Small turbojet engine simulation test system

Abstract

The invention discloses a small turbojet engine simulation test system, which comprises an engine controller, an integrated engine simulation device and an avionics system or an upper computer, and is characterized in that the integrated engine simulation device is connected with the engine controller and the avionics system or the upper computer through matched cables; the engine controller is used for receiving a control signal of the avionics system or the upper computer, feeding back the working state of an engine, issuing a driving signal of an engine executing mechanism and receiving a sensor output signal; the integrated engine simulation device is used for simulating signals of all execution mechanisms and sensors of an engine and displaying the state and detailed parameters of the engine. The method is suitable for the infield and outfield joint debugging stage and the model flight stage of small turbojet engines for unmanned aerial vehicles and missiles and the debugging process of engine control equipment.

Description

Technical Field

[0001] This invention relates to the field of turbojet engine technology, and in particular to a small turbojet engine simulation test system. Background Technology

[0002] A certain type of small turbojet engine is a crucial power core for weapons and equipment such as UAVs and loitering munitions. During the control system integration and flight simulation phases, it is necessary to conduct extensive tests on the control effects of flight control and engine control equipment on the engine, including controllers and actuators, during flight simulation, hardware-in-the-loop (HIL) testing, and engine control equipment debugging. Simulating the engine system's sensors and actuators in a reasonable manner during testing, replacing the real engine system, and visually representing the engine's operating status is an important way to verify the execution of controller commands during flight simulation, HIL testing, and engine control equipment debugging. Currently, this type of small turbojet engine is mainly tested through software simulation. The simulation accuracy is low, and the engine model is a black box model, which cannot visually reflect the operating status of the engine's actuators, seriously affecting the overall system simulation test results. Summary of the Invention

[0003] To address the problems existing in the prior art, the purpose of this invention is to provide a small turbojet engine simulation test system. This invention is applicable to the indoor and outdoor joint debugging phase, simulated flight phase, and engine control equipment debugging process of small turbojet engines for UAVs and missiles.

[0004] To achieve the above objectives, the technical solution adopted by the present invention is: a small turbojet engine simulation test system, comprising: an engine controller, an integrated engine simulation device, and an avionics system or host computer. The integrated engine simulation device is connected to the engine controller and the avionics system or host computer via matching cables. The engine controller is used to receive control signals from the avionics system or host computer, provide feedback on the engine operating status, issue drive signals for engine actuators, and receive sensor output signals. The integrated engine simulation device is used to simulate the signals of various engine actuators and sensors, and display the engine status and detailed parameters.

[0005] As a further improvement of the present invention, the integrated engine simulation device specifically includes a signal generation module, a core processing module, a motor assembly, and a power supply module for power supply. The signal generation module includes a frequency signal generation module, a voltage signal generation module, and a high-precision potentiometer. The frequency signal generation module is used to generate frequency signals to simulate engine speed, the voltage signal generation module is used to generate voltage signals to simulate fuel pressure and lubricating oil pressure, and the high-precision potentiometer is used to generate resistance signals to simulate intake air temperature and exhaust air temperature. The core processing module is used to perform signal processing. The core processing module receives RS422 signals from the avionics system or the host computer, controls the signal generation module to adjust the output voltage, resistance, and output timing, drives the actuator, and realizes that the signal generation module and the actuator automatically output according to the timing sequence to complete the simulation of the engine start-up process. The motor assembly is used to simulate the engine fuel system.

[0006] As a further improvement of the present invention, the frequency output range of the frequency signal generation module is 0~100Hz, the voltage output range of the voltage signal generation module is 0~5VDC, and the output range of the resistance signal generated by the high-precision potentiometer is 0~10KΩ.

[0007] As a further improvement of the present invention, the actuator is an operation panel, specifically including an indicator light panel and a display panel. The indicator light panel is used to intuitively display the engine accessory switch status and time, and the display panel is used to accurately display the accessory status.

