Electromechanical integrated controller for helicopter

Abstract

An embodiment of the utility model discloses an electromechanical integrated controller used for a helicopter, an onboard power supply of the helicopter is connected to a power supply processing module, and the power supply processing module is respectively connected to an MCU chip, each control switch in a switch assembly and an indicating lamp of each assigned control switch. The voltage is converted and processed by the power supply processing module to form a working voltage; the control switches are respectively connected to the corresponding IO ports of the MCU chip through the switch signal acquisition module, and the input level of the corresponding IO ports on the MCU chip is read and judged through the switch signal acquisition module so as to judge the state of each control switch in the switch assembly; the MCU chip is also connected with the CAN communication module, and transmits the collected state of each control switch to an avionics system in the form of a data packet. According to the technical scheme of the utility model, the problem that time and labor are wasted in the aspects of fault positioning and fault processing due to the fact that the state of each switch cannot be monitored in the existing switch control mode of the system in the helicopter is solved.

Description

Technical Field

[0001] The utility model relates to but is not limited to the technical field of helicopter fuel system, hydraulic system and fire extinguishing system control, and in particular to an electromechanical integrated controller for helicopters. Background Art

[0002] At present, many helicopters simply use switches to control the fuel system, hydraulic system, and fire extinguishing system, and are unable to monitor the status of each switch in real time.

[0003] In the above switch control method for the helicopter onboard system, when the onboard system fails, it is impossible to directly determine whether the failure is caused by damage to the control switch or damage to the onboard system equipment, so that it is time-consuming and laborious to locate and handle the failure. Utility Model Content

[0004] Purpose of the utility model: In order to solve the above-mentioned technical problems, the embodiment of the utility model provides an electromechanical integrated controller for a helicopter to solve the problem that the existing switch control method of the onboard system in the helicopter cannot monitor the status of each switch, thereby causing time-consuming and labor-intensive problems in fault location and fault handling.

[0005] Technical solution of the utility model: The embodiment of the utility model provides an electromechanical integrated controller for a helicopter, comprising: a power processing module, a switch signal acquisition module, an MCU chip and a CAN communication module, and a switch component;

[0006] The helicopter's onboard power supply is connected to the power processing module, which is respectively connected to the MCU chip, each control switch in the switch assembly, and the indicator lights of each designated control switch in the switch assembly. The power processing module converts and processes the power to form a working voltage for supplying power to the back-end circuit devices.

[0007] Each control switch in the switch assembly is connected to the IO port corresponding to the MCU chip through the switch signal acquisition module, and the input level of the corresponding IO port on the MCU chip is read and judged by the switch signal acquisition module to judge the state of each control switch in the switch assembly; wherein the control switch in the switch assembly is set based on the control requirements of the fuel system, the hydraulic system, and the fire extinguishing system and the requirements of the load connected in the circuit of each system;

[0008] The MCU chip is also connected to the CAN communication module to send the collected status of each control switch to the avionics system in the form of a data packet;

[0009] The MCU chip is also connected to the indicator lights of each designated switch, and is used to drive all the indicator lights of each designated switch to light up through the input signal of the cockpit on the receiver, thereby realizing the inspection function of the indicator lights equipped with each designated switch, or, through the brightness conversion signal of the cockpit on the receiver, output different voltages to the indicator lights of the designated control switches, thereby realizing the day and night conversion function of the indicator lights.

[0010] Optionally, in the electromechanical integrated controller for a helicopter as described above, the power processing module includes: a DC-DC module 1, a DC-DC module 2, a surge suppression module and a filter module;

[0011] Among them, the two power supplies on the helicopter are converted and isolated by DC-DC module 1 and DC-DC module 2 respectively, and then converged. They are processed by surge suppression module and filter module in turn to eliminate surge voltage and peak voltage on the aircraft, and provide the required working voltage for each back-end circuit device.

[0012] Optionally, the electromechanical integrated controller for a helicopter as described above further comprises: a light guide plate assembly, comprising: a light guide plate, and a blue-white light source and a night vision green light source built into the light guide plate and connected in parallel;

[0013] The light guide plate of the light guide plate assembly is arranged on the back side of the switch assembly, serving as the backlight plate of each control switch in the switch assembly; wherein, the onboard power supply is selectively connected to the positive pole of the blue-white light source and the night vision green light source through the internal circuit of the light guide plate assembly, and its negative pole is grounded; so as to receive the corresponding signal through the light guide plate assembly to complete the display function of blue-white light and night vision green.

