Integrated avionics control device

Abstract

The utility model discloses an integrated avionics control device. The integrated avionics control device comprises a main control module, a posture detection module, an air pressure detection module and a motor driving module, the master control module comprises a microprocessor U1. The attitude detection module comprises an inertial sensor U2, and the No.12 end of the inertial sensor U2 is electrically connected with the No.41 end of the microprocessor U1. The air pressure detection module comprises an air pressure sensor U3, the third end of the air pressure sensor U3 is electrically connected with the 24 end of an inertial sensor U2 and the 43 end of a microprocessor U1 at the same time, and the fourth end of the air pressure sensor U3 is electrically connected with the 23 end of the inertial sensor U2 and the 42 end of the microprocessor U1 at the same time. The integrated avionics control device disclosed by the utility model has the beneficial effects that the main control module, the attitude detection module, the air pressure detection module and the motor driving module are simultaneously integrated on the control circuit board of the four-axis unmanned aerial vehicle, so that the integration degree of the four-axis unmanned aerial vehicle is effectively improved, and the avionics control of the four-axis unmanned aerial vehicle is facilitated.

Description

Technical Field

[0001] This utility model belongs to the field of unmanned aerial vehicle (UAV) control, specifically relating to an integrated avionics control device. Background Technology

[0002] The patent, with publication number CN217767259U and subject title "A Utility Model Patent for a Highly Integrated Avionics Control System," and IPC classification numbers G05D1 / 08 and G05D1 / 10, discloses a "highly integrated avionics control system comprising: a central control unit connected to an air data acquisition unit and an integration unit, receiving signal data from the air data acquisition unit and the integration unit; an air data acquisition unit including a data acquisition module connected to the central control unit; an integration unit including a flight control system, a navigation system, an engine control system, and an image transmission system, wherein the flight control system, navigation system, engine control system, and image transmission system are respectively connected to the central control system; a display control unit including a host connected to the central control unit and a display device connected to the host, wherein the host receives key control parameters from the central control unit and displays them on the display device; and a power management unit connected to the central control unit, the air data acquisition unit, the flight control integration unit, and the display control unit."

[0003] Therefore, the above utility model patents have disclosed one technical solution for an integrated avionics control system. However, the technical solution disclosed in the above utility model patents does not disclose the main circuit structure and requires further improvement. Utility Model Content

[0004] This utility model addresses the shortcomings of the existing technology by providing an integrated avionics control device.

[0005] This utility model adopts the following technical solution: an integrated avionics control device, comprising a main control module, an attitude detection module, a barometric pressure detection module, and a motor drive module, wherein:

[0006] The main control module includes a microprocessor U1;

[0007] The attitude detection module includes an inertial sensor U2, and pin 12 of the inertial sensor U2 is electrically connected to pin 41 of the microprocessor U1.

[0008] The air pressure detection module includes an air pressure sensor U3. Terminal 3 of the air pressure sensor U3 is electrically connected to terminal 24 of the inertial sensor U2 and terminal 43 of the microprocessor U1. Terminal 4 of the air pressure sensor U3 is electrically connected to terminal 23 of the inertial sensor U2 and terminal 42 of the microprocessor U1.

[0009] The motor drive module includes a first-axis drive motor M1, a second-axis drive motor M2, a third-axis drive motor M3, and a fourth-axis drive motor M4, as well as a first MOSFET Q1, a second MOSFET Q2, a third MOSFET Q3, and a fourth MOSFET Q4. Terminal 2 of the first-axis drive motor M1 is electrically connected to the source of the first MOSFET Q1. The gate of the first MOSFET Q1 is electrically connected to one end of a resistor R7, and the other end of resistor R7 is electrically connected to terminal 16 of the microprocessor U1. Terminal 2 of the second-axis drive motor M2 is electrically connected to the source of the second MOSFET Q2. The gate of the third axis drive motor M3 is electrically connected to one end of resistor R9, and the other end of resistor R9 is electrically connected to pin 17 of microprocessor U1. Pin 2 of the third axis drive motor M3 is electrically connected to the source of the third MOSFET Q3. The gate of the third MOSFET Q3 is electrically connected to one end of resistor R11, and the other end of resistor R11 is electrically connected to pin 18 of microprocessor U1. Pin 2 of the fourth axis drive motor M4 is electrically connected to the source of the fourth MOSFET Q4. The gate of the fourth MOSFET Q4 is electrically connected to one end of resistor R13, and the other end of resistor R13 is electrically connected to pin 19 of microprocessor U1.

