Multi-rotor unmanned aerial vehicle flight control integrated circuit mainboard

Abstract

The invention relates to the technical field of unmanned aerial vehicle flight control circuit boards, in particular to a multi-rotor unmanned aerial vehicle flight control integrated circuit mainboard which comprises a PCB circuit substrate, and a data operation main chip, a pair of motion tracking modules, a main chip data transmission interface, an air pressure sensor and an electronic speed controller port are carried in the center of the upper surface of the PCB circuit substrate. The digital image transmission signal module comprises a transmission port and a GPS positioning system signal transmission port; the lower surface of the PCB circuit substrate is provided with two groups of high-frequency synchronous rectification step-down switch conversion modules, an analog diagram transmission OSD module, a flight data storage module and a gyroscope power supply management module, and is provided with a camera input port, an analog transmission signal module transmission port, a buzzer power supply port, an LED control power supply port and a remote control signal receiving port; and a pair of steering engine servo devices control output and power supply ports. According to the multi-rotor unmanned aerial vehicle, the flight performance, stability and functionality of the multi-rotor unmanned aerial vehicle are remarkably improved, and many defects in the prior art are effectively overcome.

Description

Technical Field

[0001] The present invention relates to the technical field of UAV flight control circuit boards, and particularly to a multi-rotor UAV flight control integrated circuit main board. Background Art

[0002] As a high-tech device widely used in fields such as aerial photography, agriculture, logistics, search and rescue, etc., the performance of the flight control system of a multi-rotor UAV directly determines the stability, reliability and functionality of the UAV. The flight control integrated circuit main board, as the core component of the UAV, is responsible for processing sensor data, executing control algorithms, managing power distribution, and realizing communication with external devices. However, most of the existing multi-rotor UAV flight control main boards have the following defects in design and function:

[0003] Firstly, the sensors (such as gyroscopes, barometers, etc.) used in traditional flight control main boards have low accuracy and are easily affected by the environment, resulting in inaccurate attitude measurement and altitude control, and affecting flight stability.

[0004] Secondly, most of the remote control signal receiving modules of the existing main boards adopt a single protocol (such as PPM or SBUS), and the signal transmission delay is relatively high, making it difficult to meet the real-time control requirements of high-dynamic flight scenarios.

[0005] Thirdly, the existing main boards have limited interfaces and it is difficult to be compatible with a variety of external devices (such as high-definition cameras, AI computing modules, etc.), which limits the function expansion and application scenarios of the UAV.

[0006] In addition, most of the main boards adopt a double-layer PCB design, and the signal routing and power distribution layers are limited, which is prone to electromagnetic interference and affects signal integrity and system stability.

[0007] Therefore, there is an urgent need for a new type of multi-rotor UAV flight control integrated circuit main board to provide an effective solution to the defects of the existing technology. Summary of the Invention

[0008] The purpose of the present invention is to provide a multi-rotor UAV flight control integrated circuit main board to solve the problems raised in the above background art.

[0009] To achieve the above purpose, the present invention provides the following technical solutions:

[0010] A flight control integrated circuit main board for a multi-rotor drone, comprising a PCB circuit substrate, on the center position of the upper surface of the PCB circuit substrate, a main data operation chip, a first motion tracking module, a second motion tracking module, a main chip data transmission interface and a barometric pressure sensor are mounted; on the rear side of the upper surface of the PCB circuit substrate, an ESC port is provided, on the front side of the upper surface of the PCB circuit substrate, a digital image transmission signal module transmission port and a GPS positioning system signal transmission port are provided; on the lower surface of the PCB circuit substrate, two groups of high-frequency synchronous rectification step-down switching conversion modules, an analog video transmission OSD module, a flight data storage module and a gyroscope power management module are provided; on the left side of the lower surface of the PCB circuit substrate, a camera input port and an analog transmission signal module transmission port are provided, on the right side of the lower surface of the PCB circuit substrate, a buzzer power supply port and an LED lamp control color change and power supply port are provided, on the front side of the lower surface of the PCB circuit substrate, a remote control signal receiving port, a first servo control output and power supply port and a second servo control output and power supply port are provided.

[0011] Further, the remote control signal receiving port includes an SBUS receiver port, a PPM receiver port and an ELRS receiver and CRSF receiver port.

[0012] Further, the first motion tracking module and the second motion tracking module are both ICM42688 gyroscopes or BMI270 gyroscopes.

[0013] Further, the main data operation chip is an H743 chip, and the H743 chip can be extended with different software firmwares to be used as an AI computing main board.

[0014] Further, the barometric pressure sensor is a BMP280 high-precision barometric pressure sensor.

[0015] Further, the high-frequency synchronous rectification step-down switching conversion module is an MP9943 synchronous rectification BEC.

[0016] Further, a TVS transient voltage suppression diode is also provided on the lower surface of the PCB circuit substrate.

[0017] Further, the flight control integrated circuit main board for the multi-rotor drone adopts a four-layer PCB circuit board structure.