[0008] As a further improvement of the present invention, the engine accessory switch status and timing include: equipment power supply, throttle action, throttle 0°, throttle 230° igniter, booster pump, fuel solenoid valve, vent solenoid valve, oxygen injection solenoid valve, and starter solenoid valve. Knobs and buttons are used to issue engine commands and adjust engine speed status, including: throttle travel check, igniter signal check, fuel solenoid valve check, engine start command, engine stop command, 50% speed, 75% speed, and 90% speed.

[0009] As a further improvement of the present invention, the accessory status includes engine speed, intake air temperature, exhaust air temperature, fuel pressure, lubricating oil pressure, voltage, current and running time.

[0010] The beneficial effects of this invention are:

[0011] This invention addresses the shortcomings of existing field engine simulation software, which cannot intuitively reflect the working status of engine actuators and support dynamic engine testing under simulated flight conditions. It proposes a design scheme for a small turbojet engine simulation testing system. By designing a simulation testing system (including an engine controller, integrated engine simulation equipment, and supporting cables), a system capable of simulating a specific type of turbojet engine is constructed. This system enables simulation testing of the fuel system and control system of a small turbojet engine under simulated flight, hardware-in-the-loop simulation, and engine control equipment debugging conditions. It is a highly integrated and high-precision engine simulation testing device specifically designed to meet user needs. Attached Figure Description

[0012] Figure 1 This is a schematic diagram of the structure of the simulation test system in an embodiment of the present invention;

[0013] Figure 2 This is a schematic diagram of the integrated engine simulation device in an embodiment of the present invention;

[0014] Figure 3 This is a circuit schematic diagram of the signal generation module in an embodiment of the present invention;

[0015] Figure 4 This is a schematic diagram of the operation panel in an embodiment of the present invention. Detailed Implementation

[0016] The embodiments of the present invention will now be described in detail with reference to the accompanying drawings.

[0017] Example 1

[0018] like Figure 1 As shown, a small turbojet engine simulation test system consists of an engine controller, an integrated engine simulation device, and supporting cables. The engine controller receives control signals from the avionics system or host computer, provides feedback on the engine's operating status, sends drive signals to the engine actuators, and receives sensor output signals. The integrated engine simulation device simulates the signals from various engine actuators and sensors, and displays the engine status and detailed parameters. The supporting cables connect the engine controller to the avionics system, host computer, and integrated engine simulation device.

[0019] like Figure 2As shown, the integrated engine simulation equipment consists of a power supply module, a signal generation module, a core processing module, an operation panel, and a motor assembly. The signal generation module includes a frequency signal generation module, a voltage signal generation module, and a high-precision potentiometer. The frequency signal generation module generates frequency signals to simulate engine speed, the voltage signal generation module generates voltage signals to simulate fuel pressure and lubricating oil pressure, and the high-precision potentiometer generates resistance signals to simulate intake and exhaust temperatures. The core processing module performs signal processing. It receives RS422 signals and controls the signal generation module to adjust the output voltage, resistance, and output timing, driving the indicator lights and motor assembly, enabling the signal generation module and actuators to automatically output signals according to the timing sequence, thus simulating the engine starting process.

[0020] like Figure 3 As shown, the engine speed is simulated by a frequency signal generation circuit with a frequency output range of 0~100Hz; the pressure sensor output signal is simulated by a voltage regulation circuit with a voltage output range of 0~5VDC; and the temperature sensor output signal is simulated by a digital potentiometer circuit with a resistance output range of 0~10KΩ.

[0021] like Figure 4 As shown, the control panel consists of an indicator light panel and a display panel. The indicator lights are used to visually display the status and time of engine accessory switches, including: power supply, throttle action, throttle 0°, throttle 230°, igniter, booster pump, fuel solenoid valve, ventilation solenoid valve, oxygen injection solenoid valve, and starter solenoid valve. Knobs and buttons are used to issue engine commands and adjust engine speed, including: "throttle travel check", "igniter signal check", "fuel solenoid valve check", "engine start command", "engine stop command", "50% speed", "75% speed", "90% speed", etc. The display is used to accurately display accessory status, including: engine speed, intake air temperature, exhaust air temperature, fuel pressure, lubricating oil pressure, voltage, current, and running time.

