Semi-physical simulation test platform of scramjet engine control system

Abstract

The invention belongs to the technical field of scramjet engine control, and particularly relates to a semi-physical simulation test platform of a scramjet engine control system, which comprises a fuel supply and control system, an engine simulator system, a flight control simulation system, a sensor simulation system, an upper computer management system and the like. The test platform can provide test equipment support for development (including control law research, control parameter optimization, performance prediction, fault diagnosis and the like) of a scramjet engine control system, and comprehensively examine system matching performance and control performance of key components such as a controller, a fuel pump, a fuel valve and the like. And stable and reliable operation of the scramjet engine control system is guaranteed.

Description

Technical Field

[0001] The present invention belongs to the technical field of scramjet engine control, and more specifically, relates to a semi-physical simulation test platform for a scramjet engine control system combining digital simulation with physical test. Background Art

[0002] Scramjet is a new type of ramjet engine in which fuel burns in supersonic airflow in the combustion chamber. It is the power system of hypersonic aircraft with a flight speed of Mach 6 or above, and is of great significance in the field of aerospace. The control system of the scramjet engine is to ensure that the scramjet engine works stably and reliably under the changing external working environment and working conditions, and give full play to the performance benefits of the scramjet engine.

[0003] The semi-physical simulation test platform of the scramjet engine control system is used to evaluate and test all physical objects in the engine control system except the engine itself. In the semi-physical simulation platform, the physical engine is replaced by a digital simulator, and the other parts of the system are all physical objects, thus forming a semi-physical simulation test platform consisting of a physical control system and a digital engine simulator.

[0004] The current semi-physical simulation platform for engines is oriented to aircraft engines, and its semi-physical simulation system is usually composed of an engine mathematical model machine, a signal conditioning box, a digital controller, and a fuel supply system. However, for scramjet engines, its semi-physical simulation test technology is not yet mature, and there is currently no semi-physical simulation test platform dedicated to scramjet engine control system verification. Different from the traditional semi-physical simulation test platform of aircraft engines, the scramjet engine has higher requirements for its semi-physical simulation test platform due to its special working environment and state, which are mainly reflected in: (1) The scramjet engine works under hypersonic conditions (Ma>6), and the internal combustion of the engine is at the millisecond level. Therefore, it is necessary to establish a more accurate mathematical model to characterize the working process of the engine, and the model should have high dynamic response capability; (2) Due to its special working principle, the scramjet engine is more susceptible to the influence of the external flight environment, that is, the aircraft and the engine are highly coupled. Therefore, the engine semi-physical simulation test platform should have a flight control simulation system to realize the real-time coupling of the aircraft and the engine; (3) The existing semi-physical simulation platform does not have a host computer management system, and cannot realize the real-time data monitoring, parameter adjustment and control functions of the entire engine semi-physical simulation platform. Summary of the invention

[0005] In view of the defects of the prior art, the present invention provides a semi-physical simulation test platform for a scramjet engine control system and meets the special use requirements of a scramjet engine control system.

