A scramjet ground test measurement and control system

Abstract

The present invention belongs to the technical field of scramjet engine control, and specifically is a scramjet engine ground test measurement and control system, including an integrated controller, a data collector, a sensor, a motor controller, an electric fuel pump and a fuel valve. In the scramjet engine ground test, according to the engine state parameters such as engine temperature and pressure measured in real time by the data collector, the integrated controller of DSP+FPGA embedded architecture performs high-speed online calculation and real-time control of the actuators (electric fuel pump and fuel valve) in the engine measurement and control system, realizing the functions of ignition, flameout, fuel addition / reduction, state monitoring and fault handling of the scramjet engine. The measurement and control system uses switch signals and CAN bus to realize real-time and reliable information interaction with the wind tunnel control system and the flight control debugging system during the engine operation process, ensuring the stable and reliable operation of the scramjet engine in the ground test and giving full play to its performance benefits.

Description

Technical Field

[0001] The present invention belongs to the technical field of scramjet engine control, and more specifically, relates to a scramjet engine ground test measurement and control system with full authority digital electronic control technology as its core. Background Art

[0002] As a power device for hypersonic vehicles, scramjet engines have the characteristics of high specific impulse under flight conditions above Mach 6, which has obvious advantages over other power cycles. Therefore, scramjet engines have become one of the core technologies of hypersonic vehicles, and the research on various mechanisms and application technologies of scramjet engines has become a hot topic in recent years.

[0003] The measurement and control system of the scramjet engine is an important link in the process of the scramjet engine's transition from early theoretical research to engineering application. It is the brain, nerves and perception system of the scramjet engine. It mainly realizes the engine's real-time control, status monitoring, fault handling and communication functions, ensuring the engine's stable and reliable operation under external changing conditions and giving full play to the engine's performance benefits.

[0004] After decades of theoretical research at home and abroad, the basic principles of scramjet engines have been basically understood. In recent years, scramjet engines have gradually moved towards engineering applications. There is a lack of literature and patents on scramjet engine measurement and control systems at home and abroad, and the technology of scramjet engine measurement and control systems is still immature. Different from traditional aircraft engines, scramjet engines have higher requirements for their measurement and control systems due to their special working environment and state, which are mainly reflected in: (1) Gas passes through the combustion chamber at supersonic speed and reacts chemically with fuel, with a residence time of milliseconds, which means that the engine test system and control system have sufficient response speed and performance. For the control system, it is necessary to make real-time feedback adjustments to the engine's working state and handle various abnormal working conditions that the engine may encounter (such as inlet failure to start, overtemperature, overpressure, abnormal flameout, etc.), which requires the control system to have high computing efficiency, control accuracy and real-time processing capabilities. For the test system, the sensor should have sufficient frequency response and quickly capture the transient characteristics of the engine, and the collector should have a sufficiently high sampling frequency. (2) Scramjet engines require many variables to be monitored, and the transmission rate and stability of the measurement and control system are high, and data packet loss cannot occur. (3) Due to its changeable and severe operating environment, the scramjet engine measurement and control system is required to work stably and reliably, and have good anti-interference capabilities. (4) The engine ground test measurement and control system has the ability to interact with the wind tunnel system, and can cooperate with the flight control debugging system in the ground test to simulate the entire engine's actual flight workflow. Summary of the invention

[0005] In view of the defects of the prior art, the present invention provides a measurement and control system suitable for ground testing of scramjet engines and meets the special use requirements of scramjet engines.

[0006] To achieve the above-mentioned purpose of the invention, the technical solution of the present invention is as follows:

[0007] A scramjet ground test measurement and control system adopts an overall integrated design. In addition to a remote host computer, the measurement and control subsystems are integrated into an integrated engine measurement and control platform. The entire platform is hoisted and moved as a whole through a hook and a base. During the test, the platform is located in the wind tunnel test section or its periphery, and interacts online with the wind tunnel control system and the flight control debugging system.

