gas source storage device, a gas distribution controller module, a pressure reducing device, and an electrical connector cable. The gas source storage device is used to supply control gas, pipeline purging gas, and fire-fighting gas for rocket body control. The gas distribution controller module is used to receive instructions from the main control system, execute the working sequence of the gas distribution system, and complete the gas supply function. The pressure reducing device is used to reduce the pressure of the required gas source before supplying it to each gas source device. The electrical connector cable is used for communication with the main control system.

[0024] The forced disconnect device is used to receive instructions sent by the main control system to execute the working sequence and realize the separation of the rocket body from the electrical connector equipment. The forced disconnect device includes: a forced disconnect controller, a DC motor and a fixed bracket. The forced disconnect controller is controlled by a touch screen for local debugging and the DC motor is controlled to rotate.

[0025] The evacuation device receives instructions (including evacuation pressure parameters) from the main control system to perform the rocket body evacuation function, ensuring complete propellant filling of the rocket body. The evacuation device includes: an evacuation tank, an evacuation controller module, a pump motor, valves, and vacuum instruments. The evacuation tank stores some of the propellant inside the rocket body. The evacuation controller module performs local control of the evacuation system, controlling the start and stop of the pump motor via an AC contactor, evacuating to the appropriate range according to process requirements, and satisfying the corresponding evacuation function by measuring the vacuum level sensor readings from analog signals.

[0026] The safety monitoring system is used to monitor the operating status of the process system and feed it back to the main control system. When an abnormality occurs, it will issue an alarm and receive control commands sent by the main control system to intervene and handle the devices included in the process system that are abnormal, so as to ensure on-site safety and stability.

[0027] In one embodiment, the monitoring equipment of the safety monitoring system includes: a pressure sensor, a temperature sensor, a liquid level sensor, an oxygen concentration alarm, a methane concentration alarm, a kerosene concentration alarm, a flame detector, an explosion-proof camera, and an audible and visual alarm. The safety monitoring system promptly detects safety issues based on collected system pressure, temperature, liquid level, concentration, flame signals, and video images. If the pressure sensor (temperature sensor) exceeds the set safety threshold and generates an alarm signal, the corresponding actuator valve will be automatically interlocked for remote control processing, such as automatically opening the discharge valve and closing the process valve. If the liquid level sensor is below the set safety threshold and generates an alarm signal, the corresponding filling valve will be automatically interlocked for remote control processing, stopping the filling of the rocket body. The oxygen concentration alarm and methane concentration alarm use a concentration measurement mode. If the oxygen concentration and methane concentration exceed the safety warning range, an alarm will be triggered if the oxygen concentration exceeds 23%, and a first-level alarm will be triggered if the methane concentration exceeds 25%, and a second-level alarm will be triggered if the methane concentration exceeds 50%. At the same time, the corresponding safety interlock will be performed, closing the corresponding process equipment valves, opening the nitrogen fire-fighting valve, and triggering the audible and visual alarm display. The flame detector uses infrared measurement technology. If a flame signal is detected, the valves of the safety process equipment will be closed, the nitrogen fire-fighting valve will be opened, and the audible and visual alarm display will be triggered. Explosion-proof cameras are used to monitor the operating status of the on-site process equipment and record relevant safety information if any abnormality occurs. The safety monitoring system monitors all safety indicators of the filling process system in real time. When any indicator is abnormal, a fault alarm can be triggered in a timely manner, ensuring high safety and reliability.

[0028] It should be noted that the safety monitoring system uses corresponding gas concentration sensors for safety monitoring based on the specific type of rocket fuel. For example, some rocket types use methane and oxygen as fuel, and correspondingly use methane concentration alarms and oxygen concentration alarms, while other rocket types use kerosene and oxygen as fuel, and correspondingly use methane concentration alarms and oxygen concentration alarms.