[0022] Example 2

[0023] The technical problem to be solved in this embodiment is to construct a small turbojet engine simulation test system to replace existing engine simulation software. By designing integrated engine simulation equipment, it simulates environmental conditions, engine status, and engine actuator actions, and displays the status of the engine actuators. Furthermore, it forms a simulation test system with a specific engine controller and matching cables, capable of completely simulating a specific turbojet engine model, completing semi-physical simulation tests and engine control equipment debugging, and performing non-ignition dynamic tests of the entire installed engine system during field flight simulations to verify the normality of the flight control system and host computer's control over the engine. This invention is applicable to the indoor and outdoor joint debugging phases, flight simulation phases, and engine control equipment debugging processes of small turbojet engines for UAVs and missiles.

[0024] This embodiment is implemented as follows: a small turbojet engine simulation test system includes:

[0025] 1) When the small turbojet engine simulation test system is working, the flight controller or host computer sends control signals to the engine controller of a certain model via the RS422 communication interface. The controller outputs actuator drive signals to the integrated engine simulation equipment according to the embedded software preset program, and receives sensor signals output by the engine simulation equipment. Based on the collected sensor information, it comprehensively judges the engine operating status. Specifically, the integrated engine simulation equipment's signal generation module simulates engine environmental conditions, pressure sensor output, flow sensor output, and speed sensor output. The core processing module can automatically simulate various types of sensor signals in sequence. The operation panel allows manual adjustment of the signal generation module and observation of the actuator and engine operating status. The motor combination module can realistically simulate the engine fuel supply mechanism.

[0026] 2) By designing the speed signal simulation circuit, temperature signal simulation circuit and pressure signal simulation circuit of the signal generation module, parameters such as engine speed, intake air temperature, exhaust air temperature, fuel pressure and lubricating oil pressure are simulated respectively. The output of the signal generation module can be adjusted by knob, button and host computer program.

[0027] 3) Engine status parameters are displayed through the indicator light module and display module on the control panel. The indicator lights are used to visually display the status and time of engine accessory switches, including: equipment power, throttle action, throttle 0°, throttle 230°, igniter, boost pump, fuel solenoid valve, ventilation solenoid valve, oxygen injection solenoid valve, and starter solenoid valve. The display module is used to accurately display the accessory status, including: engine speed, intake air temperature, exhaust air temperature, fuel pressure, lubricating oil pressure, voltage, current, and running time.

[0028] 4) The core processing module is the core functional module of the small turbojet engine simulation test system. It is designed with an STM32 microcontroller as the core and realizes all preset functions by designing power supply circuits, RS422 communication circuits, filtering circuits, isolation drive circuits, etc.

[0029] 5) The high-precision digital potentiometer, voltage module, and motor combination realistically simulate the working states of various engine systems. The high-precision digital potentiometer is used to simulate temperature-related signal output, the voltage module is used to simulate pressure-related signal output, and the motor combination is used to simulate engine fuel system signal output.

[0030] Example 3

[0031] A small turbojet engine simulation test system comprises an engine controller of a certain model, an integrated engine simulation device, and matching cables. The integrated engine simulation device includes a power supply module, a signal generation module, a core processing module, an operation panel, and a motor assembly. By operating the integrated engine simulation device, environmental conditions, engine status, and engine actuator actions are simulated, and the status of the engine actuators is displayed. This system enables the completion of non-ignition dynamic testing of the entire engine system during simulated flight, hardware-in-the-loop (HIL) testing, and engine control equipment debugging.