[0008] The engine ground test control subsystem includes an integrated controller, data acquisition device, sensor, motor controller, electric fuel pump and fuel valve:

[0009] Integrated controller: used to send flow instructions to the electric fuel pump, control the opening and closing logic of the fuel valve, exchange information with the wind tunnel control system, exchange information with the flight control debugging system, process the data uploaded by the collector in real time, identify the working status of the engine, and perform protection control;

[0010] The data collector includes a pressure collector and a temperature collector: During the ground test of the scramjet engine, the physical quantities that need to be monitored by the engine itself include pressure and temperature. The pressure collector is used to collect the oil pressure and air pressure during the engine test. The temperature collector is used to collect the oil temperature and wall temperature data. It is electrically connected to the integrated controller and uploads the engine working status data to the integrated controller in real time. The data collector is integrated around the engine and uploads the digital signal to the integrated controller. The temperature collector has a built-in temperature sensor to perform cold end compensation on the thermocouple.

[0011] The sensor includes a pressure sensor and a temperature sensor: the pressure sensor is used to convert the oil pressure in the pipeline or the air pressure in the combustion chamber into a standard voltage value, which is then supplied to the pressure collector for collection. On the one hand, the pressure sensing component of the pressure sensor is connected to the fuel pipeline or the combustion chamber through a pressure pipe, and on the other hand, it is connected to the data collector through an analog electrical signal. The pressure sensor is installed near the engine body; the temperature sensor uses an armored thermocouple to feed back the potential difference between the temperature measurement point and the reference point to the temperature collector. The temperature sensor is arranged inside the engine flow channel to reflect the temperature of the engine;

[0012] Motor controller: used to control the speed of three-phase AC asynchronous motors by frequency conversion control, and monitor the speed, current, and shaft temperature of the motors. On the one hand, the motor controller exchanges instructions with the integrated controller, including controlling the start and stop of the motor, the motor speed, the motor temperature, and the current. On the other hand, the motor controller is connected to the motor through a power cable. The motor controller is installed on the integrated measurement and control platform.

[0013] Electric fuel pump: used to provide the engine with fuel of a certain flow rate and pressure, converting the mechanical energy of the motor into liquid kinetic energy and potential energy. The electric fuel pump is connected to the fuel valve through a pipeline, and the electric fuel pump is connected to the motor controller through a cable. The electric fuel pump is installed on the integrated measurement and control platform;

[0014] Fuel valve: used to control the on and off of fuel, whether to inject fuel into the engine combustion chamber. The integrated controller controls the opening and closing of the fuel valve through a DC signal. The fuel valve is installed around the engine.

[0015] The ground measurement and control system of the scramjet engine is centered on the integrated controller. The integrated controller exchanges data with the data acquisition device. The data of some acquisition channels participate in the calculation to realize the closed-loop control of the system, and other acquisition channels continuously collect data to evaluate the engine performance. The integrated controller outputs digital signals to control the fuel valve. The integrated controller outputs control signals to the motor controller, which controls the speed of the fuel pump motor, and the motor controller obtains key information of the fuel supply system. Information is transmitted between the integrated controller and the host computer through Ethernet. Digital signals are transmitted between the integrated controller and the wind tunnel control system. The integrated controller exchanges data with the flight control debugging system and transmits commands.

[0016] As a preferred method, the engine measurement and control system has a communication function to communicate with the host computer, wind tunnel control system, flight control debugging system, motor controller, and data acquisition device for command and data transmission;

[0017] The integrated controller and the host computer use Ethernet communication, and are designed with two network ports, which have the same functions and can back up each other.

[0018] Digital quantity is used as command signal between the integrated controller and the wind tunnel system to indicate wind tunnel start-up, wind tunnel stop and engine emergency stop;

[0019] The integrated controller outputs an analog signal to the electric fuel pump to control the fuel flow rate;

[0020] The integrated controller outputs a switch signal to the fuel valve for opening and closing control.

[0021] As a preferred method, the integrated controller and the data collector use RS485 serial communication; the integrated controller and the motor controller use RS422 serial communication; the integrated controller and the flight control debugging system use CAN communication.

[0022] As a preferred method, grounding and multi-layer shielding are used in the measurement and control system circuit to reduce electric field interference, magnetic field interference and electromagnetic field interference.