[0010] As a preferred technical solution to the above technical solutions, the integrated avionics control device also includes a color display module, which includes an LED light D2. The negative terminal of the LED light D2 is electrically connected to terminal 45 of the microprocessor U1.

[0011] As a preferred technical solution to the above technical solutions, the color display module further includes a first RGB lamp D4, a second RGB lamp D5, a third RGB lamp D6, and a fourth RGB lamp D7. The second terminal of the first RGB lamp D4 is electrically connected to the first terminal of the microprocessor U1, the fourth terminal of the first RGB lamp D4 is electrically connected to the second terminal of the second RGB lamp D5, the fourth terminal of the second RGB lamp D5 is electrically connected to the second terminal of the third RGB lamp D6, and the fourth terminal of the third RGB lamp D6 is electrically connected to the second terminal of the fourth RGB lamp D7.

[0012] As a preferred technical solution to the above technical solutions, the integrated avionics control device also includes a wireless communication module, which comprises a first radio frequency chip U5 and a second radio frequency chip U7, wherein:

[0013] Terminal 1 of the first RF chip U5 is electrically connected to terminal 3 of the second RF chip U7 and terminal 29 of the microprocessor U1.

[0014] The second terminal of the first RF chip U5 is electrically connected to the fourth terminal of the second RF chip U7 and the 25th terminal of the microprocessor U1.

[0015] The third terminal of the first RF chip U5 is electrically connected to the fifth terminal of the second RF chip U7 and the 26th terminal of the microprocessor U1.

[0016] The 4th terminal of the first RF chip U5 is electrically connected to the 6th terminal of the second RF chip U7 and the 28th terminal of the microprocessor U1.

[0017] The 5th terminal of the first RF chip U5 is electrically connected to the 7th terminal of the second RF chip U7 and the 27th terminal of the microprocessor U1.

[0018] The 6th terminal of the first RF chip U5 is electrically connected to the 8th terminal of the second RF chip U7 and the 20th terminal of the microprocessor U1.

[0019] As a preferred technical solution to the above technical solutions, the integrated avionics control device also includes a power module, which includes a power chip U11. The third terminal of the power chip U11 is electrically connected to the common terminal between the Schottky diode D3 and the capacitor C4.

[0020] As a preferred technical solution to the above technical solutions, the integrated avionics control device also includes a battery voltage detection module. The battery voltage detection module includes resistors R4 and R5 and capacitor C6. One end of capacitor C6 is electrically connected to the common terminal between resistors R4 and R5, and the other end of capacitor C6 is grounded together with resistor R5.

[0021] The integrated avionics control device disclosed in this utility model has the advantage that the main control module, attitude detection module, air pressure detection module and motor drive module are simultaneously integrated on the control circuit board of the quadcopter, which effectively improves the integration level of the quadcopter and facilitates the avionics control of the quadcopter. Attached Figure Description

[0022] Figure 1 This is the circuit schematic of the main control module of this application.

[0023] Figure 2 This is the circuit schematic of the attitude detection module of this application.

[0024] Figure 3 This is a circuit schematic diagram of the color display module of this application.

[0025] Figure 4 This is the circuit schematic of the motor drive module of this application.

[0026] Figure 5 This is the circuit schematic diagram of the wireless communication module of this application.

[0027] Figure 6 This is the circuit diagram of the air pressure detection module of this application.

[0028] Figure 7 This is the circuit schematic of the power module of this application.