[0006] To achieve the above-mentioned purpose of the invention, the technical solution of the present invention is as follows: A semi-physical simulation test platform for scramjet engine control system, including fuel supply control system, flight control simulation system, simulator system, sensor simulation system and host computer management system. in: Fuel supply control system: divided into engine fuel supply system and engine control system, used to supply fuel to scramjet engine, adjust fuel supply flow rate and control fuel supply opening and closing status in real time as well as control functions of the whole working process of engine. Engine control system sends aircraft attitude, altitude, Mach number, fuel pump flow rate and valve status to simulator system through serial communication as input parameters of simulator system; engine fuel supply system and engine control system transmit signals through serial communication and power motor through power cable; fuel supply control system transmits signals with external flight control simulation system through CAN bus communication, connects with external host computer management system through TCP / IP communication, and connects with sensor simulation device in the form of simulated electrical signals; Flight control simulation system: used to simulate the aircraft controller and the information exchange between the flight control computer and the engine controller during flight. The flight control simulation system sends the control instructions of the flight control computer to the engine control system to realize the start and stop of the engine and the conversion of the working state. The flight control simulation system is connected to the engine control system through the CAN bus, and transmits data with the host computer management system through the TCP / IP bus. Simulator system: used to simulate the real-time working state of the scramjet engine. Under the stimulation of the input parameters of the engine control system, the simulator system completes the calculation of the engine state parameters and outputs the calculation results in its interface circuit; it transmits information about fuel flow and valve opening and closing between it and the engine control system through analog electrical signals and digital electrical signals, and transmits temperature and pressure values ​​between the simulator system and the sensor simulation system through analog current; Sensor simulation system: used to simulate the real combustion chamber air pressure, pipeline oil pressure, combustion chamber temperature and pipeline oil temperature physical quantities. The sensor simulation system and the simulator system transmit information through simulated electrical signals. The sensor simulation system converts the signal from the simulator system into a signal type and range that can be recognized by the engine control system, and sends the engine state parameters to the engine control system after conditioning. The sensor simulation system and the fuel supply control system are connected in the form of simulated electrical signals; Host computer management system: used to monitor the status of each system during the entire semi-physical simulation process. It is connected to the simulator system and the fuel supply control system through a serial port, and is connected to the flight control system through a TCP / IP bus.

[0007] As a preferred method, the flight control simulation system includes a flight control computer, a CAN communication module and a flight control software; Flight control computer: used to simulate the entire flight process, send ignition, shutdown, and fuel target flow commands to the engine, receive and process engine status feedback information, and is the hardware carrier attached to the flight control system; CAN communication module: used for CAN communication with the engine controller to realize data and information transmission functions. It is connected to the flight control computer through the USB bus and to the engine controller through the CAN bus; Flight control simulation software: runs in real time in the flight control computer, including flight logic and data processing.

[0008] As a preferred embodiment, the flight control simulation system software is respectively composed of a CAN communication parameter configuration and status display module, a CAN transceiver information display module, a flight control command setting and display module, an engine status display module and a hardware device operation module; CAN communication parameter configuration and status display module: used to configure the CAN communication protocol between the simulated flight control system and the engine control system, and display the real-time status of the communication; CAN transceiver information display module: used to display the original instructions received from the engine control system and the original instructions sent by the simulated flight control system to the CAN bus; Flight control command setting and display module: used to set the simulated flight control commands, including editing, setting and displaying ignition and shutdown commands; Engine status display module: used to parse the CAN commands transmitted by the engine control system in real time and display the parsing results as the working status of the engine; Hardware device operation module: used to directly operate the CAN hardware module, shut down or start the CAN hardware module.

[0009] As a preferred method, the engine mathematical model used in the engine digital simulator system adopts a one-dimensional rapid evaluation model based on the influence coefficient method to quickly calculate the engine operating status (Mach number, pressure and temperature) according to the input parameters. The simulator hardware system is designed using embedded hardware circuits. Finally, the engine's one-dimensional mathematical model program is burned onto the embedded hardware platform to form an engine digital simulator system.

[0010] As a preferred method, the host computer management system communicates with the engine simulator through the RS422 / 485 serial port to monitor the real-time parameters of the engine simulator, burn the program, and modify the parameters; The host computer management system and the engine controller communicate via serial ports to achieve the modification of the engine control program, the display and recording of sensor test data, and the monitoring of the engine status; The host computer management system and the flight control simulation system communicate via TCP / IP to achieve remote monitoring and control of the flight control system.