[0018] Compared with the prior art, the beneficial effects of the present invention are:

[0019] 1. In the present invention, the motion tracking module uses a pair of ICM42688 gyroscopes or BMI270 gyroscopes, providing attitude balance and stability control for the aircraft, effectively reducing the malfunction of the aircraft caused by errors in the components themselves during flight. This improves the stability and reliability of flight performance; the main data operation chip 15 uses H743 as the main chip, which has sufficient computing power surplus and can expand different software firmware, or serves as an AI computing mainboard, greatly enhancing the performance and expandability of the flight control mainboard;

[0020] 2. The present invention integrates SBUS, PPM, and ELRS / CRSF ports, supports multiple remote control protocols, reduces signal latency, and meets the requirements of high-dynamic flight;

[0021] 3. The present invention uses an MP9943 synchronous rectifier BEC and a gyroscope power management module to optimize power distribution, improve system energy efficiency, and extend the battery life;

[0022] 4. The present invention integrates TVS transient suppression diodes, effectively absorbing surge voltage and protecting the system from lightning strikes and electrostatic interference;

[0023] 5. The present invention adopts a four-layer PCB circuit board design to optimize signal routing and power distribution, reduce electromagnetic interference, and improve system stability and mechanical strength. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is a front structural schematic diagram of a flight control integrated circuit mainboard for a multi-rotor unmanned aerial vehicle;

[0025] Figure 2 It is a back structural schematic diagram of a flight control integrated circuit mainboard for a multi-rotor unmanned aerial vehicle;

[0026] Figure 3 It is a front wiring diagram of a flight control integrated circuit mainboard for a multi-rotor unmanned aerial vehicle;

[0027] Figure 4 It is a back wiring diagram of a flight control integrated circuit mainboard for a multi-rotor unmanned aerial vehicle;

[0028] Figure 5 It is the top layer of the hierarchical circuit of a flight control integrated circuit mainboard for a multi-rotor unmanned aerial vehicle;

[0029] Figure 6 It is the middle upper layer of the hierarchical circuit of a flight control integrated circuit mainboard for a multi-rotor unmanned aerial vehicle;

[0030] Figure 7 It is the middle lower layer of the hierarchical circuit of a flight control integrated circuit mainboard for a multi-rotor unmanned aerial vehicle;

[0031] Figure 8It is the bottom layer of the hierarchical circuit of a flight control integrated circuit main board for a multi-rotor UAV;

[0032] Figure 9 It is the schematic diagram of the main data operation chip in a flight control integrated circuit main board for a multi-rotor UAV;

[0033] Figure 10 It is the schematic diagram of each sensor in a flight control integrated circuit main board for a multi-rotor UAV;

[0034] Figure 11 It is the power supply schematic diagram of a flight control integrated circuit main board for a multi-rotor UAV;

[0035] Figure 12 It is the schematic diagram of each port in a flight control integrated circuit main board for a multi-rotor UAV.

[0036] In the figure: 1. Camera input port; 2. Transmission port of analog signal module; 3. Buzzer power supply port; 4. LED light control color change and power supply port; 5. SBUS receiver port; 6. PPM receiver port; 7. ELRS receiver and CRSF receiver port; 8. Control output and power supply port of the first servo; 9. Control output and power supply port of the second servo; 10. ESC port; 11. Transmission port of digital image transmission signal module; 12. GPS positioning system signal transmission port; 13. Main chip data transmission interface; 14. Barometric pressure sensor; 15. Main data operation chip; 16. First motion tracking module; 17. Second motion tracking module; 18. High-frequency synchronous rectification buck switching module; 19. TVS transient suppression diode; 20. Analog video transmission OSD module; 21. Flight data storage module; 22. Gyroscope power management module. Specific implementation mode

[0037] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0038] Embodiment 1: Please refer to Figures 1 to 12A flight control integrated circuit main board for a multi-rotor unmanned aerial vehicle, comprising a PCB circuit substrate, on the center position of the upper surface of the PCB circuit substrate, a main data operation chip 15, a first motion tracking module 16, a second motion tracking module 17, a main chip data transmission interface 13 and a barometric pressure sensor 14 are mounted; on the rear side of the upper surface of the PCB circuit substrate, an electronic speed controller port 10 is provided, on the front side of the upper surface of the PCB circuit substrate, a digital image transmission signal module transmission port 11 and a GPS positioning system signal transmission port 12 are provided; on the lower surface of the PCB circuit substrate, two groups of high-frequency synchronous rectification step-down switching conversion modules 18, an analog video transmission OSD module 20, a flight data storage module 21 and a gyroscope power management module 22 are provided; on the left side of the lower surface of the PCB circuit substrate, a camera input port 1 and an analog transmission signal module transmission port 2 are provided, on the right side of the lower surface of the PCB circuit substrate, a buzzer power supply port 3 and an LED lamp control color change and power supply port 4 are provided, on the front side of the lower surface of the PCB circuit substrate, a remote control signal receiving port, a first servo driver control output and a power supply port 8 and a second servo driver control output and a power supply port 9 are provided.