[0029] Figure 8 This is a circuit diagram of the battery voltage detection module of this application. Detailed Implementation

[0030] This utility model discloses an integrated avionics control device. The following description, in conjunction with a preferred embodiment (Embodiment 1), refers to the accompanying drawings. Figure 1-8 The specific embodiments of this utility model will be further described below.

[0031] See attached diagram. Figures 1 to 8 , Figures 1 to 8 The circuit structures of the main control module, attitude detection module, color display module, motor drive module, wireless communication module, air pressure detection module, power supply module, and battery voltage detection module of the integrated avionics control device are shown respectively.

[0032] Example 1.

[0033] Preferably, the integrated avionics control device includes a main control module, an attitude detection module, a barometric pressure detection module, and a motor drive module, wherein:

[0034] The main control module includes a microprocessor U1;

[0035] The attitude detection module includes an inertial sensor U2, and pin 12 of the inertial sensor U2 is electrically connected to pin 41 of the microprocessor U1.

[0036] The air pressure detection module includes an air pressure sensor U3. Terminal 3 of the air pressure sensor U3 is electrically connected to terminal 24 of the inertial sensor U2 and terminal 43 of the microprocessor U1. Terminal 4 of the air pressure sensor U3 is electrically connected to terminal 23 of the inertial sensor U2 and terminal 42 of the microprocessor U1.

[0037] The motor drive module includes a first-axis drive motor M1, a second-axis drive motor M2, a third-axis drive motor M3, and a fourth-axis drive motor M4, as well as a first MOSFET Q1, a second MOSFET Q2, a third MOSFET Q3, and a fourth MOSFET Q4. Terminal 2 of the first-axis drive motor M1 is electrically connected to the source of the first MOSFET Q1. The gate of the first MOSFET Q1 is electrically connected to one end of a resistor R7, and the other end of resistor R7 is electrically connected to terminal 16 of the microprocessor U1. Terminal 2 of the second-axis drive motor M2 is electrically connected to the source of the second MOSFET Q2. The gate of the third axis drive motor M3 is electrically connected to one end of resistor R9, and the other end of resistor R9 is electrically connected to pin 17 of microprocessor U1. Pin 2 of the third axis drive motor M3 is electrically connected to the source of the third MOSFET Q3. The gate of the third MOSFET Q3 is electrically connected to one end of resistor R11, and the other end of resistor R11 is electrically connected to pin 18 of microprocessor U1. Pin 2 of the fourth axis drive motor M4 is electrically connected to the source of the fourth MOSFET Q4. The gate of the fourth MOSFET Q4 is electrically connected to one end of resistor R13, and the other end of resistor R13 is electrically connected to pin 19 of microprocessor U1.

[0038] It should be noted that the attitude detection module's inertial sensor U2 outputs an inertial attitude signal at pin 12, and the barometric pressure detection module's barometric pressure sensor U3 outputs a barometric pressure signal at pin 3. The microprocessor U1 simultaneously acquires both the inertial attitude signal and the barometric pressure signal and simultaneously outputs the first axis drive signal, the second axis drive signal, the third axis drive signal, and the fourth axis drive signal. The first axis drive motor M1's pin 2 acquires the first axis drive signal through the first MOSFET Q1, the second axis drive motor M2's pin 2 acquires the second axis drive signal through the second MOSFET Q2, the third axis drive motor M3's pin 2 acquires the third axis drive signal through the third MOSFET Q3, and the fourth axis drive motor M4's pin 2 acquires the fourth axis drive signal through the fourth MOSFET Q4. The main control module, attitude detection module, barometric pressure detection module, and motor drive module are all integrated on the quadcopter's control circuit board, effectively improving the quadcopter's integration level and facilitating its avionics control, especially enabling independent flight based on both inertial attitude signals and barometric pressure signals simultaneously.

[0039] The integrated avionics control unit also includes a color display module, which includes an LED light D2. The negative terminal of the LED light D2 is electrically connected to terminal 45 of the microprocessor U1.

