A multi-mode aircraft engine ground start control device

Abstract

The utility model discloses a kind of multi-mode aeroengine ground starting control device, including main control module, key input module and state indicating module, the state indicating module includes multiple indicator lights, the key input circuit is connected with the main control module, so that the main control module can be based on the hardware filtering characteristic of the key input circuit and its internal clock resource and carry out delay sampling;The connection relationship between each the indicator light and the main control module output port is configured as in response to any valid key trigger signal, so that only with the drive loop of one the indicator light corresponding to the currently activated operating mode is turned on, while the drive loop of remaining the indicator light is all in off state.The utility model is integrated by key input, state indication, analog signal acquisition and communication interface module, combined with software anti-shake, LED mutual exclusion display and flight control mode forced mutual exclusion logic, high reliability, low misoperation rate ground operation control is realized.

Description

Technical Field

[0001] This utility model belongs to the technical field of aviation ground support equipment, and particularly relates to the technical field of aviation ground support equipment. Background Technology

[0002] When aircraft engines are started, tested, unsealed from fuel storage, or cold-run on the ground, specialized ground control devices are required to issue precise commands. Traditional control devices are mostly built using logic circuits based on discrete relays or simple programmable logic controllers (PLCs), which have the following obvious drawbacks: First, in terms of hardware construction, the modules are scattered and the connections are complex, resulting in a large device size, poor portability, and difficulty in deployment in space-constrained hangars or field applications. Second, regarding interference resistance, mechanical buttons are prone to contact bounce when pressed, and traditional designs lack effective hardware filtering and logic processing coordination mechanisms, which may lead to false triggers or lost instructions, resulting in insufficient reliability. Third, in terms of functional logic, existing devices have fixed operating modes, and buttons typically only support instantaneous triggering of a single function, unable to distinguish between different operation intentions such as short presses and long presses, and lack intelligent interlocking and switching logic between different operating modes, resulting in poor flexibility. Finally, in terms of human-computer interaction, status indicators often use a simple arrangement of multiple indicator lights. When switching modes, the indicator status is chaotic or unclear, making it difficult for operators to accurately identify the currently active mode in a short time, posing a high risk of misoperation and potentially causing safety issues.

[0003] Therefore, this utility model discloses a multi-mode aero-engine ground start control device. Utility Model Content

[0004] The purpose of this invention is to solve the problems in the prior art by proposing a multi-mode aero-engine ground start control device.

[0005] A multi-mode aircraft engine ground start control device, comprising: Main control module; A key input module includes multiple function keys, which are connected to the input port of the main control module via a key input circuit with pull-up resistors. A status indication module includes multiple indicator lights, each of which is connected to the output port of the main control module via an independent drive circuit. The key input circuit is connected to the input port of the main control module, enabling the main control module to perform delayed sampling based on the hardware filtering characteristics and internal clock resources of the key input circuit in order to identify valid key trigger signals. The connection between each indicator light and the output port of the main control module is configured such that, in response to any valid button trigger signal, only the drive circuit of one indicator light corresponding to the currently activated working mode is turned on, while the drive circuits of the other indicator lights are turned off.

[0006] The device also includes an analog signal acquisition module, whose signal output terminal is connected to the data input terminal of the main control module; A communication interface module, the signal input terminal of which is connected to the data output terminal of the main control module; The analog signal acquisition module, the main control module, and the communication interface module are connected in series to form a signal path for acquiring analog quantities and outputting corresponding data commands in a specific working mode.

[0007] In the above-mentioned device, the main control module includes a key state locking unit. The input of the key state locking unit is connected to the key input circuit, and its output state is associated with the continuous low level state of the key signal. When the key state locking unit is in the locked state, the main control module does not respond to other key trigger signals of the key input module.

[0008] In the above device, the analog signal acquisition module includes a potentiometer and an analog-to-digital converter chip, and the analog-to-digital converter chip is connected to the main control module through a serial peripheral interface bus.

[0009] In the above device, the communication interface module includes a UART serial communication circuit and a level conversion circuit, and the input terminal of the level conversion circuit is connected to the serial communication pin of the main control module.