[0014] Optionally, in the electromechanical integrated controller for a helicopter as described above, the designated control switches in the switch assembly include: 1-engine fire extinguishing switch, 2-engine fire extinguishing switch, APU fire extinguishing switch, and fire extinguishing level release switch;

[0015] The electromechanical integrated controller is used to convert the ground signal sent from the aircraft into a ground signal filtered by the power processing module through the photoelectric coupler in the MCU chip when the MCU chip receives a low signal sent from the cockpit on the aircraft, and output a control signal to each indicator light of the four control switches through the IO port of the MCU chip to drive all the indicator lights to light up, thereby realizing the inspection function of the indicator lights on the four switches.

[0016] Optionally, in the electromechanical integrated controller for a helicopter as described above, the indicator lights of each designated control switch include a red light and a yellow light;

[0017] The electromechanical integrated controller is also used to convert the day and night brightness conversion signal issued by the aircraft into a corresponding signal filtered by the power processing module through the photoelectric coupler of the MCU chip when the MCU chip receives the day and night brightness conversion signal issued by the cockpit on the aircraft. After reading the day brightness signal, a (20±1)VDC voltage is provided to the light and / or the yellow light through the IO port. After reading the night brightness signal, a (15±0.5)VDC voltage is provided to the light and / or the yellow light through the IO port, thereby realizing the day and night conversion function.

[0018] Optionally, in the electromechanical integrated controller for a helicopter as described above, the switch assembly is provided with a plurality of different types of control switches, and each type of control switch has at least one of the mechanical properties of two-position, three-position, locking, and self-resetting.

[0019] Optionally, in the electromechanical integrated controller for a helicopter as described above, the emergency pump switch and the brake electric pump switch are three-position switches, and the other switches are two-position switches;

[0020] The electromechanical integrated controller is used to perform state determination of a two-position switch. When the IO port of the MCU chip detects a high-level signal, the corresponding switch is determined to be in an off state; when the IO port detects a low level, the corresponding switch is determined to be in an on state.

[0021] The electromechanical integrated controller is used to perform state determination of the three-position switch, and determines whether the switch is in the disconnected, connected or automatic state by detecting the output level signals of the corresponding points in the upper and lower groups of the three-position switch.

[0022] Beneficial effects of the utility model: The electromechanical integrated controller for helicopters provided by the utility model embodiment integrates the control functions of the fuel system, hydraulic system, and fire extinguishing system on the helicopter in the switch assembly of the electromechanical integrated controller, collects the current status of each control switch in the switch assembly through the switch signal acquisition module, and sends it out through the CAN communication module, so that it can be clearly known whether the control switch has a fault; in addition, for a specified control switch, the light inspection and day and night mode switching functions can be realized through the input signal provided by the cockpit. The electromechanical integrated controller provided by the utility model embodiment realizes the functions of integrated indicator light control, signal acquisition and communication in the form of hardware circuits, has the characteristics of rapid fault location and fault isolation, and the electromechanical integrated controller has the advantages of light weight, simple maintenance, high reliability, etc. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The accompanying drawings are used to provide a further understanding of the technical solution of the utility model and constitute a part of the specification. Together with the embodiments of the present application, they are used to explain the technical solution of the utility model and do not constitute a limitation on the technical solution of the utility model.

[0024] Figure 1 A schematic diagram of the structure of an electromechanical integrated controller for a helicopter provided in an embodiment of the utility model;

[0025] Figure 2 A schematic diagram of the state judgment of a two-position switch in an embodiment of the utility model;

[0026] Figure 3 This is a schematic diagram of the state judgment of the three-position switch in the embodiment of the utility model. Figure 3 Figure a shows the on state, figure b shows the off state, and figure c shows the automatic state. DETAILED DESCRIPTION

[0027] In order to make the purpose, technical solution and advantages of the utility model more clear, the embodiments of the utility model will be described in detail with reference to the accompanying drawings. It should be noted that the embodiments and features in the embodiments of the present application can be combined with each other arbitrarily without conflict.

[0028] As described in the above background technology, the existing switch control method of the helicopter onboard system cannot directly determine whether the fault is caused by damage to the control switch or damage to the onboard system equipment when the onboard system fails, so that it is time-consuming and laborious to locate and handle the fault.