[0040] The color display module also includes a first RGB LED D4, a second RGB LED D5, a third RGB LED D6, and a fourth RGB LED D7. Terminal 2 of the first RGB LED D4 is electrically connected to terminal 1 of the microprocessor U1. Terminal 4 of the first RGB LED D4 is electrically connected to terminal 2 of the second RGB LED D5. Terminal 4 of the second RGB LED D5 is electrically connected to terminal 2 of the third RGB LED D6. Terminal 4 of the third RGB LED D6 is electrically connected to terminal 2 of the fourth RGB LED D7.

[0041] Among them, the microprocessor U1 preferably adopts STM32F103C8T6.

[0042] Among them, the inertial sensor U2 is preferably an MPU6050.

[0043] Among them, the barometric pressure sensor U3 is preferably FBM320, BMP280 or SPL06.

[0044] Among them, the first axis drive motor M1 is preferably PH2.0, the second axis drive motor M2 is preferably PH2.0, the third axis drive motor M3 is preferably PH2.0, and the fourth axis drive motor M4 is preferably PH2.0.

[0045] Among them, the first MOSFET Q1 is preferably SI2302, the second MOSFET Q2 is preferably SI2302, the third MOSFET Q3 is preferably SI2302, and the fourth MOSFET Q3 is preferably SI2302.

[0046] Example 2.

[0047] The technical solution of Embodiment 2, based on the technical solution of Embodiment 1, further includes the following technical solutions.

[0048] Preferably, the integrated avionics control device further includes a wireless communication module, which comprises a first radio frequency chip U5 and a second radio frequency chip U7, wherein:

[0049] Terminal 1 of the first RF chip U5 is electrically connected to terminal 3 of the second RF chip U7 and terminal 29 of the microprocessor U1.

[0050] The second terminal of the first RF chip U5 is electrically connected to the fourth terminal of the second RF chip U7 and the 25th terminal of the microprocessor U1.

[0051] The third terminal of the first RF chip U5 is electrically connected to the fifth terminal of the second RF chip U7 and the 26th terminal of the microprocessor U1.

[0052] The 4th terminal of the first RF chip U5 is electrically connected to the 6th terminal of the second RF chip U7 and the 28th terminal of the microprocessor U1.

[0053] The 5th terminal of the first RF chip U5 is electrically connected to the 7th terminal of the second RF chip U7 and the 27th terminal of the microprocessor U1.

[0054] The 6th terminal of the first RF chip U5 is electrically connected to the 8th terminal of the second RF chip U7 and the 20th terminal of the microprocessor U1.

[0055] The integrated avionics control unit also includes a power module, which includes a power chip U11. Terminal 3 of the power chip U11 is electrically connected to the common terminal between the Schottky diode D3 and the capacitor C4.

[0056] The integrated avionics control unit also includes a battery voltage detection module, which includes resistors R4 and R5 and capacitor C6. One end of capacitor C6 is electrically connected to the common terminal between resistors R4 and R5, and the other end of capacitor C6 is grounded together with resistor R5.

[0057] Among them, the first radio frequency chip U5 is preferably Si24R1.

[0058] The second radio frequency chip U7 is preferably an NRF24L01-2.4G.

[0059] Among them, the power chip U11 preferably adopts ME6206A33M3G.

[0060] Among them, the Schottky diode D3 is preferably 1N5819W.

[0061] It is worth mentioning that the specific selection of RGB lights and the possible avionics control methods of the microprocessor U1 involved in this utility model patent application should be regarded as prior art. The specific structure, working principle and possible control methods and spatial arrangement of these technical features can be adopted by conventional choices in the field and should not be regarded as the inventive point of this utility model patent. This utility model patent will not elaborate further.