[0010] The device also includes an acoustic-optical feedback module, which includes a buzzer and its driving circuit. The control terminal of the driving circuit is connected to a designated output pin of the main control module.

[0011] In the aforementioned device, the number of the plurality of function buttons includes at least eight, and specifically corresponds to eight functions: shot detection, start-up, stage transition, flight control, cold operation, oil unsealing, shutdown, and buzzer control. Attached Figure Description

[0012] Figure 1 This is a model diagram of a multi-mode aero-engine ground start control device disclosed in this utility model.

[0013] Figure 2 This is a signal flow diagram of a multi-mode aero-engine ground start control device disclosed in this utility model.

[0014] Figure 3This utility model discloses a multi-mode aero-engine ground start control device that uses chip simulation acquisition and SPI interface circuit diagram. Detailed Implementation

[0015] To facilitate understanding of this application and to make the aforementioned objectives, features, and advantages of this application more apparent, a detailed description of specific embodiments of this application is provided below in conjunction with the accompanying drawings. Numerous specific details are set forth in the following description to provide a thorough understanding of this application, and preferred embodiments are shown in the accompanying drawings. However, this application can be implemented in many different forms and is not limited to the embodiments described herein. Rather, these embodiments are provided to provide a more thorough and complete understanding of the disclosure of this application. This application can be implemented in many other ways different from those described herein, and those skilled in the art can make similar modifications without departing from the spirit of this application; therefore, this application is not limited to the specific embodiments disclosed below. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this application, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified. In the description of this application, "several" means at least one, such as one, two, etc., unless otherwise explicitly specified. It should be noted that when an element is referred to as being "fixed to" another element, it can be directly attached to the other element or there may be an intervening element. When an element is referred to as being "connected to" another element, it can be directly connected to the other element or there may be an intervening element. The terms "vertical," "horizontal," "left," "right," and similar expressions used herein are for illustrative purposes only and do not represent the only possible implementations. Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used herein is only for describing particular implementations and is not intended to limit the scope of this application. The term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0016] like Figures 1-3 As shown, this utility model provides a multi-mode aero-engine ground start control device based on a single-chip microcomputer, comprising: Main control module; A key input module includes multiple function keys, which are connected to the input port of the main control module via a key input circuit with pull-up resistors. A status indication module includes multiple indicator lights, each of which is connected to the output port of the main control module via an independent drive circuit. The connection between the key input circuit and the main control module is configured such that the main control module can identify valid key triggers based on the hardware-filtered signal and preset delay logic. The connection between each indicator light and the main control module is configured such that when a working mode is activated due to the effective triggering of any of the function keys, the main control module controls the driving circuit of only the indicator light corresponding to the activated working mode to be turned on.

[0017] Preferably, the device further includes a mode mutual exclusion circuit, which is integrated into the main control module or implemented by its pin logic, and is configured to: when the first working mode is in an active state, if a trigger signal for the second working mode is received, automatically output a signal to turn off the first working mode and activate the second working mode, while switching the display state of the status indicator module.

[0018] In this embodiment, the main control module can be a microcontroller of model STC89C52RC, labeled U1. This microcontroller has general-purpose input / output pins, a serial communication interface and a serial peripheral interface to meet the control and communication requirements of the system.

[0019] The button input module contains multiple function buttons, each composed of eight tactile switches, labeled SW1 to SW8. Switch SW1 corresponds to the firing detection mode, SW2 to the start mode, SW3 to the stage transition mode, SW4 to the flight control mode, SW5 to the cold run mode, SW6 to the oil seal opening mode, SW7 to the stop mode, and SW8 controls the buzzer switch. One end of each tactile switch is directly grounded. The other end is connected to a 10kΩ pull-up resistor and then to a 5V DC power supply. Wires are led from this connection point to the eight pins of the P1 port of the microcontroller U1, specifically SW1 to P1.0, SW2 to P1.1, and so on until SW8 to P1.7. This circuit constructs a low-level active detection network. When the button is not activated, the microcontroller detects a high level; when the button is pressed, the corresponding pin is pulled low, thus forming a simple hardware filtering network.