[0023] As a preferred method, the integrated controller is connected to the fuel valve via a 28V power DO, exchanges commands with the motor controller via RS422 serial port communication, exchanges commands with the wind tunnel control system via digital DI / DO, exchanges information with the flight control debugging system via CAN bus, and exchanges commands with the data collector via RS485 serial port communication; the integrated controller is installed on the integrated measurement and control platform.

[0024] As a preferred method, the data collector only uploads the digital signal of the engine working status to the integrated controller via the RS485 bus.

[0025] As a preferred mode, the motor controller exchanges instructions with the integrated controller via the RS422 bus on the one hand, and is connected to the motor via a power cable on the other hand.

[0026] As a preferred embodiment, the electric fuel pump is connected to the motor controller via a 380V three-phase cable.

[0027] As a preferred embodiment, the integrated controller controls the opening and closing of the fuel valve via a 28V DC signal.

[0028] As a preferred method, online interactive commands are exchanged between the engine ground test measurement and control system and the wind tunnel system, as well as between the engine and the flight control debugging system, to simulate the entire workflow of the engine in the air during the ground test.

[0029] The measurement and control cabinet is equipped with an on-site host computer and display screen, which can be operated and displayed on-site or switched to remote control.

[0030] The measurement and control system consists of an integrated controller, a collector, a communication component, a pressure sensor, a motor controller, etc. The integrated controller and the pressure / temperature collector exchange data in real time. The integrated controller is self-developed using the DSP+FPGA embedded architecture. This mode combines the programmability and ease of use of DSP with the high performance of FPGA, with high real-time performance, and is suitable for relatively complex data processing and logic control fields such as scramjet engines.

[0031] The temperature collector is a special data collector used to measure temperature. It is used to connect K-type thermocouples to collect temperature control signals and temperature monitoring signals. The instrument has built-in platinum resistance temperature compensation.

[0032] The pressure collector is a special data collector used to measure pressure, and is used to collect pressure control signals and pressure monitoring signals. The engine measurement and control system is equipped with a pressure control signal collector, which collects pressure signals to the integrated controller and participates in algorithm processing for system control. The engine measurement and control system is equipped with temperature monitoring signal acquisition, which collects temperature signals to the integrated controller and stores them for engine test performance evaluation. The measurement and control system is equipped with pressure monitoring signal acquisition, and the pressure signals are transmitted to the integrated controller and stored for engine experimental performance evaluation. The measurement and control system is equipped with a measurement and control system host computer and control system analysis software to realize parameter setting, system debugging, offline data recovery and other functions. The measurement and control system is equipped with an AO channel, provides power DO output, built-in relay isolation, and provides DI channels and DO channels.

[0033] Passive switch quantity is used between the integrated controller and the wind tunnel system as command signals for ramjet engine preparation, ignition, emergency stop command, emergency stop request, etc. The integrated controller outputs analog signals to the electric fuel pump for fuel flow control. The integrated controller outputs switch signals to the fuel valve for on-off control.

[0034] Scramjet engines face severe and changeable working environments. Reasonable grounding and multi-layer shielding are used in the measurement and control system circuit to effectively reduce electric field interference, magnetic field interference and electromagnetic field interference. The use of effective isolation technology ensures a high degree of isolation between input and output, effectively suppresses the transmission of interference, and the measurement and control system has good anti-interference ability, which is suitable for use in industrial environments.

[0035] The integrated controller of the present invention adopts the self-developed DSP+FPGA embedded architecture, and the system has high real-time performance, fast response speed, and high computing efficiency. It is suitable for large amounts of data processing and complex logic control in the ground test of scramjet engines, and ensures real-time feedback control of the engine. The present invention takes into account the working environment of the measurement and control system, fully considers stability, adaptability, safety, security, and maintainability, and meets the requirements of long-term stable, safe and reliable use. The measurement and control system has undergone severe environmental tests of temperature, humidity and vibration. According to the amount of data transmitted between different devices, the requirements of real-time performance and the communication characteristics, the present invention selects reliable and most suitable communication protocols between different devices. The entire measurement and control system has fast data transmission speed, reasonable transmission distance and high reliability. The present invention adopts a reasonable grounding design and uses multi-layer shielding to effectively suppress electric field interference, magnetic field interference and electromagnetic field interference, and the measurement and control system has good anti-interference ability. In addition, the scramjet ground test measurement and control system interacts online with the flight control debugging system and the wind tunnel control system, and can simulate the actual working process of the engine in the sky during the ground test. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Figure 1The figure is a block diagram of the measurement and control system of the scramjet engine of the present invention.