[0029] With the development of computer technology and intelligent technology, intelligent control technology will gradually be used in electromechanical control. Therefore, the rational integration of intelligent control technology into electromechanical control systems can not only facilitate pilots to grasp the status of various systems on board in real time during flight, but also accurately locate the fault location and quickly handle it after it occurs.

[0030] In view of the problems existing in the existing switch control of helicopters, an embodiment of the utility model provides an electromechanical integrated controller for helicopters. By integrating the control functions of the onboard fuel system, hydraulic system, and fire extinguishing system, and realizing integrated indicator light control, signal acquisition and communication functions in the form of hardware circuits, the electromechanical integrated controller has the characteristics of rapid fault location and fault isolation, and the electromechanical integrated controller is light in weight, simple to maintain, and highly reliable.

[0031] The utility model provides the following specific embodiments which can be combined with each other, and the same or similar concepts or processes may not be described in detail in some embodiments.

[0032] Figure 1 The schematic diagram of the structure of a mechatronic integrated controller for a helicopter provided by the embodiment of the utility model. Figure 1As shown, the electromechanical integrated controller for a helicopter provided by the embodiment of the utility model includes: a power processing module, a switch signal acquisition module, an MCU chip and a CAN communication module, and a switch component.

[0033] like Figure 1 In the structure of the electromechanical integrated controller shown, the onboard power supply of the helicopter is connected to the power processing module, and the power processing module is respectively connected to the MCU chip, each control switch in the switch assembly, and the indicator lights of each designated control switch in the switch assembly. After conversion and processing by the power processing module, a working voltage is formed to supply power to the back-end circuit devices.

[0034] It should be noted that the switch assembly of the embodiment of the utility model includes various control switches for realizing the control requirements of the fuel system, the hydraulic system, and the fire extinguishing system. Among these control switches, only the designated switches have indicator lights, and the other switches do not have indicator lights.

[0035] In an embodiment of the utility model, each control switch in the switch assembly is connected to the corresponding IO port of the MCU chip through a switch signal acquisition module, and the switch signal acquisition module reads and judges the input level of the corresponding IO port on the MCU chip to judge the state of each control switch in the switch assembly; wherein, the control switch in the switch assembly is set based on the control requirements of the fuel system, the hydraulic system, and the fire extinguishing system and the requirements of the load connected in the circuit of each system.

[0036] The MCU chip in the embodiment of the utility model is also connected to the CAN communication module to send the collected status of each control switch to the avionics system in the form of a data packet; thereby the status of each control switch can be clearly known.

[0037] In addition, the electromechanical integrated controller for a helicopter provided in the embodiment of the utility model can also realize the indicator light checking function of the control switch and the day and night switching function of the indicator light.

[0038] The MCU chip is also connected to the indicator lights of each designated switch, and is used to drive all the indicator lights of each designated switch to light up through the input signal of the cockpit on the receiver, thereby realizing the inspection function of the indicator lights equipped with each designated switch, or, through the brightness conversion signal of the cockpit on the receiver, output different voltages to the indicator lights of the designated control switches, thereby realizing the day and night conversion function of the indicator lights.

[0039] like Figure 1 As shown in the figure, the switch assembly in the embodiment of the utility model includes 12 control switches, among which 1 fire extinguishing switch, 2 fire extinguishing switches, APU fire extinguishing switch and fire extinguishing level release switch are designated switches, which are respectively provided with red light and yellow light.

[0040] In one implementation of the present utility model, Figure 1 As shown, the power processing module includes: DC-DC module 1, DC-DC module 2, surge suppression module and filter module.

[0041] Among them, the two power supplies on the helicopter are converted and isolated by DC-DC module 1 and DC-DC module 2 respectively, and then converged. They are processed by surge suppression module and filter module in turn to eliminate surge voltage and peak voltage on the aircraft, and provide the required working voltage for each circuit device at the back end; for example, 3.3V, 15V and 20V voltages are converted, and 3.3V voltage is used to supply power to each control switch in the MCU chip and the switch component respectively, and 15V or 20V voltage is used to supply power to the indicator lights of each designated switch respectively.

[0042] In one implementation of the present utility model, Figure 1 As shown, the electromechanical integrated controller also includes: a light guide plate assembly, for example, including: a light guide plate, and a blue-white light source and a night-vision green light source built into the light guide plate and connected in parallel.