[0062] For those skilled in the art, modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. An integrated avionics control device, characterized in that, It includes a main control module, an attitude detection module, an air pressure detection module, and a motor drive module, among which: The main control module includes a microprocessor U1; The attitude detection module includes an inertial sensor U2, and pin 12 of the inertial sensor U2 is electrically connected to pin 41 of the microprocessor U1. The air pressure detection module includes an air pressure sensor U3. Terminal 3 of the air pressure sensor U3 is electrically connected to terminal 24 of the inertial sensor U2 and terminal 43 of the microprocessor U1. Terminal 4 of the air pressure sensor U3 is electrically connected to terminal 23 of the inertial sensor U2 and terminal 42 of the microprocessor U1. The motor drive module includes a first-axis drive motor M1, a second-axis drive motor M2, a third-axis drive motor M3, and a fourth-axis drive motor M4, as well as a first MOSFET Q1, a second MOSFET Q2, a third MOSFET Q3, and a fourth MOSFET Q4. Terminal 2 of the first-axis drive motor M1 is electrically connected to the source of the first MOSFET Q1. The gate of the first MOSFET Q1 is electrically connected to one end of a resistor R7, and the other end of resistor R7 is electrically connected to terminal 16 of the microprocessor U1. Terminal 2 of the second-axis drive motor M2 is electrically connected to the source of the second MOSFET Q2. The gate of the third axis drive motor M3 is electrically connected to one end of resistor R9, and the other end of resistor R9 is electrically connected to pin 17 of microprocessor U1. Pin 2 of the third axis drive motor M3 is electrically connected to the source of the third MOSFET Q3. The gate of the third MOSFET Q3 is electrically connected to one end of resistor R11, and the other end of resistor R11 is electrically connected to pin 18 of microprocessor U1. Pin 2 of the fourth axis drive motor M4 is electrically connected to the source of the fourth MOSFET Q4. The gate of the fourth MOSFET Q4 is electrically connected to one end of resistor R13, and the other end of resistor R13 is electrically connected to pin 19 of microprocessor U1.

2. The integrated avionics control device according to claim 1, characterized in that, The integrated avionics control unit also includes a color display module, which includes an LED light D2. The negative terminal of the LED light D2 is electrically connected to pin 45 of the microprocessor U1.

3. The integrated avionics control device according to claim 2, characterized in that, The color display module also includes a first RGB LED D4, a second RGB LED D5, a third RGB LED D6, and a fourth RGB LED D7. Terminal 2 of the first RGB LED D4 is electrically connected to terminal 1 of the microprocessor U1. Terminal 4 of the first RGB LED D4 is electrically connected to terminal 2 of the second RGB LED D5. Terminal 4 of the second RGB LED D5 is electrically connected to terminal 2 of the third RGB LED D6. Terminal 4 of the third RGB LED D6 is electrically connected to terminal 2 of the fourth RGB LED D7.

4. The integrated avionics control device according to claim 1, characterized in that, The integrated avionics control unit also includes a wireless communication module, which comprises a first radio frequency chip U5 and a second radio frequency chip U7, wherein: Terminal 1 of the first RF chip U5 is electrically connected to terminal 3 of the second RF chip U7 and terminal 29 of the microprocessor U1. The second terminal of the first RF chip U5 is electrically connected to the fourth terminal of the second RF chip U7 and the 25th terminal of the microprocessor U1. The third terminal of the first RF chip U5 is electrically connected to the fifth terminal of the second RF chip U7 and the 26th terminal of the microprocessor U1. The 4th terminal of the first RF chip U5 is electrically connected to the 6th terminal of the second RF chip U7 and the 28th terminal of the microprocessor U1. The 5th terminal of the first RF chip U5 is electrically connected to the 7th terminal of the second RF chip U7 and the 27th terminal of the microprocessor U1. The 6th terminal of the first RF chip U5 is electrically connected to the 8th terminal of the second RF chip U7 and the 20th terminal of the microprocessor U1.

5. The integrated avionics control device according to claim 1, characterized in that, The integrated avionics control unit also includes a power module, which includes a power chip U11. Terminal 3 of the power chip U11 is electrically connected to the common terminal between the Schottky diode D3 and the capacitor C4.

6. The integrated avionics control device according to claim 1, characterized in that, The integrated avionics control unit also includes a battery voltage detection module, which includes resistors R4 and R5 and capacitor C6. One end of capacitor C6 is electrically connected to the common terminal between resistors R4 and R5, and the other end of capacitor C6 is grounded together with resistor R5.

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