[0037] Figure 2 The communication block diagram of the scramjet engine ground test of the present invention is shown.

[0038] Figure 3 This is a block diagram of the hardware composition principle of the integrated controller in the measurement and control system of the present invention. DETAILED DESCRIPTION

[0039] 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.

[0040] A scramjet ground test measurement and control system adopts an overall integrated design. In addition to a remote host computer, the measurement and control subsystems are integrated into an integrated engine measurement and control platform. The entire platform is hoisted and moved as a whole through a hook and a base. During the test, the platform is located in the wind tunnel test section or its periphery, and interacts online with the wind tunnel control system and the flight control debugging system.

[0041] The engine ground test control subsystem includes an integrated controller, data acquisition device, sensor, motor controller, electric fuel pump and fuel valve:

[0042] Integrated controller: used to send flow instructions to the electric fuel pump, control the opening and closing logic of the fuel valve, exchange information with the wind tunnel control system, exchange information with the flight control debugging system, process the data uploaded by the collector in real time, identify the working status of the engine, and perform protection control;

[0043] The data collector includes a pressure collector and a temperature collector: During the ground test of the scramjet engine, the physical quantities that need to be monitored by the engine itself include pressure and temperature. The pressure collector is used to collect the oil pressure and air pressure during the engine test. The temperature collector is used to collect the oil temperature and wall temperature data. It is electrically connected to the integrated controller and uploads the engine working status data to the integrated controller in real time. The data collector is integrated around the engine and uploads the digital signal to the integrated controller. The temperature collector has a built-in temperature sensor to perform cold end compensation on the thermocouple.

[0044] The sensor includes a pressure sensor and a temperature sensor: the pressure sensor is used to convert the oil pressure in the pipeline or the air pressure in the combustion chamber into a standard voltage value, which is then supplied to the pressure collector for collection. On the one hand, the pressure sensing component of the pressure sensor is connected to the fuel pipeline or the combustion chamber through a pressure pipe, and on the other hand, it is connected to the data collector through an analog electrical signal. The pressure sensor is installed near the engine body; the temperature sensor uses an armored thermocouple to feed back the potential difference between the temperature measurement point and the reference point to the temperature collector. The temperature sensor is arranged inside the engine flow channel to reflect the temperature of the engine;

[0045] Motor controller: used to control the speed of three-phase AC asynchronous motors by frequency conversion control, and monitor the speed, current, and shaft temperature of the motors. On the one hand, the motor controller exchanges instructions with the integrated controller, including controlling the start and stop of the motor, the motor speed, the motor temperature, and the current. On the other hand, the motor controller is connected to the motor through a power cable. The motor controller is installed on the integrated measurement and control platform.

[0046] Electric fuel pump: used to provide the engine with fuel of a certain flow rate and pressure, converting the mechanical energy of the motor into liquid kinetic energy and potential energy. The electric fuel pump is connected to the fuel valve through a pipeline, and the electric fuel pump is connected to the motor controller through a cable. The electric fuel pump is installed on the integrated measurement and control platform;

[0047] Fuel valve: used to control the on and off of fuel, whether to inject fuel into the engine combustion chamber. The integrated controller controls the opening and closing of the fuel valve through a DC signal. The fuel valve is installed around the engine.

[0048] The ground measurement and control system of the scramjet engine is centered on the integrated controller. The integrated controller exchanges data with the data acquisition device. The data of some acquisition channels participate in the calculation to realize the closed-loop control of the system, and other acquisition channels continuously collect data to evaluate the engine performance. The integrated controller outputs digital signals to control the fuel valve. The integrated controller outputs control signals to the motor controller, which controls the speed of the fuel pump motor, and the motor controller obtains key information of the fuel supply system. Information is transmitted between the integrated controller and the host computer through Ethernet. Digital signals are transmitted between the integrated controller and the wind tunnel control system. The integrated controller exchanges data with the flight control debugging system and transmits commands.