[0032] During the operation of the simulation test system, the signal generation module mainly includes: speed signal simulation circuit, temperature signal simulation circuit, and pressure signal simulation circuit, which can simulate parameters such as engine speed, intake air temperature, exhaust air temperature, fuel pressure, and lubricating oil pressure. The circuit parameters can be adjusted by the knobs and key switches on the operation panel, or by the core processing module controlling the output of the signal generation module according to the preset timing sequence through the host computer program, simulating the sensor output signals of the entire engine operation process.

[0033] During the operation of the simulation test system, the status of the engine's main actuators is displayed through indicator light modules and a display screen, which are mounted on the control panel. The indicator light modules are used to display whether the engine is operating normally or abnormally, whether the controller communication is normal or abnormal, and the status of the actuators; the display screen module is used to display parameters such as engine speed, intake air temperature, exhaust air temperature, fuel pressure, lubricating oil pressure, voltage, and current.

[0034] During the operation of the simulation test system, the engine fuel system simulation is achieved through the motor combination. The output of the motor combination includes: throttle 0° signal, throttle 230° signal and throttle action signal, which can control the on and off of the corresponding indicator lights. The throttle action lever is equipped with a throttle action indicator, which can intuitively show whether the throttle is activated or not.

[0035] The embodiments described above are merely illustrative of specific implementations of the present invention, and while the descriptions are detailed, they should not be construed as limiting the scope of the present invention. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these modifications and improvements all fall within the scope of protection of the present invention.

Claims

1. A small turbojet engine simulation test system, characterized in that, include: The system includes an engine controller, an integrated engine simulation device, and an avionics system or host computer. The integrated engine simulation device is connected to the engine controller and the avionics system or host computer via matching cables. The engine controller receives control signals from the avionics system or host computer, provides feedback on the engine's operating status, sends drive signals to the engine's actuators, and receives sensor output signals. The integrated engine simulation device simulates the signals from the engine's various actuators and sensors, and displays the engine's status and detailed parameters.

2. The small turbojet engine simulation test system according to claim 1, characterized in that, The integrated engine simulation equipment specifically includes a signal generation module, a core processing module, a motor assembly, and a power supply module. The signal generation module comprises a frequency signal generation module, a voltage signal generation module, and a high-precision potentiometer. The frequency signal generation module generates frequency signals to simulate engine speed, the voltage signal generation module generates voltage signals to simulate fuel pressure and lubricating oil pressure, and the high-precision potentiometer generates resistance signals to simulate intake and exhaust temperatures. The core processing module performs signal processing, receiving RS422 signals from the avionics system or host computer, and controlling the signal generation module to adjust the output voltage, resistance, and output timing to drive the actuator, enabling the signal generation module and actuator to automatically output according to the timing sequence, thus simulating the engine start-up process. The motor assembly simulates the engine fuel system.

3. The small turbojet engine simulation test system according to claim 2, characterized in that, The frequency output range of the frequency signal generation module is 0~100Hz, the voltage output range of the voltage signal generation module is 0~5VDC, and the output range of the resistance signal generated by the high-precision potentiometer is 0~10KΩ.

4. The small turbojet engine simulation test system according to claim 2, characterized in that, The actuator is an operation panel, specifically including an indicator light panel and a display panel. The indicator light panel is used to visually display the engine accessory switch status and time, and the display panel is used to accurately display the accessory status.

5. The small turbojet engine simulation test system according to claim 4, characterized in that, Engine accessory switch status and timing include: equipment power supply, throttle action, throttle 0°, throttle 230°, igniter, booster pump, fuel solenoid valve, vent solenoid valve, oxygen injection solenoid valve, and starter solenoid valve. Knobs and buttons are used to issue engine commands and adjust engine speed status, including: throttle travel check, igniter signal check, fuel solenoid valve check, engine start command, engine stop command, 50% rev range, 75% rev range, and 90% rev range.

6. The small turbojet engine simulation test system according to claim 4, characterized in that, Accessory status includes engine speed, intake air temperature, exhaust air temperature, fuel pressure, lubricating oil pressure, voltage, current, and running time.

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