[0029] Example 2 This invention provides a rocket ground refueling control method, based on the rocket ground refueling control system in Embodiment 1. The main control system controls the process system and safety monitoring system through control commands. The entire control process is as follows: Figure 6 As shown, where: The main control system receives instructions from the ground refueling workstation, initializes the system, and then first determines whether to use a remote automatic mode or a local manual mode. If the remote automatic mode is selected, it acquires the preset planning parameters and generates control commands based on these parameters. If the local manual mode is selected, it acquires the parameters manually set by the engineer and generates corresponding control commands. These parameters include propellant flow rate parameters, refueling time parameters, gas distribution system pressure parameters, and vacuum pressure parameters. The generated control commands are then sent to each unit for control. The control process for the propellant unit includes: determining whether the main control system has issued a propellant loading start signal; if so, sequentially opening the control valve and the corresponding solenoid valve; monitoring whether the propellant flow rate reaches a preset threshold; if it reaches the preset threshold, maintaining the opening of the solenoid valve; if a stop loading signal is received during propellant loading, directly controlling the solenoid valve to close (e.g., if the preset threshold is reached, maintaining the opening of this solenoid valve, e.g., 50% opening; if a stop loading signal is received during propellant loading, directly controlling the solenoid valve opening to 0%, i.e., closing the valve). The control process for the evacuation unit includes: starting the pump motor according to a preset pressure value and monitoring whether the pump motor's operating status is normal; if normal, further determining whether the vacuum pressure value is normal; if normal, shutting off the pump motor; if an abnormality is detected in the pump motor or vacuum pressure value, controlling the pump motor to shut off. The control process of the gas distribution device includes: setting a preset pressure value, determining whether the main control system sends a motor start signal, if so, controlling the opening of the electric pressure reducer and the corresponding solenoid valve to reduce pressure, closing the corresponding solenoid valve when the pressure reaches the preset pressure threshold, and controlling the closing of the corresponding solenoid valve if a gas supply stop signal is received during this period. The control process for the forced disconnect device includes: determining whether the main control system sends a motor start signal; if so, starting the motor to rotate forward and controlling the motor to run stably; if a stop motor rotation signal is received during the motor rotation process, the motor is turned off and the corresponding electrical connector is disconnected. In one specific embodiment, the gas distribution device remotely controls the electric pressure reducer via the main control system based on the gas source pressure required by each system. For example, the electric pressure reducer reduces the pressure to the required control gas pressure of 0.7 MPa, purge gas pressure of 2 MPa, booster gas pressure of 5 MPa, and booster gas pressure of 10 MPa, supplying the gas to each system. Simultaneously, after receiving the flow meter parameters and the vacuum system pressure parameters, the propellant device activates the charging signal, and the equipment pre-cools. Once the pre-cooling temperature reaches the required set value, and the vacuum pressure reaches the set value, the propellant charging valve is opened. For example, when the flow meter reaches the set values ​​of 200 L / min and 50 L / min, flow accumulation begins. Once the required charging flow rate is met, the corresponding propellant charging valve is automatically closed. Simultaneously, the vacuum device remotely activates the pump motor to perform the rocket body evacuation function. Once the evacuation pressure reaches the set value, the pump motor start button is turned off, and propellant charging begins. During the propellant loading process, the main control system receives the propellant loading level signal and observes the propellant loading level height, which is divided into levels I, II, III, and IV. Once the level height reaches level IV, the propellant system stops loading and simultaneously starts the forced removal device. The forced removal device starts the DC motor, and the motor runs stably. The received motor stable operation indicator light is observed. Once the loading level electrical connector is forcibly disconnected, the motor indicator light turns off, the forced removal motor stops, and the forced removal device operation ends.

[0030] The control process for the safety monitoring device includes: simultaneously monitoring one of the following: propellant flow rate, methane concentration, and kerosene concentration; oxygen concentration; the operating status and pressure of the evacuation unit; the pressure and temperature of the gas supply unit; and whether the status of the video monitoring equipment is abnormal; and issuing an alarm signal when at least one of them is abnormal.