[0011] As a preferred embodiment, the engine fuel supply system includes a fuel pump, a motor, a high-temperature fuel shut-off valve, a flow meter and pipeline components; The fuel pump is the core component of the engine's fuel supply system. As the power element of the entire fuel supply system, it is located at the source of the fuel supply system. The fuel pump pressurizes the fuel and connects the fuel to the high-temperature fuel shut-off valve through the fuel pipeline. The high-temperature fuel shut-off valve is located downstream of the fuel supply system and controls whether the fuel is injected into the engine. The motor is the power source of the fuel pump and is connected to the fuel pump through a coupling. The motor converts electrical energy into rotational mechanical energy and drives the fuel pump to rotate through the coupling. The flow meter is located at the outlet of the fuel pump and is used to measure the fuel flow entering the engine in real time and feed back the electrical signal to the controller of the engine control system through serial communication.

[0012] As a preferred embodiment, the engine control system includes a controller, a collector, a temperature sensor, a pressure sensor and a power supply component; The controller is the core component of the engine control system. The controller interacts with the collector to collect data through RS422 / 485 serial communication. The collector uploads the collected data to the controller in real time, and the controller further uploads it to the host computer through the bus protocol. The controller and the collector are placed at the test site, the temperature sensor is connected to the collector through a temperature compensation cable, the pressure sensor is connected to the collector through a shielded signal line, and the power supply component is connected to the controller and the pressure sensor through wires to supply power to the entire control system. The various components of the control system are integrated on the operating table at the test site.

[0013] As a preferred method: the engine fuel supply system and the engine control system inside the fuel supply control system transmit signals through RS422 / 485 serial communication, and the motor is powered by a DC power cable.

[0014] As a preferred method, the host computer management system is connected to the simulator system and the fuel supply control system via RS422 / 485 serial ports, and is connected to the flight control system via a TCP / IP bus.

[0015] The flight control simulation system sends the control instructions of the flight control computer to the engine controller to realize the start and stop of the engine and the conversion of the working state; the engine control system sends the aircraft attitude, altitude, Mach number, fuel pump flow and valve state to the engine simulator through serial communication as the input parameters of the simulator system; under the stimulation of the input parameters, the engine simulator completes the calculation of the engine state parameters and outputs the calculation results to its interface circuit; the sensor simulation device converts the signal from the simulator into a signal type and range that can be recognized by the engine control, and sends the engine state parameters to the control system after conditioning.

[0016] The beneficial effects of the present invention compared with the prior art are: (1) The engine mathematical model adopts a one-dimensional rapid evaluation model based on the influence coefficient method, which can quickly characterize the dynamic working process of the engine; (2) The flight control simulation system is designed on the semi-physical simulation platform of the scramjet engine control system to achieve real-time coupling between the aircraft and the engine, and to more realistically and fully verify the functional indicators and performance parameters of the engine control system; (3) The scramjet engine control system semi-physical simulation platform has designed an upper management system that can realize the real-time data monitoring, parameter adjustment and control functions of the entire engine semi-physical simulation platform; (4) The platform effectively solves the shortcomings of high cost and risk points of full physical testing of scramjet engines, while also solving the defects of insufficient accuracy and insufficient physical verification capabilities of pure numerical simulations, providing a powerful tool for the development of scramjet engine control systems (control laws, parameter optimization, performance prediction, fault diagnosis, etc.). BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is the overall structure diagram of the semi-physical platform of the scramjet engine.

[0018] Figure 2 This is the structural relationship of each subsystem of the semi-physical simulation test platform.

[0019] Figure 3 This is the structural diagram of the host computer management system in the semi-physical platform of the scramjet engine. DETAILED DESCRIPTION

[0020] The following describes the embodiments of the present invention through specific examples, and those skilled in the art can easily understand other advantages and effects of the present invention from the contents disclosed in this specification. The present invention can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present invention.

