An aircraft fuel system semi-physical simulation test system and method
By employing hardware-in-the-loop simulation testing methods, combined with equipment such as capacitor simulation boxes to simulate the electrical characteristics of fuel system sensors, the safety and efficiency issues of aircraft fuel system controller verification were resolved, enabling efficient system-level verification and iteration.
Patent Information
- Application Number
- CN202610924511.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2026-06-25
- Publication Date
- 2026-08-25
AI Technical Summary
Existing technologies cannot accurately reflect the electrical characteristics and real-time response performance of aircraft fuel system controllers. Furthermore, the construction of a full physical verification test bench is time-consuming and costly, and cannot be synchronized with the development and iteration of controller hardware.
The hardware-in-the-loop simulation test method is adopted. The controlled object model of the fuel system is run through a real-time processor, and the controller under test is connected to the I/O interface to simulate the state of the fuel system. The electrical characteristics of the sensors are simulated by using a capacitor simulation box, a resistor simulation card, and a density meter simulation card to form a closed-loop test.
It enables system-level verification in a laboratory environment, improves the safety and iterative efficiency of fuel system R&D testing, avoids safety risks of real fuel and high-pressure actuators, and shortens the test preparation cycle.
Smart Images
Figure CN122632653A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of aircraft fuel system simulation testing technology, specifically to a semi-physical simulation testing system and method for aircraft fuel systems. Background Technology
[0002] The main functions of an aircraft fuel system controller include fuel quantity measurement, fuel system equipment status monitoring, and issuing fuel loading / discharging control commands. When validating a fuel system controller, pure software simulation methods are insufficient to accurately reflect the electrical characteristics and real-time response performance of the controller hardware. Furthermore, the construction of a full physical verification test bench is time-consuming and costly, often failing to keep pace with the controller hardware's research and development iterations. Therefore, a hardware-in-the-loop (HIL) simulation testing method is needed. A real-time processor runs a simulation model to simulate the state of the controlled object, and the system is verified by connecting the controller under test via I / O interfaces. Summary of the Invention
[0003] To improve the safety of aircraft fuel system R&D and testing processes, reduce test bench construction costs, and enhance the efficiency of controller software and hardware R&D and testing iterations, this application provides a semi-physical simulation test system and method for aircraft fuel systems to avoid using real fuel tanks and fuel for fuel measurement and control system testing. This aims to improve the safety of aircraft fuel system R&D and testing processes and enhance the efficiency of software and hardware R&D and testing iterations.
[0004] This application provides the following technical solution: a semi-physical simulation test system for an aircraft fuel system, comprising:
[0005] The host computer is used to simulate the aircraft's avionics system, sending and receiving ARINC429 signals and hardwired signals. The real-time simulator is connected to the host computer and is used to run the controlled object model of the fuel system to simulate the real aircraft fuel system and calculate the simulated fuel tank state simulation signal and the sensor simulation signal in the fuel system in real time. The lower-level machine is communicatively connected to the upper-level machine and the real-time simulator, and the lower-level machine includes a reflective memory board, a communication board, and an analog quantity board. The fuel controller is electrically connected to the communication board and analog signal board of the lower-level machine; The real-time simulator sends the calculated digital simulation signal to the reflective memory board of the lower-level machine. After the upper-level machine reads the data from the reflective memory board of the lower-level machine, it converts the digital simulation signal into a control command for driving the signal simulation device according to a preset mapping relationship, and sends the control command to the analog signal board of the lower-level machine. The digital simulation signal is then converted into a physical signal simulating the electrical characteristics of a real sensor in real time through the analog signal board or the signal simulation device connected to the analog signal board, and output to the fuel controller. The fuel controller is used to calculate the fuel quantity based on the preset calculation logic of the received physical signal and the bus signal forwarded by the communication board, and output control commands to the communication board of the lower computer based on the calculation result. The lower-level machine is used to transmit the received control commands to the upper-level machine for display, and at the same time transmit them back to the real-time simulator via the reflective memory board, so that the real-time simulator updates the simulation calculation of the controlled object model according to the transmitted control commands, thus forming a closed-loop test.