[0031] In this embodiment of the invention, during the propellant system refueling process, the safety monitoring system monitors the operation in real time, checking whether the propellant flow rate exceeds the thresholds of 200 ± 10 L / min and 50 ± 10 L / min. If so, a system alarm is triggered. Simultaneously, the propellant unit controls the regulating valve to reduce the system flow rate to meet the requirements. Simultaneously, it monitors methane and oxygen concentrations in real time for leakage alarms. A first-level alarm is triggered if the methane concentration exceeds 25%, and a second-level alarm is triggered if it exceeds 50%. An oxygen concentration exceeding 23% triggers a leakage alarm. Alarms are also triggered if the evacuation unit pressure or pump motor starts abnormally; corresponding alarms are triggered if the pressure and temperature sensors in the gas distribution unit display abnormal states. The status of each process system is observed through a video system, which also generates corresponding alarms.

[0032] The rocket ground refueling control method provided in this invention can monitor various safety indicators of the refueling process system in real time. When any indicator is abnormal, it can promptly issue a fault alarm, ensuring high safety and reliability and guaranteeing the safe and stable operation of the entire system.

[0033] Obviously, the above embodiments are merely illustrative examples for clear explanation and are not intended to limit the implementation. Those skilled in the art will recognize that other variations or modifications can be made based on the above description. It is neither necessary nor possible to exhaustively list all possible implementations here. However, obvious variations or modifications derived therefrom are still within the scope of protection of this invention.

Claims

1. A rocket ground refueling control system, characterized in that, include: The system comprises a central command and control network, a ground refueling station, a main control system, a process system, and a safety monitoring system. The process system includes: propellant handling units, gas distribution units, evacuation units, and forced removal units. The central command and control network, located in the back-end command and control hall, is used for the management of the transmission and reception of timing instructions for the process system, as well as the monitoring and recording of data status. The ground refueling workstation, located in the front-end command and control hall, is used to receive instructions from the central command and control network and send them to the main control system, as well as to monitor and record the data status of the process system and feed it back to the central command and control network. The main control system is used to receive communication commands from the ground refueling workstation and connect to the controller of the process system via an Ethernet interface. It then controls various devices in the process system, collects the status parameters of the process system, stores and records the data, and feeds the data storage records back to the ground refueling workstation. The propellant unit is used to receive instructions from the main control system to execute the propellant loading sequence, control the valves, and collect the flow rate of the loaded fuel. The gas distribution device is used to receive instructions sent by the main control system to execute the working sequence and realize the gas supply function; The forced disconnect device is used to receive instructions sent by the main control system to execute the working sequence and realize the separation of the rocket body from the electrical connector equipment; The evacuation device is used to receive instructions from the main control system to perform the vacuum function of the rocket body, so that the propellant completely fills the rocket body; The safety monitoring system is used to monitor the operating status of the process system and feed it back to the main control system. It will issue an alarm when an abnormality occurs and receive control commands sent by the main control system to intervene and handle the devices included in the process system that are abnormal. Each device in the main control system and process system has a general-purpose control device, which includes: a main controller CPU module, a redundant power supply module, two analog input modules, one analog output module, two digital input modules, two digital output modules, an electrical connector interface, an electrical connector cable, local buttons, and remote buttons. The main controller CPU module has a redundant network interface and dual RS485 communication interfaces. The control device of the process system is connected to each device through an electrical connector cable based on the electrical connector interface.

2. The rocket ground refueling control system according to claim 1, characterized in that, The propellant device, gas distribution device, evacuation device, and forced removal device all include touch screens. The touch screens are connected to the devices via an RS485 communication interface for local single-point testing of the devices and for remote system integration testing via the touch screen or remote buttons after local debugging is completed.

3. The rocket ground refueling control system according to claim 2, characterized in that, The propellant system includes: a fuel storage device, a propellant controller module, a valve system, a flow meter, and electrical connector cables. The fuel storage device is used to store the propellant fuel required for the rocket body. The propellant controller module executes the propellant loading sequence, controls the valves, and collects data from the flow meter.