[0043] In this implementation, the light guide plate of the light guide plate assembly is arranged on the back side of the switch assembly, serving as the backlight plate of each control switch in the switch assembly; wherein, the onboard power supply is selectively connected to the positive pole of the blue-white light source and the night vision green light source through the internal circuit of the light guide plate assembly, and its negative pole is grounded; so as to receive the corresponding signal through the light guide plate assembly to complete the display function of blue-white light and night vision green.

[0044] The electromechanical integrated controller for a helicopter provided in the above embodiment of the utility model realizes the indicator light inspection function in the following manner:

[0045] When the MCU chip receives a low signal from the cockpit on the aircraft, the optocoupler in the MCU chip converts the ground signal from the aircraft into a ground signal filtered by the power processing module, and outputs control signals to the indicator lights of the four control switches through the IO port of the MCU chip, driving all the indicator lights to light up, thereby realizing the inspection function of the indicator lights on the four switches.

[0046] The electromechanical integrated controller for a helicopter provided in the above embodiment of the utility model realizes the day and night switching function of the indicator light in the following manner:

[0047] When the MCU chip receives the day / night brightness conversion signal from the cockpit, the photoelectric coupler of the MCU chip converts the day / night brightness conversion signal from the aircraft into a corresponding signal filtered by the power processing module. After reading the day brightness signal, a (20±1) VDC voltage is provided to the light and / or the yellow light through the IO port. After reading the night brightness signal, a (15±0.5) VDC voltage is provided to the light and / or the yellow light through the IO port, thereby realizing the day / night conversion function.

[0048] Furthermore, the switch assembly of the embodiment of the utility model is provided with a plurality of different types of control switches, and each type of control switch has at least one of the mechanical properties of two-position, three-position, locking, and self-resetting, which can meet the pilot's requirements for stable control and anti-misoperation protection during flight.

[0049] For example, the emergency pump switch and the brake electric pump switch use three-position switches with three states: disconnected, connected, and automatic. Other switches use two-position switches with two states: disconnected and connected.

[0050] Execute the status judgment of the two-bit switch. When the IO port of the MCU chip detects a high-level signal, it is judged that the corresponding switch is in the off state; when the IO port detects a low level, it is judged that the corresponding switch is in the on state.

[0051] The state judgment of the three-position switch is performed by detecting the output level signals of the corresponding points in the upper and lower groups of the three-position switch to judge whether the switch is in the disconnected, connected or automatic state; the specific judgment method is described in detail in the following embodiment.

[0052] By using the electromechanical integrated controller for a helicopter provided in an embodiment of the utility model, the connecting cables on the helicopter are connected to the connector of the electromechanical integrated controller, and the switches on the product are operated according to the system control logic of the helicopter of this model to connect or switch the load. The level conversion on the CAN bus is detected by special equipment to complete the control and status monitoring of the fuel system, hydraulic system, and fire extinguishing system.

[0053] The electromechanical integrated controller for helicopters provided by the embodiment of the utility model integrates the control functions of the fuel system, hydraulic system, and fire extinguishing system on the helicopter in the switch assembly of the electromechanical integrated controller, collects the current status of each control switch in the switch assembly through the switch signal acquisition module, and sends it out through the CAN communication module, so that it can be clearly known whether the control switch has a fault; in addition, for a specified control switch, the light inspection and day and night mode switching functions can be realized through the input signal provided by the cockpit. The electromechanical integrated controller provided by the embodiment of the utility model realizes the functions of integrated indicator light control, signal acquisition and communication in the form of hardware circuits, has the characteristics of rapid fault location and fault isolation, and the electromechanical integrated controller has the advantages of light weight, simple maintenance, high reliability, etc.

[0054] The following is a schematic illustration of the implementation of the electromechanical integrated controller for a helicopter provided by the utility model through a specific embodiment.

[0055] like Figure 1The figure shows a schematic diagram of the structure of the electromechanical integrated controller for a helicopter provided in the embodiment. The electromechanical integrated controller is, for example, a control box, through which the control functions of the fuel system, hydraulic system, and fire extinguishing system on the helicopter can be integrated, and the functions of indicator light control, signal acquisition, and communication can be integrated through the MCU chip, with the characteristics of rapid fault location and fault isolation, etc., and the product is light in weight, simple to maintain, and highly reliable.