[0006] According to one embodiment of this application, the host computer includes a system virtual integration test platform and a fuel test system integrated management platform; The system virtual integration test platform is used to realize functions such as calling lower-level computer boards, bus signal packaging / unpacking, signal value input, signal recording, automated test script execution, and test result analysis. The integrated management platform for the fuel testing system is used to realize functions such as displaying a simplified diagram of the fuel system, displaying alarm status, simulating the fuel control panel in the cockpit, inputting fuel quantity in the simulation model, switching wiring, simulating power supply, and injecting faults.
[0007] According to one embodiment of this application, the controlled object model running in the real-time simulator includes a fuel quantity calculation module, a fuel pump simulation module, a shut-off valve simulation module, a fuel supply pipeline simulation module, a fuel filling and discharging module, a capacitor calculation module, and a fault injection module.
[0008] According to one embodiment of this application, the signal simulation device includes a capacitance simulation box, a resistance simulation card, and a density meter simulation card; it converts the simulated digital signal into a physical signal that simulates the electrical characteristics of a real sensor in real time, including: outputting the capacitance value of a simulated oil level sensor through the capacitance simulation box, outputting the resistance value of a simulated temperature sensor through the resistance simulation card, and outputting the frequency value of a simulated density meter through the density meter simulation card.
[0009] This application also provides a semi-physical simulation test method for an aircraft fuel system, including the following steps: S1. Start the host computer and the real-time simulator, initialize the slave computer through the host computer, set the configuration of the real or simulated component of the controller under test, set the test environment initialization parameters, and run the controlled object model in the real-time simulator. S2. The real-time simulator runs the controlled object model to simulate the aircraft refueling, fuel consumption and fuel transfer process, and calculates the digital fuel tank status simulation signal and the sensor simulation signal in the fuel system in real time, and sends them to the lower computer's reflection memory board through the reflection memory board of the real-time simulator. S3. The host computer reads the data in the reflection memory board of the slave computer, converts the digital simulation signal into a control command for driving the signal simulation device according to the preset mapping relationship, and sends the control command to the analog board of the slave computer. Through the signal simulation device connected to the analog board, the digital simulation signal is converted into a physical signal that simulates the electrical characteristics of the real sensor in real time. At the same time, the host computer sends the bus signal of the simulated avionics system to the communication board of the slave computer. S4. The fuel controller receives the physical signal and the bus signal, calculates the fuel quantity according to the preset calculation logic, and outputs control commands to the communication board of the lower-level machine according to the calculation results. S5. The lower-level machine transmits the control command to the upper-level machine for display, and simultaneously transmits it back to the real-time simulator via the reflective memory board. The real-time simulator updates the simulation calculation of the controlled object model according to the transmitted control command, forming a closed-loop test.
[0010] According to one embodiment of this application, in step S1, the test environment initialization parameters include: aircraft engine operating signal, aircraft flap angle, aircraft wheel load signal, flight attitude angle, fuel density, fuel temperature, fuel mass of each fuel tank, fuel pump start / stop status, shut-off valve switch status, and engine fuel consumption.
[0011] According to one embodiment of this application, in step S1, setting the configuration of the real or simulated controller under test includes: according to the test requirements, switching the target terminal of the lower-level machine's board signal output, using a Simulink model to replace one or more real fuel controller devices, and realizing individual testing of a specific real controller.
[0012] According to one embodiment of this application, in step S2, the simulation of aircraft refueling, fuel consumption and fuel transfer process includes: based on the fuel supply pipeline simulation module, fuel addition and dispensing module and fuel quantity calculation module in the controlled object model, realizing the increase and decrease of fuel quantity in the fuel tank and the fuel transfer between different fuel tanks, and calculating the fuel quality in each fuel tank in real time.
[0013] According to one embodiment of this application, in step S2, the digital simulation signals of the fuel tank status and the sensor simulation signals in the fuel system are calculated in real time, including: calculating the fuel volume based on the fuel mass and fuel density; based on the fuel volume, and according to the pre-input flight attitude angle and fuel surface slice database, calculating the fuel volume and the fuel immersion height of each sensor at the flight attitude angle using an interpolation algorithm; and based on the sensor fuel immersion height, calculating the capacitance value, resistance value, or frequency value according to a preset sensor model.