[0021] like Figure 1 As shown, this embodiment provides a semi-physical simulation test platform for a scramjet engine control system, including a fuel supply control system, a flight control simulation system, a simulator system, a sensor simulation system and a host computer management system. in: Fuel supply control system: divided into engine fuel supply system and engine control system, used to supply fuel to scramjet engine, adjust fuel supply flow rate and control fuel supply opening and closing status in real time as well as control functions of the whole working process of engine. Engine control system sends aircraft attitude, altitude, Mach number, fuel pump flow rate and valve status to simulator system through serial communication as input parameters of simulator system; engine fuel supply system and engine control system transmit signals through serial communication and power motor through power cable; fuel supply control system transmits signals with external flight control simulation system through CAN bus communication, connects with external host computer management system through TCP / IP communication, and connects with sensor simulation device in the form of simulated electrical signals; Flight control simulation system: used to simulate the aircraft controller and the information exchange between the flight control computer and the engine controller during flight. The flight control simulation system sends the control instructions of the flight control computer to the engine control system to realize the start and stop of the engine and the conversion of the working state. The flight control simulation system is connected to the engine control system through the CAN bus, and transmits data with the host computer management system through the TCP / IP bus. Simulator system: The Mach number influence coefficient method is used to perform a one-dimensional rapid evaluation of the engine working state. It is used to simulate the real-time working state of the scramjet engine. Under the stimulation of the input parameters of the engine control system, the simulator system completes the calculation of the engine state parameters and outputs the calculation results in its interface circuit. It transmits information about fuel flow and valve opening and closing between it and the engine control system through analog electrical signals and digital electrical signals. The simulator system and the sensor simulation system transmit temperature and pressure values ​​through analog current. Sensor simulation system: used to simulate the real combustion chamber air pressure, pipeline oil pressure, combustion chamber temperature and pipeline oil temperature physical quantities. The sensor simulation system and the simulator system transmit information through simulated electrical signals. The sensor simulation system converts the signal from the simulator system into a signal type and range that can be recognized by the engine control system, and sends the engine state parameters to the engine control system after conditioning. The sensor simulation system and the fuel supply control system are connected in the form of simulated electrical signals; Host computer management system: used to monitor the status of each system during the entire semi-physical simulation process. It is connected to the simulator system and the fuel supply control system through a serial port, and is connected to the flight control system through a TCP / IP bus.

[0022] Preferably, the flight control simulation system includes a flight control computer, a CAN communication module and a flight control software; Flight control computer: used to simulate the entire flight process, send ignition, shutdown, and fuel target flow commands to the engine, receive and process engine status feedback information, and is the hardware carrier attached to the flight control system; CAN communication module: used for CAN communication with the engine controller to realize data and information transmission functions. It is connected to the flight control computer through the USB bus and to the engine controller through the CAN bus; Flight control simulation software: runs in real time in the flight control computer, including flight logic and data processing.

[0023] Preferably, the flight control simulation system software is respectively composed of a CAN communication parameter configuration and status display module, a CAN transceiver information display module, a flight control command setting and display module, an engine status display module and a hardware device operation module; CAN communication parameter configuration and status display module: used to configure the CAN communication protocol between the simulated flight control system and the engine control system, and display the real-time status of the communication; CAN transceiver information display module: used to display the original instructions received from the engine control system and the original instructions sent by the simulated flight control system to the CAN bus; Flight control command setting and display module: used to set the simulated flight control commands, including editing, setting and displaying ignition and shutdown commands; Engine status display module: used to parse the CAN commands transmitted by the engine control system in real time and display the parsing results as the working status of the engine; Hardware device operation module: used to directly operate the CAN hardware module, shut down or start the CAN hardware module.

[0024] Preferably, the engine mathematical model used in the engine digital simulator system adopts a one-dimensional rapid evaluation model based on the influence coefficient method, the simulator hardware system is designed using an embedded hardware circuit, and finally the engine's one-dimensional mathematical model program is burned onto the embedded hardware platform to form an engine digital simulator system.

[0025] Preferably, the host computer management system communicates with the engine simulator through RS422 / 485 serial port to monitor the real-time parameters of the engine simulator and to burn the program and modify the parameters; The host computer management system and the engine controller communicate via serial ports to achieve the modification of the engine control program, the display and recording of sensor test data, and the monitoring of the engine status; The host computer management system and the flight control simulation system communicate via TCP / IP to achieve remote monitoring and control of the flight control system.