[0020] The status indicator module contains seven LEDs, labeled LED1 to LED7, which correspond to the seven operating modes represented by SW1 to SW7. The anodes of all LEDs are connected to a 5V power supply via a common 220Ω current-limiting resistor. The cathodes of each LED are connected to the seven pins of the P0 port of the microcontroller U1, specifically P0.0 for LED1, P0.1 for LED2, and so on up to P0.6 for LED7. By programming the output level of each pin of the microcontroller's P0 port, the on / off state of each LED can be independently controlled. To achieve intuitive mutual exclusion display, in the software control logic, when a new mode indicator needs to be lit, a subroutine is first executed to set all relevant pins of the P0 port to a high level to turn off all indicator lights. Then, only the pin corresponding to the target mode is set to a low level, thus lighting only that single indicator light.

[0021] The audio-visual feedback module includes an active buzzer BZ1 and an NPN transistor Q1 (model S8050). The positive terminal of buzzer BZ1 is connected to a +5V power supply, and its negative terminal is connected to the collector of transistor Q1. The emitter of transistor Q1 is directly grounded, and its base is connected to pin P2.5 of microcontroller U1 through a 1000Ω current-limiting resistor. When microcontroller U1 needs to provide an audio prompt, its pin P2.5 outputs a high-level signal, driving transistor Q1 to saturate and conduct, thus causing buzzer BZ1 to sound.

[0022] The analog signal acquisition module consists of a multi-turn precision potentiometer RP1 and an analog-to-digital converter chip U2, model XPT2046. The two ends of potentiometer RP1 are connected to the reference voltage and circuit ground, respectively, and its sliding lead is connected to the channel input pin of chip U2. The power supply pin and reference voltage pin of chip U2 are connected as specified. Its serial peripheral interface, including chip select pin, data input pin, data output pin, and clock pin, is connected to pins P3.3, P3.4, P3.5, and P3.6 of microcontroller U1, respectively.

[0023] The communication interface module adopts a universal asynchronous transceiver to RS-232 standard scheme. The transmit pin TXD (P3.1) and receive pin RXD (P3.0) of the microcontroller U1 are connected to the transistor logic level side of a MAX232 level conversion chip. The RS-232 level side of the MAX232 chip is brought out through a standard DB9 connector for establishing a communication connection with a host computer or other ground support equipment.

[0024] The power management module employs a low-dropout linear regulator, model AMS1117-5.0, to stably convert the externally input DC voltage into DC voltage to power the entire control device. To enhance power quality, a 0.1μF ceramic capacitor is connected in parallel near the power pins of integrated circuits such as the microcontroller U1, the analog-to-digital converter U2, and the level converter MAX232 for decoupling.

[0025] The working principle and process of the device described in this embodiment are as follows: After the device is powered on, the microcontroller U1 executes the initialization program, sets all the control indicator pins to high level, turns off all LEDs, and the system enters standby mode, continuously scanning key inputs.

[0026] The microcontroller U1 reads the voltage levels of each pin on its P1 port at fixed intervals. When a pin, such as the P1.3 pin corresponding to flight control button SW4, changes from high to low, the system does not immediately recognize it as a valid operation. Instead, it waits for ten to twenty milliseconds until the mechanical jitter subsides before checking the pin level again. If it is still low, the flight control button is considered to have been pressed validly. At this time, a memory unit inside the microcontroller used to record the button release state is set, and the number of the currently pressed button is stored in another dedicated memory.

[0027] Subsequently, the microcontroller executes the corresponding mode processing program based on the stored button number. Taking flight control mode as an example, the program first calls a function to output a high level on all relevant pins of port P0, turning off all indicator lights. Next, it controls pin P0.3 to output a low level, causing the corresponding LED4 to light up, indicating that flight control mode has been activated. The system then enters the flight control working state.

[0028] During flight control mode activation, microcontroller U1 sends control words to the XPT2046 chip at a certain frequency, for example, ten times per second, via the serial peripheral interface bus and reads the converted digital value. This digital value reflects the voltage position of the potentiometer's sliding terminal. The microcontroller encapsulates this value into a data frame according to a predetermined protocol. The frame contains a start flag, flight control mode code, data bytes, and a checksum. After encapsulation, the data frame is sent to the MAX232 chip via its serial communication interface for level conversion, and finally sent to external devices in RS-232 standard format, enabling continuous adjustment of engine parameters.