[0014] Compared with existing technologies, the beneficial effects achieved by at least one of the above-mentioned technical solutions adopted in the embodiments of this specification include at least the following: The embodiments of this invention introduce a hardware-in-the-loop simulation testing method. This method uses a real-time processor to run a model of the controlled object, simulating the actual state of the fuel system, and connects to the actual controller under test via an I / O interface, thereby achieving system-level verification in a laboratory environment. Specifically, the embodiments of this invention simulate changes in the fuel tank level and the immersion depth, temperature, and density characteristics of the sensors within the fuel tank using model simulation. Simultaneously, capacitor boards, resistor boards, and frequency boards are used to simulate the electrical characteristics of the fuel sensor, temperature sensor, and density sensor, respectively. Therefore, the debugging and testing of the controller can be carried out without building a physical test environment containing a real fuel tank, sensors, and actuators. The system consists of a host computer, a real-time simulator, a slave computer, and a fuel controller, realizing a complete process from simulation modeling and signal simulation to controller closed-loop verification. Furthermore, since the use of real fuel and high-pressure actuators is avoided, the entire testing process eliminates safety risks such as fuel leakage, fire, or mechanical damage, significantly improving the safety of aircraft fuel system research and development and testing. The semi-physical simulation environment is easy to reconfigure and adjust parameters, and can keep pace with the development rhythm of controller software and hardware, greatly shortening the test preparation cycle and thus improving the iterative efficiency of overall R&D testing. Attached Figure Description
[0015] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0016] Figure 1 This is a schematic diagram of a semi-physical simulation test system architecture for an aircraft fuel system according to an embodiment of the present invention. Detailed Implementation
[0017] The embodiments of this application will now be described in detail with reference to the accompanying drawings.
[0018] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. This application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this application. It should be noted that, in the absence of conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.
[0019] This invention provides a semi-physical simulation test system for aircraft fuel systems. This system uses a real-time simulator to run a fuel system model, simulating changes in fuel quantity within the fuel tank and the immersion height of various devices in the fuel, thus replacing the use of a real fuel tank in the test. A capacitance simulation box, a resistance simulation card, and a density meter simulation card are used to simulate the electrical characteristics of fuel quantity sensors, temperature sensors, and density meters, thereby avoiding the use of real sensors, fuel tanks, and actuators in the experiment. This system includes the following hardware devices: The host computer is used to simulate the aircraft's avionics system. It sends ARINC429 signals and hardwired signals to the lower-level computer and the real-time simulator, receives ARINC429 signals and hardwired signals from the fuel controller collected by the lower-level computer, and records and visualizes the above signals. In addition, the host computer software is also responsible for data interaction between the signal acquisition board and the reflection memory board in the lower-level computer.
[0020] A real-time simulator, communicating with the host computer, is used to run the controlled object model of the fuel system to simulate the real aircraft fuel system and to calculate the simulated fuel tank state signals and sensor signals in the fuel system in real time. Specifically, the controlled object model is built using Simulink and is used to simulate the changes in fuel quantity, density, and temperature in the fuel tank. It can also simulate the immersion height of equipment in the fuel and resolve the signals from fuel sensors, densitometers, and thermometers. Furthermore, it can simulate the operation of each device in the entire fuel system and output the feedback signals from the corresponding sensors and valve opening / closing signals. Data transmission with the host computer is conducted via TCP / IP protocol, and data transmission with the lower-level computer's reflected memory is conducted via optical fiber.
[0021] The lower-level computer is communicatively connected to both the upper-level computer and the real-time simulator. The lower-level computer includes a reflective memory board, a communication board, and an analog quantity board. Specifically, the lower-level computer sends signals from the upper-level computer to the fuel controller via the communication board, and receives sensor simulation signals and status simulation signals from the real-time simulator via the reflective memory board. These signals include resistance, capacitance, voltage, frequency, and switching signals. After being read by the upper-level computer software, these signals are sent to the lower-level computer's analog quantity board, relays, capacitor banks, and other devices to convert the digital signals into real physical quantities, simulating the electrical characteristics of a real aircraft, such as the capacitance of a fuel sensor, the resistance of a temperature sensor, and the frequency of a densitometer.