4. The rocket ground refueling control system according to claim 2, characterized in that, The gas distribution device includes: a gas source storage device, a gas distribution controller module, a pressure reducer device, and an electrical connector cable. The gas source storage device provides control gas, pipeline purging gas, and fire-fighting gas for use in rocket body control. The gas distribution controller module receives instructions from the main control system, executes the gas distribution system's operating sequence, and completes the gas supply function. The pressure reducer device reduces the pressure of the required gas source before supplying it to each gas source device. The electrical connector cable is used for communication with the main control system.

5. The rocket ground refueling control system according to claim 2, characterized in that, The forced disconnect device includes: a forced disconnect controller, a DC motor and a fixed bracket. The forced disconnect controller is locally debugged and the DC motor is controlled to rotate via a touch screen.

6. The rocket ground refueling control system according to claim 2, characterized in that, The evacuation device includes: an evacuation tank, an evacuation controller module, a pump motor, valves, and vacuum instruments. The evacuation tank is used to store propellant inside the rocket body. The evacuation controller module is used to complete the local control of the evacuation system. It controls the start and stop functions of the pump motor by controlling the AC contactor, evacuates to the corresponding range according to process requirements, and executes the corresponding evacuation function by using the readings of the vacuum sensor acquired by analog signals.

7. The rocket ground refueling control system according to claim 1, characterized in that, The monitoring equipment of the safety monitoring system includes: pressure sensor, temperature sensor, liquid level sensor, oxygen concentration alarm, methane concentration alarm, kerosene concentration alarm, flame detector, explosion-proof camera, and audible and visual alarm.

8. A rocket ground refueling control method, based on the rocket ground refueling control system according to any one of claims 1-7, characterized in that, include: The main control system controls the process system and safety monitoring system through control commands, collects status parameters in real time, and stores and records the data. The process system includes: propellant unit, gas distribution unit, evacuation unit, and forced removal unit. The control process for the propellant device includes: determining whether the main control system has issued a signal to start propellant loading; if so, opening the control valve and the corresponding solenoid valve in sequence; monitoring whether the propellant flow rate reaches the preset threshold; if the preset threshold is reached, maintaining the opening of the solenoid valve; and if a stop loading signal is received during the propellant loading process, directly controlling the solenoid valve to close. The control process of the evacuation device includes: starting the pump motor according to the preset pressure value, and monitoring whether the pump motor is operating normally. If it is normal, further determine whether the vacuum pressure value is normal. If it is normal, shut down the pump motor. If the pump motor or vacuum pressure value is detected to be abnormal, control the pump motor to shut down. The control process of the gas distribution device includes: setting a preset pressure value, determining whether the main control system sends a motor start signal, if so, controlling the opening of the electric pressure reducer and the corresponding solenoid valve to reduce pressure, closing the corresponding solenoid valve when the pressure reaches the preset pressure threshold, and controlling the closing of the corresponding solenoid valve if a gas supply stop signal is received during this period. The control process for the forced disconnect device includes: determining whether the main control system sends a motor start signal; if so, starting the motor to rotate forward and controlling the motor to run stably; if a stop motor rotation signal is received during the motor rotation process, the motor is turned off and the corresponding electrical connector is disconnected. The control process of the safety monitoring system includes: simultaneously monitoring one of the following: propellant flow rate, methane concentration and kerosene concentration, oxygen concentration, operating status and pressure of the evacuation unit, pressure and temperature of the gas supply unit, and whether the status of the video monitoring equipment is abnormal; and issuing an alarm signal when at least one of them is abnormal.

9. The rocket ground refueling control method according to claim 8, characterized in that, Before the main control system issues control commands, the process also includes: initializing the system and determining the mode, selecting either remote automatic mode or local manual mode. If remote automatic mode is selected, the system obtains the preset planning parameters and generates control commands based on the planning parameters. If local manual mode is selected, the system obtains the parameters manually set by the engineer and generates the corresponding control commands.

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