[0029] If, during flight control mode operation, the operator presses the detection button SW1, the microcontroller, after confirming the effective press of SW1 via anti-shake processing, will immediately execute a forced mode switch. Specifically, this involves: terminating the periodic transmission of current flight control data, controlling the P0.3 pin to output a high level to turn off LED4, then controlling the P0.0 pin to output a low level to turn on LED1, and immediately sending a detection command frame outward through the communication interface. This process demonstrates the forced mutual exclusion function between modes implemented by the hardware connection and the embedded logic.

[0030] Furthermore, the memory cell set upon first detection of a valid key press will remain in that state until the microcontroller detects that the corresponding key's pin level has returned to high, i.e., the physical key has been released. Only then will the memory cell be cleared. During the period when this cell is set, the microcontroller's key scanning program can be configured to temporarily ignore responses to other key press events, thereby achieving operation locking before key release and effectively preventing accidental triggering.

[0031] To provide multiple feedback mechanisms, the microcontroller can control its P2.5 pin to output a brief high-level pulse after each successful processing of a valid key press, driving the buzzer to emit a prompt tone and providing clear auditory confirmation to the operator.

[0032] As is known from common technical knowledge, this utility model can be implemented through other embodiments that do not depart from its spirit or essential characteristics. Therefore, the disclosed embodiments described above are merely illustrative in all respects and are not the only ones. All modifications within the scope of this utility model or its equivalents are included in this utility model.

Claims

1. A multi-mode aircraft engine ground start control device, characterized in that, include: Main control module; A key input module includes multiple function keys, which are connected to the input port of the main control module via a key input circuit with pull-up resistors. A status indication module includes multiple indicator lights, each of which is connected to the output port of the main control module via an independent drive circuit. The key input circuit is connected to the input port of the main control module, enabling the main control module to perform delayed sampling based on the hardware filtering characteristics and internal clock resources of the key input circuit in order to identify valid key trigger signals. The connection between each indicator light and the output port of the main control module is configured such that, in response to any valid button trigger signal, only the drive circuit of one indicator light corresponding to the currently activated working mode is turned on, while the drive circuits of the other indicator lights are turned off.

2. The multi-mode aero-engine ground start control device according to claim 1, characterized in that, Also includes: An analog signal acquisition module, the signal output terminal of which is connected to the data input terminal of the main control module; A communication interface module, the signal input terminal of which is connected to the data output terminal of the main control module; The analog signal acquisition module, the main control module, and the communication interface module are connected in series to form a signal path for acquiring analog quantities and outputting corresponding data commands in a specific working mode.

3. The multi-mode aero-engine ground start control device according to claim 1, characterized in that, The main control module includes a key state locking unit. The input of the key state locking unit is connected to the key input circuit, and its output state is associated with the continuous low level state of the key signal. When the key state locking unit is in the locked state, the main control module does not respond to other key trigger signals of the key input module.

4. The multi-mode aero-engine ground start control device according to claim 2, characterized in that, The analog signal acquisition module includes a potentiometer and an analog-to-digital converter chip, which is connected to the main control module via a serial peripheral interface bus.

5. The multi-mode aero-engine ground start control device according to claim 2, characterized in that, The communication interface module includes a UART serial communication circuit and a level conversion circuit. The input terminal of the level conversion circuit is connected to the serial communication pin of the main control module.

6. The multi-mode aero-engine ground start control device according to claim 1, characterized in that, It also includes an acoustic-optical feedback module, which includes a buzzer and its driving circuit. The control terminal of the driving circuit is connected to a designated output pin of the main control module.

7. The multi-mode aero-engine ground start control device according to claim 6, characterized in that, The number of the aforementioned function buttons is at least eight, and they specifically correspond to eight functions: shot detection, start-up, stage transition, flight control, cold run, oil seal opening, stop, and buzzer control.

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