[0022] The fuel controller is a real airborne fuel system controller, electrically connected to the communication board and analog signal board of the lower-level machine; it includes a fuel measurement and management computer, a fuel remote data concentrator, and a fuel filling and discharging control panel. It receives physical signals from the signal simulation equipment and bus signals sent by the lower-level machine communication board. After software calculation, it issues status information such as fuel quantity and instruction information such as switch signals, which are fed back to the lower-level machine communication board. Under certain circumstances, one or more controllers can be simulated using a simulation model.
[0023] The real-time simulator sends the calculated digital simulation signal to the reflective memory board of the lower-level machine. After the upper-level machine reads the data from the reflective memory board of the lower-level machine, it converts the digital simulation signal into a control command for driving the signal simulation device according to a preset mapping relationship, and sends the control command to the analog signal board of the lower-level machine. The analog signal board, or the signal simulation device connected to the analog signal board, converts the digital simulation signal into a physical signal simulating the electrical characteristics of a real sensor in real time and outputs it to the fuel controller. The fuel controller calculates the fuel quantity according to a preset calculation logic based on the received physical signal and the bus signal forwarded by the communication board, and outputs a control command to the communication board of the lower-level machine based on the calculation result. The lower-level machine transmits the received control command to the upper-level machine for display, and simultaneously sends it back to the real-time simulator via the reflective memory board, so that the real-time simulator updates the simulation calculation of the controlled object model according to the returned control command, forming a closed-loop test.
[0024] In specific implementation, such as Figure 1 As shown in the figure, the semi-physical simulation test system for an aircraft fuel system in this embodiment mainly consists of four core parts: a host computer, a real-time simulator, a slave computer, and a fuel controller.
[0025] The host computer, specifically a high-performance industrial control computer, serves as the management and monitoring center for the entire testing system. It runs two core software programs: a system virtual integration test platform and a fuel testing system integrated management platform. The system virtual integration test platform is primarily responsible for underlying hardware scheduling and data processing, such as calling slave computer boards, packing and unpacking ARINC429 bus signals, forcibly inputting and recording signal values, and executing automated test scripts and analyzing test results. The fuel testing system integrated management platform provides a visual operating interface, including a fuel system diagram page, an alarm list, and a soft panel simulation of the cockpit fuel control panel. It can also perform initial fuel quantity settings for the simulation model, signal wiring switching, controller power supply control, and fault injection.
[0026] The real-time simulator is the core computing unit of the system, typically employing a high-real-time platform such as PXI or CompactRIO. Internally, it runs a fuel system controlled object model built using Simulink. This model includes at least a fuel quantity calculation module, a fuel pump simulation module, a shut-off valve simulation module, a fuel supply line simulation module, a fuel filling / draining module, a capacitor calculation module, and a fault injection module. The real-time simulator interacts with the host computer via TCP / IP protocol for non-real-time data exchange (e.g., downloading the model, uploading monitoring data), while simultaneously connecting with the slave computer via fiber optic cable, utilizing a reflective memory board for high-speed real-time data exchange with microsecond-level latency to ensure the real-time performance of closed-loop control.
[0027] The real-time simulator can calculate the changes in fuel quantity in the fuel tank, the immersion depth of each device in the fuel tank, and the working status of each device in real time based on factors such as engine fuel extraction volume, refueling pressure, and the status of the refueling solenoid valve. It can also calculate the capacitance value of the fuel sensor, the resistance value of the temperature sensor, and the frequency value of the hydrometer in real time. Furthermore, it can set different fault modes for the fuel system equipment to simulate the state characteristics and system performance under fault conditions.
[0028] The lower-level machine acts as a hub for converting physical signals to digital signals. It communicates with the fuel controller via a bus through communication boards (such as ARINC429, CAN, or discrete I / O boards). The lower-level machine receives digital signals from sensors (such as capacitance, resistance, and frequency values) from the real-time simulator. Then, through internal analog boards, it controls external capacitor simulation boxes (outputting pF-level adjustable capacitors), resistance simulation cards (outputting variable resistance), and densitometer simulation cards (outputting variable frequency pulses). The capacitor simulation box outputs the capacitance value of a simulated fuel level sensor, the resistance simulation card outputs the resistance value of a simulated temperature sensor, and the densitometer simulation card outputs the frequency value of a simulated densitometer, converting these digital quantities into real physical electrical characteristics. Simultaneously, it can also simulate the electrical characteristics of inductive loads such as refueling solenoid valves and drain valves using load simulation devices such as power resistors and inductors.