[0049] The engine measurement and control system has a communication function, which can transmit commands and data with the host computer, wind tunnel control system, flight control debugging system, motor controller, and data acquisition device;

[0050] The integrated controller and the host computer use Ethernet communication, and are designed with two network ports, which have the same functions and can back up each other.

[0051] Digital quantity is used as the command signal between the integrated controller and the wind tunnel system;

[0052] The integrated controller outputs an analog signal to the electric fuel pump to control the fuel flow rate;

[0053] The integrated controller outputs a switch signal to the fuel valve for opening and closing control.

[0054] The integrated controller and the data collector use RS485 serial port communication; the integrated controller and the motor controller use RS422 serial port communication; the integrated controller and the flight control debugging system use CAN communication.

[0055] Grounding and multi-layer shielding are used in the measurement and control system circuit to reduce electric field interference, magnetic field interference and electromagnetic field interference.

[0056] The integrated controller is connected to the fuel valve via a 28V power DO, exchanges commands with the motor controller via RS422 serial port communication, exchanges commands with the wind tunnel control system via digital DI / DO, exchanges information with the flight control debugging system via CAN bus, and exchanges commands with the data collector via RS485 serial port communication; the integrated controller is installed on the integrated measurement and control platform.

[0057] The data collector is connected to the integrated controller via the RS485 bus, and the engine operating status data is uploaded to the integrated controller in real time. The data collector only uploads the digital signal to the integrated controller via the RS485 bus.

[0058] The motor controller exchanges instructions with the integrated controller via the RS422 bus on the one hand, and is connected to the motor via a power cable on the other hand.

[0059] The electric fuel pump is connected to the motor controller via a 380V three-phase cable.

[0060] The integrated controller controls the opening and closing of the fuel valve through a 28V DC signal.

[0061] The online interactive commands between the engine ground test measurement and control system and the wind tunnel system, as well as the online interactive commands between the engine and the flight control debugging system, simulate the entire work flow of the engine in the sky during the ground test.

[0062] like Figure 1As shown. The engine measurement and control system is equipped with an integrated controller, which is connected to the temperature and pressure signal collector and has interfaces such as CAN communication, multi-channel RS422 communication, power supply, Ethernet, and programming. The engine measurement and control system is equipped with a temperature control signal collector, which collects temperature signals to the integrated controller and participates in algorithm processing for system control. RS485 communication is used between the integrated controller and the pressure / temperature collector, and the star connection mode is adopted. The data of some acquisition channels need to participate in the calculation to realize the closed-loop control of the system, and other acquisition channels continuously collect data to evaluate the engine operation performance. The integrated controller outputs DO switch quantity to control the fuel valve. The integrated controller outputs 4-20mA analog quantity to the motor controller, controls the speed of the fuel pump motor through the motor controller, and uses RS422 communication with the motor controller to obtain key information of the fuel supply system. Ethernet communication is adopted between the integrated controller and the host computer. DI / O switch quantity communication control is adopted between the integrated controller and the wind tunnel control system. The integrated controller has a CAN communication interface for exchanging data with the flight control system.

[0063] In the communication system, commands and data are transmitted with the host computer, wind tunnel control system, flight control debugging system, motor controller, collector, etc. Figure 2 As shown. Ethernet communication is adopted between the integrated controller and the host computer. Two network ports are designed, with the same functions as backup for each other. Passive switch quantity is used as the command signal between the integrated controller and the wind tunnel system. The integrated controller outputs 4-20mA current analog signal to the electric fuel pump for fuel flow control. The integrated controller outputs 28V switch signal to the fuel valve for opening and closing control. The integrated controller and the collector use RS485 serial port communication. RS422 serial port communication is adopted between the integrated controller and the motor controller. CAN communication is adopted between the integrated controller and the flight control debugging system. Figure 2 The signal types and connection methods between the various components of the scramjet engine ground test control system are explained more concisely. The integrated controller exchanges wind tunnel start-up, stop-down and engine emergency stop commands with the wind tunnel control system through DI / DO. The integrated controller uploads test data and working status information to the host computer through Ethernet. The integrated controller exchanges motor fuel pump flow commands and motor status data with the motor control through the RS422 bus. The integrated controller controls the opening and closing state of the fuel valve through power DO. The integrated controller and the collector obtain engine detection data through RS485.