[0026] Preferably, the engine fuel supply system comprises a fuel pump, a motor, a high temperature fuel shut-off valve, a flow meter and pipeline components. The fuel pump is the core component of the engine's fuel supply system. As the power element of the entire fuel supply system, it is located at the source of the fuel supply system. The fuel pump pressurizes the fuel and connects the fuel to the high-temperature fuel shut-off valve through the fuel pipeline. The high-temperature fuel shut-off valve is located downstream of the fuel supply system and controls whether the fuel is injected into the engine. The motor is the power source of the fuel pump and is connected to the fuel pump through a coupling. The motor converts electrical energy into rotational mechanical energy and drives the fuel pump to rotate through the coupling. The flow meter is located at the outlet of the fuel pump and is used to measure the fuel flow entering the engine in real time and feed back the electrical signal to the controller of the engine control system through serial communication.

[0027] Preferably, the engine control system comprises a controller, a collector, a temperature sensor, a pressure sensor and a power supply component; The controller is the core component of the engine control system. The controller interacts with the collector to collect data through RS422 / 485 serial communication. The collector uploads the collected data to the controller in real time, and the controller further uploads it to the host computer through the bus protocol. The controller and the collector are placed at the test site, the temperature sensor is connected to the collector through a temperature compensation cable, the pressure sensor is connected to the collector through a shielded signal line, and the power supply component is connected to the controller and the pressure sensor through wires to supply power to the entire control system. The various components of the control system are integrated on the operating table at the test site.

[0028] Preferably, the engine fuel supply system and the engine control system within the fuel supply control system transmit signals via RS422 / 485 serial communication, and power the motor via a DC power cable.

[0029] Preferably, the host computer management system is connected to the simulator system and the fuel supply control system via RS422 / 485 serial ports, and is connected to the flight control system via a TCP / IP bus.

[0030] like Figure 2As shown in the figure, the flight control simulation system and the fuel supply and control system exchange commands and data in real time through CAN communication. The physical quantities simulated by the sensor simulation system are acquired in real time by the collector and sensor in the fuel supply and control system. The fuel supply and control system transmits valve information and fuel flow information to the engine simulator through digital signals and analog signals respectively. The simulator calculates the output state of the engine and transmits it to the sensor simulation system through analog quantities. The host computer management system monitors the status of each subsystem in the entire system.

[0031] The flight control simulation system sends the control instructions of the flight control computer to the engine controller to realize the start and stop of the engine and the conversion of the working state; the engine control system sends the aircraft attitude, altitude, Mach number, fuel pump flow and valve state to the engine simulator through serial communication as the input parameters of the simulator system; under the stimulation of the input parameters, the engine simulator completes the calculation of the engine state parameters and outputs the calculation results to its interface circuit; the sensor simulation device converts the signal from the simulator into a signal type and range that can be recognized by the engine control, and sends the engine state parameters to the control system after conditioning.

[0032] The flight control simulation system is designed in ground tests to simulate the flight control system of an aircraft or missile during flight. It mainly implements the issuance of engine control commands and the reception and information exchange of engine status parameters. Only when the flight control system issues corresponding instructions to the engine can the engine start and switch to the working state. The flight control simulation system exchanges data with the engine in real time and continuously adjusts the control parameters.

[0033] The engine digital simulator calculates the engine state parameters such as temperature and pressure signals, but these signals are digital signals, not real physical quantities. Some sensors, such as temperature sensors, are difficult to integrate with real sensors and apply real physical effects, so they are generally simulated by sensor simulation devices. The sensor simulation system is for sensors that cannot participate in the test due to conditions, such as temperature, pressure, vibration and other sensors. According to the output value of the engine model calculation, it uses signal simulation to provide analog input to the electronic controller, thereby completing the signal conversion from the simulator to the controller. The signal output by the simulator is a digital signal. First, it should be converted into a standard 0-5V analog signal through D / A conversion, and then converted into a signal with the same output type and range of the pressure sensor and temperature sensor through an amplification circuit. This signal can be collected by the collector.