[0029] The fuel controller is the object under test, including real onboard equipment such as a fuel measurement and management computer, a fuel remote data concentrator, and a fuel filling / draining control panel. The fuel controller collects analog sensor signals and bus signals from a lower-level computer, runs a real control algorithm, and outputs fuel quantity, alarm information, and valve / pump control commands. When testing a specific controller, a simulation model in a real-time simulator can be used to replace other controllers not being tested, through configuration on the upper-level computer, enabling flexible mixed testing of real and simulated components.
[0030] This application also provides a semi-physical simulation test method for an aircraft fuel system, including the following steps: Step S1: Experiment preparation and initialization.
[0031] Start the host computer and real-time simulator. Use the host computer's virtual system integration test platform to identify, self-test, and initialize all lower-level computer boards. In the fuel testing system's integrated management platform, set the configuration of the controller under test according to the test plan (e.g., only set the fuel measurement management computer as a real device, while using simulation models for other controllers). Simultaneously, set the initial test environment parameters, including: aircraft engine operating signals, aircraft flap angles, aircraft wheel load signals, flight attitude angles, fuel density, fuel temperature, fuel mass in each fuel tank, fuel pump start / stop status, shut-off valve on / off status, and engine fuel consumption. After completing the power distribution settings, start the controlled object model in the real-time simulator.
[0032] Step S2: Real-time simulation calculation and signal conversion.
[0033] The real-time simulator begins to run the model periodically, simulating the refueling process, fuel consumption process, and fuel transfer between the three fuel tanks in a real aircraft. It calculates fuel quantity sensor, pressure sensor, valve position information, fuel temperature, and fuel density information in real time, and sends them to the lower-level reflective memory board through the transmit memory. After being read by the upper-level system virtual integration platform, it is forwarded to the corresponding lower-level board to simulate capacitance, resistance, switching quantity, and frequency values. At the same time, other A429 bus information from the avionics system is packaged into the corresponding data format after being set by the upper-level fuel test system integrated management platform and sent directly to the lower-level communication board.
[0034] For example, simulating an aircraft engine consuming fuel at a rate of 200 kg / h, the fuel quantity calculation module and fuel supply pipeline simulation module in the model will calculate the reduction of fuel quantity in each fuel tank in real time. The capacitance calculation module calculates the fuel volume based on the current fuel mass and density in the fuel tank, and combines it with the current flight attitude angle (e.g., pitch +2°, roll 0°), queries a pre-generated fuel surface slice database, calculates the immersion height of each fuel sensor in the fuel tank through an interpolation algorithm, and then calculates the capacitance value based on the linear relationship between sensor capacitance and immersion height (the preset sensor model). This capacitance value is used as simulation data and sent to the lower-level computer's reflective memory board through reflective memory. After receiving this data, the lower-level computer controls the capacitance simulation box through its analog board to output a capacitance value of 85.6 pF on the corresponding output channel.
[0035] Step S3: Controller calculation.
[0036] After receiving physical signals and bus and hardwire signals from the lower-level machine, the fuel controller first calculates the fuel density and temperature based on the frequency signal fed back by the analog density meter and the resistance signal fed back by the analog thermometer. Then, it calculates the fuel quantity based on the fuel density, fuel temperature and the capacitance value fed back by the analog fuel sensor. Combining the bus signals from the avionics system and the test conditions, it outputs the bus signals and hardwire signals and sends them to the communication board of the lower-level machine.
[0037] For example, the fuel controller acquires an 85.6pF capacitance signal from the lower-level computer, a frequency signal output from the density meter simulation card, and a resistance signal output from the temperature sensor simulation card through its I / O interface. The controller's internal software first calculates the current fuel density and temperature based on the frequency and resistance values, and then uses a fuel quantity calculation algorithm, combined with the capacitance, density, and temperature, to calculate the current fuel quantity in the tank. Simultaneously, based on avionics bus signals simulated from the upper-level computer (such as a "refueling request"), the controller outputs a discrete command signal to "open the refueling valve."