[0064] The integrated controller is designed with DSP+FPGA embedded architecture. The hardware composition and principle are as follows: Figure 3As shown. The functional modules include Flash memory, RAM memory, program burning serial port, power processing module, BIT self-test circuit, serial port circuit, DI and DO, etc. The electrical connection between the chip and the circuit module is printed by PCB. DSP and FPGA are the core components of the integrated controller. Flash memory and RAM memory are connected to the corresponding pins through the chip reserved interface. The power processing module reduces the voltage of the external 28V DC power supply through the power chip to form a voltage range suitable for chip power supply to power the chip. The functions of other hardware modules are similar. Dedicated chips or special circuits are selected to realize module functions, and then they are connected through the reserved pins of DSP and FPGA chips. Data is exchanged bidirectionally between the memory and the chip. The external program is burned into the chip through the serial port. The host computer exchanges data with the controller chip through the Ethernet interface, and the BIT circuit transmits the detection signal to the chip.

[0065] This mode combines the programmability of DSP with the high performance of FPGA, with high real-time performance. It is suitable for relatively complex data processing and logic control fields such as scramjet engines, and can realize stable and reliable timing control of the engine, provide long-term and accurate dynamic fuel supply for the engine, and other functions. With Flash memory, the system can be disconnected from the computer and controlled by the wind tunnel control system. After the collector is powered on, sampling is carried out, and the DI / O switch signal given by the wind tunnel control system is given to the integrated controller. After algorithm processing, the fuel pump and fuel valve are controlled. During the working process, the parameters of the control system, the engine flow control program, the collected data, the control status information, etc. need to be stored in the Flash. The measurement and control system has a BIT self-test system, which is used to detect the working status of the integrated controller and return the self-test results to the software platform through the Ethernet interface. Three types of BIT self-tests are realized after the system is powered on, before the engine works, and during the engine works, to test the correctness of the system hardware functions and locate the faults. BIT self-test is only carried out under specified conditions and does not affect the normal operation of the controller.

[0066] 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 scramjet ground test measurement and control system, characterized by: The overall integrated design is adopted. In addition to the remote host computer, the measurement and control subsystems are integrated into an integrated engine measurement and control platform. The entire platform is hoisted and moved as a whole through the hook and the base. During the test, the platform is located in the wind tunnel test section or its surroundings, and interacts online with the wind tunnel control system and the flight control debugging system. The engine ground test control subsystem includes an integrated controller, data acquisition device, sensor, motor controller, electric fuel pump and fuel valve: Integrated controller: used to send flow instructions to the electric fuel pump, control the opening and closing logic of the fuel valve, exchange information with the wind tunnel control system, exchange information with the flight control debugging system, process the data uploaded by the collector in real time, identify the working status of the engine, and perform protection control; The data collector includes a pressure collector and a temperature collector: During the ground test of the scramjet engine, the physical quantities that need to be monitored by the engine itself include pressure and temperature. The pressure collector is used to collect the oil pressure and air pressure during the engine test. The temperature collector is used to collect the oil temperature and wall temperature data. It is electrically connected to the integrated controller and uploads the engine working status data to the integrated controller in real time. The data collector is integrated around the engine and uploads the digital signal to the integrated controller. The temperature collector has a built-in temperature sensor to perform cold end compensation on the thermocouple. The sensor includes a pressure sensor and a temperature sensor: the pressure sensor is used to convert the oil pressure in the pipeline or the air pressure in the combustion chamber into a standard voltage value, which is then supplied to the pressure collector for collection. On the one hand, the pressure sensing component of the pressure sensor is connected to the fuel pipeline or the combustion chamber through a pressure pipe, and on the other hand, it is connected to the data collector through an analog electrical signal. The pressure sensor is installed near the engine body; the temperature sensor uses an armored thermocouple to feed back the potential difference between the temperature measurement point and the reference point to the temperature collector. The temperature sensor is arranged inside the engine flow channel to reflect the temperature of the engine; Motor controller: used to control the speed of three-phase AC asynchronous motors by frequency conversion control, and monitor the speed, current, and shaft temperature of the motors. On the one hand, the motor controller exchanges instructions with the integrated controller, including controlling the start and stop of the motor, the motor speed, the motor temperature, and the current. On the other hand, the motor controller is connected to the motor through a power cable. The motor controller is installed on the integrated measurement and control platform. Electric fuel pump: used to provide fuel for the engine, converting the mechanical energy of the motor into liquid kinetic energy and potential energy. The electric fuel pump is connected to the fuel valve through a pipeline, and the electric fuel pump is connected to the motor controller through a cable. The electric fuel pump is installed on the integrated measurement and control platform; Fuel valve: used to control the on and off of fuel, whether to inject fuel into the engine combustion chamber. The integrated controller controls the opening and closing of the fuel valve through a DC signal. The fuel valve is installed around the engine. The ground measurement and control system of the scramjet engine is centered on the integrated controller. The integrated controller exchanges data with the data acquisition device. The data of some acquisition channels participate in the calculation to realize the closed-loop control of the system, and other acquisition channels continuously collect data to evaluate the engine performance. The integrated controller outputs digital signals to control the fuel valve. The integrated controller outputs control signals to the motor controller, which controls the speed of the fuel pump motor, and the motor controller obtains key information of the fuel supply system. Information is transmitted between the integrated controller and the host computer through Ethernet. Digital signals are transmitted between the integrated controller and the wind tunnel control system. The integrated controller exchanges data with the flight control debugging system and transmits commands.