[0056] The electromechanical integrated controller provided by the embodiment of the utility model includes: a power processing module (including DC-DC module 1 and DC-DC module 2), a switch signal acquisition module, an MCU chip and a CAN communication module, as well as a switch assembly and a light guide plate assembly; wherein the switch assembly includes 12 control switches, namely: 1-engine oil cut-off switch, 2-engine oil cut-off switch, front fuel pump switch, rear fuel pump 1 switch, rear fuel pump 2 switch, emergency pump switch, parking brake switch, brake electric pump switch, 1-engine fire extinguishing switch, 2-engine fire extinguishing switch, APU fire extinguishing switch, fire extinguishing level release switch, wherein 1-engine fire extinguishing switch, 2-engine fire extinguishing switch, APU fire extinguishing switch, fire extinguishing level release switch have indicator lights. The structural relationship and functions of the above-mentioned parts are described in detail below:

[0057] (1) Power processing module:

[0058] The power processing module is composed of a DC-DC module 1, a DC-DC module 2, a surge suppression module and a filter module. Two 28V power supplies are provided on the helicopter, which are converged after conversion and isolation by the DC-DC module 1 and the DC-DC module 2, and are processed by the surge suppression module and the filter module in turn to eliminate the surge voltage and peak voltage on the aircraft, and provide a clean and stable working voltage for the back-end electrical equipment.

[0059] like Figure 1 As shown, after being processed by the voltage processing module, the 28V voltage is converted into the 3.3V voltage, 15V and 20V voltage required by the electrical equipment. The 3.3V voltage is used to supply power to the MCU chip and each control switch in the switch assembly respectively, and the 15V or 20V voltage is used to supply power to the indicator lights of the 1st fire extinguishing switch, the 2nd fire extinguishing switch, the APU fire extinguishing switch and the fire extinguishing level release switch respectively.

[0060] (2) Control functions of the fuel system, hydraulic system, and fire extinguishing system:

[0061] Based on the control requirements for the fuel system, hydraulic system, and fire extinguishing system, as well as the requirements for the loads connected in the circuits of the above-mentioned different systems, the switch assembly in this embodiment selects a variety of different types of control switches for logical control. Each type of switch has one or more of the following mechanical properties: two-position, three-position, locking, and self-resetting, which can meet the pilot's requirements for stable control and anti-maloperation protection during flight.

[0062] (3) Display function of the light guide plate assembly:

[0063] Through the internal circuit design of the light guide plate assembly and the selection of light-emitting diode components, the display of blue-white light and night vision green is realized through the diode), the light guide plate assembly receives the corresponding signal to complete the display function of blue-white light and night vision green.

[0064] (4) Light inspection function, used to detect whether the indicator lights of the four designated switches are functioning normally:

[0065] like Figure 1 As shown, the MCU chip in this embodiment adopts, for example, a single-chip microcomputer of model HWD32F103VEELQFP100, which receives a ground signal (i.e., an input signal from the cockpit on board) emitted by a cockpit lighting brightness adjustment mechanism through an electrical connector, and converts the ground signal emitted on board (the ground signal is a given light-on signal) into a ground signal filtered by a power processing module through a photoelectric coupler in the MCU chip (i.e., the filtered ground signal is used to replace the ground signal on board for the stability of the light) to ensure the stability of the ground signal. After the single-chip microcomputer reads the replaced ground signal, it outputs a control signal to each indicator light of the four control switches through the IO port, drives all the indicator lights to light up, and realizes the inspection function of the indicator lights on the four switches.

[0066] After cutting off the ground signal on the machine, the indicator light goes out and the filtered ground signal is not needed.

[0067] During the lamp inspection process, the red and yellow lights of the indicator light are on together.

[0068] (5) Day and night conversion function for the indicator light on the specified control switch:

[0069] like Figure 1As shown, the MCU chip in this embodiment adopts a single-chip microcomputer of model HWD32F103VEELQFP100, receives the day and night brightness conversion signal (i.e., the input signal from the cockpit on the aircraft, ground signal / + high level signal, representing night / day respectively) issued by the cockpit lighting brightness adjustment mechanism through an electrical connector, converts the day and night brightness conversion signal issued on the aircraft into a corresponding signal filtered by the power supply processing module through the photoelectric coupler of the MCU chip, and after the single-chip microcomputer reads the day brightness signal (high level signal), it outputs a control signal to the relay through the IO port, and provides a (20±1)VDC voltage of the red light and / or the yellow light through the relay conversion. After the single-chip microcomputer reads the night brightness signal (low signal), it outputs a control signal to the relay through the IO port, and provides a (15±0.5)VDC voltage of the red light and / or the yellow light through the relay conversion, thereby realizing the day and night conversion function.