[0034] like Figure 3As shown in the figure, the host computer management system mainly consists of two parts: the host computer and the monitoring video display. The host computer monitors the status of the flight control simulation system through the switch, and the host computer monitors the working status of the engine controller and the engine simulator through the serial port device. The camera is arranged at the test site and then the video is uploaded to the monitoring video display screen through the Ethernet of the switch.

[0035] The host management system is composed of a host computer, communication interface (CAN, RS422), parameter display and control module, video display and adaptation software, which realizes the data monitoring, parameter adjustment and control functions of the entire engine semi-physical simulation platform. The relationship between the host management system and other subsystems is as follows Figure 3 shown.

[0036] The above embodiments are merely illustrative of the principles and effects of the present invention, and are not intended to limit the present invention. Anyone familiar with the art may modify or alter the above embodiments without departing from the spirit and scope of the present invention. Therefore, all equivalent modifications or alterations made by a person of ordinary skill in the art without departing from the spirit and technical ideas disclosed by the present invention shall still be covered by the claims of the present invention.

Claims

1. A semi-physical simulation test platform for a scramjet engine control system, characterized by: Including fuel supply control system, flight control simulation system, simulator system, sensor simulation system and host computer management system, in: Fuel supply control system: divided into engine fuel supply system and engine control system, used to supply fuel to scramjet engine, adjust fuel supply flow rate and control fuel supply opening and closing status in real time as well as control functions of the whole working process of engine. Engine control system sends aircraft attitude, altitude, Mach number, fuel pump flow rate and valve status to simulator system through serial communication as input parameters of simulator system; engine fuel supply system and engine control system transmit signals through serial communication and power motor through power cable; fuel supply control system transmits signals with external flight control simulation system through CAN bus communication, connects with external host computer management system through TCP / IP communication, and connects with sensor simulation device in the form of simulated electrical signals; Flight control simulation system: used to simulate the aircraft controller and the information exchange between the flight control computer and the engine controller during flight. The flight control simulation system sends the control instructions of the flight control computer to the engine control system to realize the start and stop of the engine and the conversion of the working state. The flight control simulation system is connected to the engine control system through the CAN bus, and transmits data with the host computer management system through the TCP / IP bus. Simulator system: used to simulate the real-time working state of the scramjet engine. Under the stimulation of the input parameters of the engine control system, the simulator system completes the calculation of the engine state parameters and outputs the calculation results in its interface circuit; it transmits information about fuel flow and valve opening and closing between it and the engine control system through analog electrical signals and digital electrical signals, and transmits temperature and pressure values ​​between the simulator system and the sensor simulation system through analog current; Sensor simulation system: used to simulate the real combustion chamber air pressure, pipeline oil pressure, combustion chamber temperature and pipeline oil temperature physical quantities. The sensor simulation system and the simulator system transmit information through simulated electrical signals. The sensor simulation system converts the signal from the simulator system into a signal type and range that can be recognized by the engine control system, and sends the engine state parameters to the engine control system after conditioning. The sensor simulation system and the fuel supply control system are connected in the form of simulated electrical signals; Host computer management system: used to monitor the status of each system during the entire semi-physical simulation process. It is connected to the simulator system and the fuel supply control system through a serial port, and is connected to the flight control system through a TCP / IP bus.

2. The semi-physical simulation test platform for the scramjet engine control system according to claim 1 is characterized by: The flight control simulation system includes a flight control computer, a CAN communication module and flight control software; Flight control computer: used to simulate the entire flight process, send ignition, shutdown, and fuel target flow commands to the engine, receive and process engine status feedback information, and is the hardware carrier attached to the flight control system; CAN communication module: used for CAN communication with the engine controller to realize data and information transmission functions. It is connected to the flight control computer through the USB bus and to the engine controller through the CAN bus; Flight control simulation software: runs in real time in the flight control computer, including flight logic and data processing.