[0038] Step S4: Closed-loop feedback.
[0039] The lower-level computer transmits the signals from the fuel controller to the upper-level computer, which displays the fuel quantity, fuel temperature, density, pump and valve on / off status, alarm information, etc. through a visual interface. It also sends control commands back to the lower-level computer's reflective memory board, and then sends them to the real-time simulator. The simulation model performs simulation calculations of the latest state in real time based on the input and outputs the simulation results, thus forming a closed-loop control test.
[0040] For example, when the lower-level computer's communication board captures the "open refueling valve" command output by the fuel controller, it immediately sends the command to the real-time simulator via the reflection memory board. Simultaneously, the command is uploaded to the upper-level computer, where the corresponding refueling valve icon changes from red to green on the upper-level computer's schematic page, indicating that the valve is open. Upon receiving the command, the real-time simulator's fuel addition / discharge module begins operation, calculating the amount of fuel to be added to the tank in the next simulation step, thus updating the simulated fuel quantity and forming a complete closed-loop control test.
[0041] By following the steps described above, the functionality and performance of the aircraft fuel system controller can be fully, safely, and efficiently verified without using real fuel or most of the real actuators.
[0042] This application discloses a semi-physical simulation test method and system for aircraft fuel systems. It simulates fuel tank level changes and the immersion height, temperature, and density characteristics of sensors within the fuel tank using a model. Furthermore, it simulates the electrical characteristics of fuel sensors, temperature sensors, and density sensors using capacitor boards, resistor boards, and frequency boards. This avoids the need for using actual fuel tanks, sensors, and actuators for controller debugging and testing, thus achieving semi-physical simulation testing of the fuel controller. The system consists of a host computer, a real-time simulator, a slave computer, and a fuel controller. This method improves the safety of the aircraft fuel system R&D and testing process and enhances the iteration efficiency of software and hardware R&D and testing.
[0043] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.
Claims
1. A semi-physical simulation test system for an aircraft fuel system, characterized in that, include: The host computer is used to simulate the aircraft's avionics system, sending and receiving ARINC429 signals and hardwired signals. The real-time simulator is connected to the host computer and is used to run the controlled object model of the fuel system to simulate the real aircraft fuel system and calculate the simulated fuel tank state simulation signal and the sensor simulation signal in the fuel system in real time. The lower-level machine is communicatively connected to the upper-level machine and the real-time simulator, and the lower-level machine includes a reflective memory board, a communication board, and an analog quantity board. The fuel controller is electrically connected to the communication board and analog signal board of the lower-level machine; The real-time simulator sends the calculated digital simulation signal to the reflective memory board of the lower-level machine. After the upper-level machine reads the data from the reflective memory board of the lower-level machine, it converts the digital simulation signal into a control command for driving the signal simulation device according to a preset mapping relationship, and sends the control command to the analog signal board of the lower-level machine. The digital simulation signal is then converted into a physical signal simulating the electrical characteristics of a real sensor in real time through the analog signal board or the signal simulation device connected to the analog signal board, and output to the fuel controller. The fuel controller is used to calculate the fuel quantity based on the preset calculation logic of the received physical signal and the bus signal forwarded by the communication board, and output control commands to the communication board of the lower computer based on the calculation result. The lower-level machine is used to transmit the received control commands to the upper-level machine for display, and at the same time transmit them back to the real-time simulator via the reflective memory board, so that the real-time simulator updates the simulation calculation of the controlled object model according to the transmitted control commands, thus forming a closed-loop test.
2. The semi-physical simulation test system for aircraft fuel systems according to claim 1, characterized in that, The host computer includes a system virtual integration test platform and a fuel test system comprehensive management platform; The system virtual integration test platform is used to realize functions such as calling lower-level computer boards, bus signal packaging / unpacking, signal value input, signal recording, automated test script execution, and test result analysis. The integrated management platform for the fuel testing system is used to realize functions such as displaying a simplified diagram of the fuel system, displaying alarm status, simulating the fuel control panel in the cockpit, inputting fuel quantity in the simulation model, switching wiring, simulating power supply, and injecting faults.