[0070] (6)Signal acquisition function:

[0071] The switch status acquisition module has a photocoupler, which determines the status of the corresponding control switch by reading and judging whether the corresponding IO port input of the MCU chip is high or low. Immediately after the system is powered on, the IO port inside the MCU chip is initialized, and then a loop is entered to determine the status of the 12 control switches in turn.

[0072] The function of the photoelectric coupler is to convert the level signal of the control switch into a level signal output to the IO port, which is then collected by the switch status acquisition module to determine the switch status.

[0073] (7) The switches used in the switch assembly are of two types: two-position switches and three-position switches.

[0074] like Figure 2 , which is a schematic diagram of state judgment of a two-position switch in an embodiment of the utility model.

[0075] When making a two-position switch judgment, the 3.3V high level is connected to one end of the 10KΩ current limiting resistor, and the other end of the current limiting resistor is connected to one end of the switch auxiliary contact (such as Figure 2 The left end of 1A in the figure), the other end of the auxiliary contact of the switch (the right end of 1A) is connected to the corresponding IO port by selecting 3A or 2A. For example, when the level of the 3A port is detected, when 1A is connected to 3A, the IO port detects a high level signal and determines that the switch is in the off state; when 1A is connected to 2A, the IO port detects a low level and determines that the switch is in the on state.

[0076] like Figure 3 , which is a schematic diagram of the state judgment of the three-position switch in the embodiment of the utility model, Figure 3 Figure a is the on state, figure b is the off state, and figure c is the automatic state; Figure 3 It can be seen that the three-position switch has two groups, upper and lower, each group has 4 switch positions. Figure b is the initial state. When the upper group is dialed, the 4 switch positions of the lower group switch positions, and when the lower group is dialed, the 4 switch positions of the upper group switch positions.

[0077] When making a three-position switch judgment, Figure 3 As shown in Figure b, the initial state of the switch is that 1A and 1B in the auxiliary contacts normally input a 3.3V high-level signal, 2A and 2B output a high-level signal, and 3A and 3B are both in a high-impedance state, and the switch state is determined to be disconnected at this time; after the three-position switch is turned up, as shown in Figure a, when 2A and 3B collect a high level, 3A and 2B are both in a high-impedance state, and the switch state is determined to be connected at this time; after the three-position switch is turned down, as shown in Figure c, when 2B and 3A collect a high level, 2A and 3B are both in a high-impedance state, and the switch state is determined to be automatic at this time; if 3A and 3B are both high levels, the switch state is determined to be faulty at this time.

[0078] When the states of the 12 control switches in the switch assembly are collected, the collected data packets are stored in the sending buffer and wait for data transmission.

[0079] (8) CAN communication function, which sends the collected switch status in the form of data packets

[0080] The CAN communication function is realized by the CAN controller built into the MCU chip and the external CAN transceiver. The software design of the CAN communication module mainly includes two parts, namely the node initialization program and the message sending program. After the system is powered on, the configuration of the working mode, baud rate, priority, etc. is completed according to the CAN communication requirements of the onboard system. Then the collected switch status data is assigned to the structure sent by the CAN according to the format, and the library function is called to write the content to the sending mailbox to complete the data sending.

[0081] Although the implementation methods disclosed in the utility model are as above, the content is only an implementation method adopted to facilitate the understanding of the utility model, and is not used to limit the utility model. Any technician in the field to which the utility model belongs can make any modifications and changes in the form and details of implementation without departing from the spirit and scope disclosed in the utility model, but the scope of patent protection of the utility model shall still be based on the scope defined in the attached claims.