2. The scramjet engine ground test measurement and control system according to claim 1, characterized in that: The engine measurement and control system has a communication function, which can transmit commands and data with the host computer, wind tunnel control system, flight control debugging system, motor controller, and data acquisition device; The integrated controller and the host computer use Ethernet communication, and are designed with two network ports, which have the same functions and can back up each other. Digital quantity is used as command signal between the integrated controller and the wind tunnel system to indicate wind tunnel start-up, wind tunnel stop and engine emergency stop; The integrated controller outputs an analog signal to the electric fuel pump to control the fuel flow rate; The integrated controller outputs a switch signal to the fuel valve for opening and closing control.

3. The scramjet engine ground test measurement and control system according to claim 1, characterized in that: The integrated controller and the data collector use RS485 serial port communication; the integrated controller and the motor controller use RS422 serial port communication; the integrated controller and the flight control debugging system use CAN communication.

4. The scramjet engine ground test measurement and control system according to claim 1, characterized in that: Grounding and multi-layer shielding are used in the measurement and control system circuit to reduce electric field interference, magnetic field interference and electromagnetic field interference.

5. The scramjet engine ground test measurement and control system according to claim 1, characterized in that: The integrated controller is connected to the fuel valve via a 28V power DO, exchanges commands with the motor controller via RS422 serial port communication, exchanges commands with the wind tunnel control system via digital DI / DO, exchanges information with the flight control debugging system via CAN bus, and exchanges commands with the data collector via RS485 serial port communication; the integrated controller is installed on the integrated measurement and control platform.

6. The scramjet engine ground test measurement and control system according to claim 1, characterized in that: The data collector only uploads the digital signal of the engine working status to the integrated controller via the RS485 bus.

7. The scramjet engine ground test measurement and control system according to claim 1, characterized in that: The motor controller exchanges instructions with the integrated controller via the RS422 bus on the one hand, and is connected to the motor via a power cable on the other hand.

8. The scramjet engine ground test measurement and control system according to claim 1, characterized in that: The electric fuel pump is connected to the motor controller via a 380V three-phase cable.

9. The scramjet engine ground test measurement and control system according to claim 1, characterized in that: The integrated controller controls the opening and closing of the fuel valve through a 28V DC signal.

10. The scramjet engine ground test measurement and control system according to claim 1, characterized in that: The online interactive commands between the engine ground test measurement and control system and the wind tunnel system, as well as the online interactive commands between the engine and the flight control debugging system, simulate the entire work flow of the engine in the sky during the ground test.

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