Electronic control unit of aviation piston type engine

Abstract

The utility model discloses an electronic control unit of an aviation piston type engine. The electric control unit comprises a main control chip; the analog signal input unit is connected with the main control chip and is used for acquiring sensor data, and the sensor data comprises throttle percentage, air inlet temperature, engine rotating speed, cylinder head temperature and environment temperature; the switching value signal input unit is used for connecting an emergency switch; a storage unit; an ignition coil control unit; an oil injection control unit; a fuel pump control unit; a turbocharging control unit; a throttle valve steering engine control unit; a tachometer output unit; the pressure sensor unit is used for collecting atmospheric pressure; and the RS232 communication unit and the CAN communication unit are used for communication between the electric control unit and an upper computer. The electronic control unit not only controls oil injection and ignition of a transmitter, but also integrates the functions of controlling a throttle valve steering engine, a fuel pump and the like, so that the design and development cycle and cost of an aircraft can be effectively reduced, and the failure rate of aircraft equipment is reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to an electronic control unit of an aviation piston engine. Background Art

[0002] The function of the ordinary piston engine electronic control unit (ECU) is very simple. This ECU is only responsible for sending injection pulse width and ignition timing instructions to the injector and spark plug, without many other functions. However, in the application of drones, in order to increase the payload, the number and weight of various devices must be reduced and lightened. Therefore, it is necessary to provide a highly integrated aviation piston engine electronic control unit. At the same time, in order to reduce the aircraft design and development cycle and cost, and reduce the failure rate of aircraft equipment, it is also necessary to provide a highly integrated aviation piston engine electronic control unit. Utility Model Content

[0003] The utility model provides a highly integrated electronic control unit for an aviation piston engine, and provides the following technical solutions:

[0004] An electronic control unit for an aviation piston engine, comprising:

[0005] Main control chip;

[0006] An analog signal input unit for collecting external sensor data and sending it to the main control chip, wherein the sensor data includes throttle opening, intake air temperature, engine speed, cylinder head temperature and ambient temperature;

[0007] A switch signal input unit for connecting an emergency switch to the main control chip;

[0008] A storage unit connected to the main control chip;

[0009] An ignition coil control unit connected to the main control chip;

[0010] A fuel injection control unit connected to the main control chip;

[0011] A fuel pump control unit connected to the main control chip;

[0012] A turbocharger control unit connected to the main control chip;

[0013] A throttle servo control unit connected to the main control chip;

[0014] A tachometer output unit connected to the main control chip;

[0015] A pressure sensor unit connected to the main control chip and used to collect atmospheric pressure;

[0016] An RS232 communication unit and a CAN communication unit connected to the main control chip and used for the electronic control unit to communicate with the host computer; and

[0017] A power management unit is used to connect to an external power source, supply power to all units of the electronic control unit, and output power to supply power to external sensors.

[0018] Furthermore, the electronic control unit is powered by 12V and includes 4 ignition coil control units, 4 fuel injection control units, 1 throttle servo control unit, 1 turbocharger control unit and 1 tachometer output unit.

[0019] Furthermore, the main control chip adopts a processor with a 32-bit ARM processor as the processing core.

[0020] Furthermore, each ignition coil control unit includes an ignition coil control chip VBG08H with a built-in power-level IGBT driver.

[0021] Furthermore, the fuel injection control unit includes a high-side MOS driver chip MAX15054.

[0022] Furthermore, the throttle servo control unit, the tachometer output unit and the turbocharger control unit adopt a MOS tube low-side drive circuit.

[0023] Furthermore, the storage unit is a flash memory.

[0024] Furthermore, the power management unit outputs a 5V power supply for powering external sensors.

[0025] The utility model achieves the following technical effects:

[0026] The utility model provides a highly integrated electronic control unit for aviation piston engines, which can not only accept user instructions and various sensor signals to control fuel injection and ignition, but also enable users to control the throttle steering gear and the power-on or power-off operation management of the electronic control unit and the fuel pump through the RS232 interface and the CAN bus interface. It can effectively reduce the aircraft design and development cycle and cost, and reduce the failure rate of aircraft equipment. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 It is a system block diagram of the electronic control unit of the aviation piston engine of the utility model;

[0028] Figure 2 The utility model is a control flow chart of an aviation piston engine. DETAILED DESCRIPTION

[0029] To further illustrate each embodiment, the present invention provides drawings. These drawings are part of the disclosure of the present invention, which are mainly used to illustrate the embodiments and can be used in conjunction with the relevant descriptions in the specification to explain the operating principles of the embodiments. With reference to these contents, ordinary technicians in this field should be able to understand other possible implementations and advantages of the present invention.

[0030] The utility model is now further described in conjunction with the accompanying drawings and specific implementation methods.