Claims

1. An electromechanical integrated controller for a helicopter, characterized in that: include: Power processing module, switch signal acquisition module, MCU chip and CAN communication module, and switch components; The helicopter's onboard power supply is connected to the power processing module, which is respectively connected to the MCU chip, each control switch in the switch assembly, and the indicator lights of each designated control switch in the switch assembly. The power processing module converts and processes the power to form a working voltage for supplying power to the back-end circuit devices. Each control switch in the switch assembly is connected to the IO port corresponding to the MCU chip through the switch signal acquisition module, and the input level of the corresponding IO port on the MCU chip is read and judged by the switch signal acquisition module to judge the state of each control switch in the switch assembly; wherein the control switch in the switch assembly is set based on the control requirements of the fuel system, the hydraulic system, and the fire extinguishing system and the requirements of the load connected in the circuit of each system; The MCU chip is also connected to the CAN communication module to send the collected status of each control switch to the avionics system in the form of a data packet; The MCU chip is also connected to the indicator lights of each designated switch, and is used to drive all the indicator lights of each designated switch to light up through the input signal of the cockpit on the receiver, thereby realizing the inspection function of the indicator lights equipped with each designated switch, or, through the brightness conversion signal of the cockpit on the receiver, output different voltages to the indicator lights of the designated control switches, thereby realizing the day and night conversion function of the indicator lights.

2. The electromechanical integrated controller for a helicopter according to claim 1, characterized in that: The power processing module includes: a DC-DC module 1, a DC-DC module 2, a surge suppression module and a filter module; Among them, the two power supplies on the helicopter are converted and isolated by DC-DC module 1 and DC-DC module 2 respectively, and then converged. They are processed by surge suppression module and filter module in turn to eliminate surge voltage and peak voltage on the aircraft, and provide the required working voltage for each back-end circuit device.

3. The electromechanical integrated controller for a helicopter according to claim 1, characterized in that: Also includes: A light guide plate assembly, comprising: a light guide plate, and a blue-white light source and a night vision green light source built into the light guide plate and connected in parallel; The light guide plate of the light guide plate assembly is arranged on the back side of the switch assembly, serving as the backlight plate of each control switch in the switch assembly; wherein, the onboard power supply is selectively connected to the positive pole of the blue-white light source and the night vision green light source through the internal circuit of the light guide plate assembly, and its negative pole is grounded; so as to receive the corresponding signal through the light guide plate assembly to complete the display function of blue-white light and night vision green.

4. The electromechanical integrated controller for a helicopter according to claim 1, characterized in that: The designated control switches in the switch assembly include: 1-engine fire extinguishing switch, 2-engine fire extinguishing switch, APU fire extinguishing switch, and fire extinguishing level release switch; The electromechanical integrated controller is used to convert the ground signal sent from the aircraft into a ground signal filtered by the power processing module through the photoelectric coupler in the MCU chip when the MCU chip receives a low signal sent from the cockpit on the aircraft, and output a control signal to each indicator light of the four control switches through the IO port of the MCU chip to drive all the indicator lights to light up, thereby realizing the inspection function of the indicator lights on the four switches.

5. The electromechanical integrated controller for a helicopter according to claim 4, characterized in that: The indicator lights of each designated control switch include red and yellow lights; The electromechanical integrated controller is also used to convert the day and night brightness conversion signal issued by the aircraft into a corresponding signal filtered by the power processing module through the photoelectric coupler of the MCU chip when the MCU chip receives the day and night brightness conversion signal issued by the cockpit on the aircraft. After reading the day brightness signal, a (20±1)VDC voltage is provided to the light and / or the yellow light through the IO port. After reading the night brightness signal, a (15±0.5)VDC voltage is provided to the light and / or the yellow light through the IO port, thereby realizing the day and night conversion function.

6. The electromechanical integrated controller for a helicopter according to any one of claims 1 to 5, characterized in that: The switch assembly is provided with a plurality of different types of control switches, and each type of control switch has at least one of the mechanical properties of two-position, three-position, locking, and self-resetting.

7. The electromechanical integrated controller for a helicopter according to claim 6, characterized in that: The emergency pump switch and brake electric pump switch use three-position switches, and other switches except the emergency pump switch and brake electric pump switch use two-position switches; The electromechanical integrated controller is used to perform state determination of a two-position switch. When the IO port of the MCU chip detects a high-level signal, the corresponding switch is determined to be in an off state; when the IO port detects a low level, the corresponding switch is determined to be in an on state. The electromechanical integrated controller is used to perform state determination of the three-position switch, and determines whether the switch is in the disconnected, connected or automatic state by detecting the output level signals of the corresponding points in the upper and lower groups of the three-position switch.

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