3. The semi-physical simulation test system for aircraft fuel systems according to claim 1, characterized in that, The controlled object model running in the real-time simulator includes a fuel quantity calculation module, a fuel pump simulation module, a shut-off valve simulation module, a fuel supply pipeline simulation module, a fuel filling and discharging module, a capacitor calculation module, and a fault injection module.
4. The semi-physical simulation test system for aircraft fuel systems according to claim 1, characterized in that, The signal simulation device includes a capacitance simulation box, a resistance simulation card, and a density meter simulation card; it converts digital simulation signals into physical signals that simulate the electrical characteristics of real sensors in real time, including: outputting the capacitance value of a simulated oil level sensor through the capacitance simulation box, outputting the resistance value of a simulated temperature sensor through the resistance simulation card, and outputting the frequency value of a simulated density meter through the density meter simulation card.
5. A semi-physical simulation test method for an aircraft fuel system, characterized in that, Includes the following steps: S1. Start the host computer and the real-time simulator, initialize the slave computer through the host computer, set the configuration of the real or simulated component of the controller under test, set the test environment initialization parameters, and run the controlled object model in the real-time simulator. S2. The real-time simulator runs the controlled object model to simulate the aircraft refueling, fuel consumption and fuel transfer process, and calculates the digital fuel tank status simulation signal and the sensor simulation signal in the fuel system in real time, and sends them to the lower computer's reflection memory board through the reflection memory board of the real-time simulator. S3. The host computer reads the data in the reflection memory board of the slave computer, converts the digital simulation signal into a control command for driving the signal simulation device according to the preset mapping relationship, and sends the control command to the analog board of the slave computer. Through the signal simulation device connected to the analog board, the digital simulation signal is converted into a physical signal that simulates the electrical characteristics of the real sensor in real time. At the same time, the host computer sends the bus signal of the simulated avionics system to the communication board of the slave computer. S4. The fuel controller receives the physical signal and the bus signal, calculates the fuel quantity according to the preset calculation logic, and outputs control commands to the communication board of the lower-level machine according to the calculation results. S5. The lower-level machine transmits the control command to the upper-level machine for display, and simultaneously transmits it back to the real-time simulator via the reflective memory board. The real-time simulator updates the simulation calculation of the controlled object model according to the transmitted control command, forming a closed-loop test.
6. The semi-physical simulation test method for aircraft fuel systems according to claim 5, characterized in that, In step S1, the test environment initialization parameters include: aircraft engine operating signal, aircraft flap angle, aircraft wheel load signal, flight attitude angle, fuel density, fuel temperature, fuel mass of each fuel tank, fuel pump start / stop status, shut-off valve switch status, and engine fuel consumption.
7. The semi-physical simulation test method for aircraft fuel systems according to claim 5, characterized in that, In step S1, the configuration of the actual or simulated controller under test is set, including: According to the testing requirements, the host computer is configured to use a simulation model to replace one or more real fuel controllers, so as to realize the individual testing of a specific real fuel controller.
8. The semi-physical simulation test method for aircraft fuel systems according to claim 5, characterized in that, Step S2 simulates the aircraft refueling, fuel consumption, and fuel transfer process, including: Based on the fuel supply pipeline simulation module, fuel addition / discharge module, and fuel quantity calculation module in the controlled object model, the fuel quantity in the fuel tank is increased or decreased, and fuel is transferred between different fuel tanks. The fuel quality in each fuel tank is calculated in real time.
9. The semi-physical simulation test method for aircraft fuel systems according to claim 5, characterized in that, In step S2, the digital simulation signals of the fuel tank status and the sensor simulation signals in the fuel system are calculated in real time, including: Calculate the fuel volume based on fuel mass and fuel density; Based on the fuel volume, and according to the pre-input flight attitude angle and fuel surface slice database, the fuel volume and the fuel immersion height of each sensor at the flight attitude angle are calculated by interpolation algorithm. Based on the oil immersion height of the sensor, the capacitance value, resistance value, or frequency value is calculated according to a preset sensor model.