[0031] like Figure 1 As shown, the utility model provides an embodiment of an electronic control unit (ECU for short) of an aviation piston engine.

[0032] In this embodiment, the electronic control unit is an electronic control unit of a four-cylinder aviation piston engine, which mainly includes: a main control chip, an analog signal input unit, a switch signal input unit, a storage unit, an ignition coil control unit, an injection control unit, a fuel pump control unit, a turbocharger control unit, a throttle servo control unit, a tachometer output unit, a pressure sensor unit, an RS232 communication unit, a CAN communication unit and a power management unit and other functional units.

[0033] The electronic control unit of this embodiment is packaged as a module, which is suitable for the electronic control requirements of a four-cylinder turbocharged aviation piston engine. The pin definition is shown in Table 1.

[0034] This electronic control unit defines multiple analog signal input units, each analog signal input unit is connected to each sensor to collect the signals of each sensor. In this embodiment, the sensors connected to each analog signal input unit mainly include cylinder head temperature sensor, intake air temperature sensor, intake air pressure sensor and throttle position sensor. The main control chip processes these sensor signals, issues control instructions, and executes control functions such as engine ignition, air-fuel ratio control, idle speed adjustment, and exhaust gas recirculation. In this embodiment, in order to ensure the long life and high reliability of the aviation piston engine, the aviation piston engine is also cooled by coolant to prevent the engine from overheating or overcooling. For this reason, this electronic control unit is also provided with an analog signal input unit to collect the coolant temperature.

[0035] In this embodiment, a switch signal input unit is provided for connecting the emergency switch and the main control chip. The main control chip can implement emergency start and stop control according to the input.

[0036] Among them, the main control chip uses a processor with a 32-bit ARM processor as the processing core, such as the STM32F3 series processor. The STM32F3 series processor has powerful processing capabilities and sufficient data interfaces of various types, which can meet the requirements of the main control chip's data processing capabilities and the number of various types of interfaces for completing various controls of aviation piston engines, and has low power consumption.

[0037] The storage unit uses a flash memory (Flash), which is a non-volatile memory that can be integrated on a circuit board and has the advantages of small size and fast reading and writing speed.

[0038] In order to effectively control the aviation piston engine, this electronic control unit defines multiple output units, mainly including: 4 ignition coil control units, 4 injection control units, 1 throttle servo control unit, 1 turbocharger control unit and 1 tachometer output unit, etc. Among them:

[0039] The ignition coil control unit uses a dedicated ignition coil control chip, such as ST's VBG08H. The VBG08H is a single-channel, intelligent electronic igniter with a built-in power-level IGBT. The ignition coil control unit is driven by a low voltage.

[0040] The fuel injection control unit is used to control the shutoff and conduction of the fuel delivery pipeline from the fuel pump to the corresponding cylinder. It uses a high-side MOS driver chip for high-voltage drive, such as the chip MAX15054. The chip MAX15054 is a high-side, n-channel MOSFET driver that can adapt to high-frequency switching high-voltage applications. Inside the electronic control unit, the fuel injection control unit needs to be connected to the 12V power supply and powered by the 12V power supply.

[0041] The throttle servo control unit is composed of a MOS tube low-side drive circuit, which is used to output the throttle servo control signal.

[0042] The turbocharger control unit is composed of a MOS tube low-side drive circuit and is used to output a turbocharger control signal.

[0043] The tachometer output unit is composed of a MOS tube low-side drive circuit and is used to output a speed signal to an external tachometer device, such as an instrument panel.

[0044] The pressure sensor unit is integrated into the electronic control unit and can sense changes in atmospheric pressure. In flight control, atmospheric pressure is an important parameter. Integrating the pressure sensor unit into the electronic control unit can simplify the design and ensure that data acquisition is more stable and reliable.

[0045] In this embodiment, in order to optimize the power supply and device connection of each sensor device, the sensors are uniformly powered by the electronic control unit. A power management unit is integrated in this electronic control unit. The power management unit draws power from the battery BAT+, generates a set of 3.3V power supplies to power the main control chip through DC voltage regulation, generates a set of 5V power outputs to power each sensor, and outputs high voltages such as 12V to power high-voltage drive devices such as the ignition coil control unit.

[0046] Table 1 Pin description of the electronic control unit

[0047]

[0048]

[0049] The control process of the electronic control unit ECU of the aviation piston engine of the utility model is as follows: Figure 2 As shown, including:

[0050] S101, system initialization step: initialization of ECU internal operating parameters, including reading parameters saved in Flash (i.e. storage unit), assigning values ​​to relevant operating parameters, etc.

[0051] S102, the step of collecting the power supply voltage and performing over-voltage or under-voltage detection: the ECU collects and calculates the voltage value of the power supply, and detects whether the voltage is under-voltage or over-voltage.