3. The semi-physical simulation test platform of the scramjet engine control system according to claim 2 is characterized by: The flight control simulation system software consists of CAN communication parameter configuration and status display module, CAN transceiver information display module, flight control command setting and display module, engine status display module and hardware equipment operation module; CAN communication parameter configuration and status display module: used to configure the CAN communication protocol between the simulated flight control system and the engine control system, and display the real-time status of the communication; CAN transceiver information display module: used to display the original instructions received from the engine control system and the original instructions sent by the simulated flight control system to the CAN bus; Flight control command setting and display module: used to set the simulated flight control commands, including editing, setting and displaying ignition and shutdown commands; Engine status display module: used to parse the CAN commands transmitted by the engine control system in real time and display the parsing results as the working status of the engine; Hardware device operation module: used to directly operate the CAN hardware module, shut down or start the CAN hardware module.

4. The semi-physical simulation test platform for the scramjet engine control system according to claim 1 is characterized by: The engine mathematical model used in the engine digital simulator system adopts a one-dimensional rapid evaluation model based on the influence coefficient method. The simulator hardware system is designed using embedded hardware circuits. Finally, the engine's one-dimensional mathematical model program is burned onto the embedded hardware platform to form an engine digital simulator system.

5. The semi-physical simulation test platform for the scramjet engine control system according to claim 1 is characterized in that: The host computer management system communicates with the engine simulator through the RS422 / 485 serial port to monitor the real-time parameters of the engine simulator, burn the program, and modify the parameters; The host computer management system and the engine controller communicate via serial ports to achieve the modification of the engine control program, the display and recording of sensor test data, and the monitoring of the engine status; The host computer management system and the flight control simulation system communicate via TCP / IP to achieve remote monitoring and control of the flight control system.

6. The semi-physical simulation test platform for the scramjet engine control system according to claim 1 is characterized by: The engine fuel supply system includes a fuel pump, a motor, a high-temperature fuel shut-off valve, a flow meter and pipeline components. The fuel pump is the core component of the engine's fuel supply system. As the power element of the entire fuel supply system, it is located at the source of the fuel supply system. The fuel pump pressurizes the fuel and connects the fuel to the high-temperature fuel shut-off valve through the fuel pipeline. The high-temperature fuel shut-off valve is located downstream of the fuel supply system and controls whether the fuel is injected into the engine. The motor is the power source of the fuel pump and is connected to the fuel pump through a coupling. The motor converts electrical energy into rotational mechanical energy and drives the fuel pump to rotate through the coupling. The flow meter is located at the outlet of the fuel pump and is used to measure the fuel flow entering the engine in real time and feed back the electrical signal to the controller of the engine control system through serial communication.

7. The semi-physical simulation test platform for the scramjet engine control system according to claim 1 is characterized by: The engine control system includes a controller, a collector, a temperature sensor, a pressure sensor and a power supply component; The controller is the core component of the engine control system. The controller interacts with the collector to collect data through RS422 / 485 serial communication. The collector uploads the collected data to the controller in real time, and the controller further uploads it to the host computer through the bus protocol. The controller and the collector are placed at the test site, the temperature sensor is connected to the collector through a temperature compensation cable, the pressure sensor is connected to the collector through a shielded signal line, the power supply component is connected to the controller and the pressure sensor through wires to supply power to the entire control system. The various components of the control system are integrated on the operating table at the test site.

8. The semi-physical simulation test platform for the scramjet engine control system according to claim 1 is characterized by: The engine fuel supply system and engine control system inside the fuel supply control system transmit signals through RS422 / 485 serial communication and power the motor through a DC power cable.

9. The semi-physical simulation test platform for the scramjet engine control system according to claim 1 is characterized by: The host computer management system is connected to the simulator system and fuel supply control system through RS422 / 485 serial ports, and is connected to the flight control system through TCP / IP bus.

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