[0052] S103, step of shutting down all outputs: When the power supply exceeds the ECU operating voltage range or the ECU executes the shutdown command in the RS232 protocol, the ECU shuts down the signals of all output channels to prevent the abnormal power supply from damaging the electronic devices connected to the ECU output channel box.

[0053] S104, fuel pump is turned on, and steps for collecting sensor data are as follows: ECU outputs an action signal to the electronic device controlling the fuel pump, and the electronic device powers on the fuel pump to start working; ECU obtains data such as throttle opening, atmospheric pressure, intake temperature, engine speed, cylinder head temperature, ambient temperature, etc. through collection and calculation.

[0054] S105, fuel pump shut-off step: ECU outputs an action signal to the electronic device controlling the fuel pump, and the electronic device shuts off the power to the fuel pump. This step is performed when it is detected that the engine speed does not reach the specified speed within the specified time of fuel pump on.

[0055] S106, ignition, fuel injection, and tachometer output steps: ECU outputs action signals to ignition and fuel injection related electronic devices, and the electronic devices drive the engine related ignition and fuel injection devices to work, so that the engine can continue to run; ECU outputs speed signals to an external tachometer device;

[0056] S107, step of modifying the servo control pulse width: the ECU executes the instruction for modifying the servo control pulse width in the CAN protocol, modifies the servo control pulse width, the servo control pulse width drives the servo on the engine through the wiring harness, and the servo drives the structure to rotate the throttle of the engine to a corresponding angle.

[0057] S108, step of sending a data packet to the host computer: the ECU executes the instruction of sending a data packet in the RS232 protocol, and sends the data packet to the host computer through the RS232 interface.

[0058] S109, step of outputting Flash data via CAN: the ECU executes the instruction for reading Flash in the RS232 protocol, and sends the Flash data to the host computer via the CAN interface.

[0059] S110, step of storing in Flash: ECU saves the modified data such as servo control pulse width, servo angle, etc. into Flash.

[0060] The utility model provides a highly integrated electronic control unit for aviation piston engines, which can not only accept user instructions and various sensor signals to control fuel injection and ignition, but also enable users to control the throttle steering gear and the power-on or power-off operation management of the electronic control unit and the fuel pump through the RS232 interface and the CAN bus interface. It can effectively reduce the aircraft design and development cycle and cost, and reduce the failure rate of aircraft equipment.

[0061] Although the present invention has been specifically demonstrated and described in conjunction with the preferred embodiments, those skilled in the art should understand that various changes may be made to the present invention in form and detail without departing from the spirit and scope of the present invention as defined in the appended claims, all of which are within the scope of protection of the present invention.

Claims

1. An electronic control unit for an aviation piston engine, characterized in that: include: Main control chip; An analog signal input unit for collecting external sensor data and sending it to the main control chip, wherein the sensor data includes throttle opening, intake air temperature, engine speed, cylinder head temperature and ambient temperature; A switch signal input unit for connecting an emergency switch to the main control chip; A storage unit connected to the main control chip; An ignition coil control unit connected to the main control chip; A fuel injection control unit connected to the main control chip; A fuel pump control unit connected to the main control chip; A turbocharger control unit connected to the main control chip; A throttle servo control unit connected to the main control chip; A tachometer output unit connected to the main control chip; A pressure sensor unit connected to the main control chip and used to collect atmospheric pressure; An RS232 communication unit and a CAN communication unit connected to the main control chip for communication between the electronic control unit and the host computer; and A power management unit is used to connect to an external power source, supply power to all units of the electronic control unit, and output power to supply power to external sensors.

2. The electronic control unit of an aviation piston engine according to claim 1, characterized in that: The electronic control unit is powered by 12V and includes 4 ignition coil control units, 4 fuel injection control units, 1 throttle servo control unit, 1 turbocharger control unit and 1 tachometer output unit.

3. The electronic control unit of an aviation piston engine according to claim 1, characterized in that: The main control chip uses a processor with a 32-bit ARM processor as the processing core.

4. The electronic control unit of an aviation piston engine according to claim 1, characterized in that: The ignition coil control unit includes an ignition coil control chip VBG08H with a built-in power-level IGBT driver.

5. The electronic control unit of an aviation piston engine according to claim 1, characterized in that: The fuel injection control unit includes a high-side MOS driver chip MAX15054.

6. The electronic control unit of an aviation piston engine according to claim 1, characterized in that: The throttle servo control unit, the tachometer output unit and the turbocharger control unit adopt a MOS tube low-side drive circuit.

7. The electronic control unit of an aviation piston engine according to claim 1, characterized in that: The storage unit is a flash memory.

8. The electronic control unit of an aviation piston engine according to claim 1, characterized in that: The power management unit outputs a 5V power supply for powering external sensors.

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