[0039] The working principle of this embodiment:

[0040] The main data operation chip 15, as the core processor, is responsible for receiving and processing data from various sensors. The main chip exchanges data with other modules through the main chip data transmission interface 13 to ensure the real-time and accuracy of information. The first motion tracking module 16 and the second motion tracking module 17 use sensors such as gyroscopes and accelerometers to monitor the attitude changes of the drone in real time. These data are transmitted to the main chip 15, and the main chip calculates the required adjustment instructions according to the algorithm and sends them to the electronic speed controller through the electronic speed controller port 10, thereby controlling the rotation speed of the motor to achieve the attitude balance and stable flight of the drone. The barometric pressure sensor 14 is used to measure the height change of the drone, and the GPS positioning system signal transmission port 12 receives satellite signals to determine the position information of the drone. These data help the drone maintain a stable height and precise positioning during flight. The digital image transmission signal module transmission port 11 and the analog video transmission OSD module 20 are responsible for transmitting the image data captured by the camera to the ground station or display device, and at the same time superimposing flight data such as height and speed on the image for the operator to monitor in real time. The two groups of high-frequency synchronous rectification buck switching modules 18 and the gyroscope power management module 22 are responsible for providing stable power supply for each module to ensure the reliability of system operation. The flight data storage module 21 is used to record key data during flight, such as flight trajectory, sensor data, etc., for subsequent analysis and troubleshooting. Interfaces such as the camera input port 1, the analog signal module transmission port 2, the buzzer power supply port 3, the LED light control color change and power supply port 4, the remote control signal receiving port, the first servo control output and power supply port 8, and the second servo control output and power supply port 9 are used to connect and control external devices such as cameras, buzzers, LED lights, and servos to expand the functions of the drone.

[0041] In this embodiment, the main board integrates multiple functional modules such as GPS positioning, image transmission, and barometric pressure sensors, reducing the dependence on external devices, simplifying the system structure, and reducing the overall weight and power consumption. The high-frequency synchronous rectification buck switching module 18 and the gyroscope power management module 22 ensure stable power supply for each module of the system, improving the energy efficiency ratio and endurance of the system. The rich interfaces enable the drone to easily connect and control various external devices, enhancing the scalability and applicability of the system. Through the highly integrated design and advanced hardware configuration in this embodiment, the flight performance, stability, and functionality of the drone are significantly improved, making it suitable for various complex flight tasks and application scenarios.

[0042] Embodiment 2: Please refer to Figure 4 , a flight control integrated circuit main board for a multi-rotor drone, which is different from Embodiment 1 in that the remote control signal receiving port includes an SBUS receiver port 5, a PPM receiver port 6, and an ELRS receiver and CRSF receiver port 7.

[0043] In this embodiment, the remote control signal receiving ports include the SBUS receiver port 5, the PPM receiver port 6, and the ELRS / CRSF receiver port 7. These ports receive signals from different remote control protocols such as SBUS, PPM, and ELRS / CRSF respectively, and decode them into standard control instructions. The decoded control instructions are transmitted to the main data operation chip 15 through the main chip data transmission interface 13, and the main chip adjusts the flight state of the drone such as attitude, speed, direction, etc. according to the instructions. The ELRS / CRSF receiver port 7 supports the high-frequency and low-latency ELRS and CRSF protocols, which are suitable for long-distance and high-precision control requirements, while the SBUS 5 and PPM 6 ports are compatible with traditional remote control devices, providing flexible connection options.

[0044] In this embodiment, through the SBUS 5, PPM 6, and ELRS / CRSF 7 ports, it is compatible with multiple remote control protocols, meeting the needs of different users and enhancing the versatility and flexibility of the system; the LRS / CRSF port 7 supports high-frequency communication, significantly reducing signal latency and improving the real-time performance and accuracy of flight control; the SBUS and PPM ports 5 and 6 use single-wire transmission, reducing the wiring complexity, lowering the system weight and failure rate; the ELRS / CRSF port 7 supports long-distance communication, expanding the control range of the drone and being suitable for large-scale operation scenarios

[0045] Embodiment 3: Please refer to Figure 1 , a flight control integrated circuit main board for a multi-rotor drone, which is different from Embodiment 1 in that both the first motion tracking module 16 and the second motion tracking module 17 are ICM42688 gyroscopes or BMI270 gyroscopes.

[0046] In this embodiment, both the first motion tracking module 16 and the second motion tracking module 17 adopt ICM42688 gyroscopes or BMI270 gyroscopes, providing attitude balance and stability control for the aircraft, effectively improving the situation where the aircraft malfunctions due to errors caused by the components themselves during flight. It improves the stability and reliability of flight performance.

[0047] Embodiment 4: Please refer to Figure 1 , a flight control integrated circuit main board for a multi-rotor drone, which is different from Embodiment 1 in that the main data operation chip 15 is an H743 chip, and the H743 chip can expand different software firmwares and be used as an AI computing main board.

[0048] In this embodiment, the main data operation chip 15 uses H743 as the main chip, which has more computing power surplus and can expand different software firmwares, or be used as an AI computing main board, greatly enhancing the performance and scalability of the flight control main board.

[0049] Embodiment 5: Please refer toFigure 1 , A flight control integrated circuit main board for a multi-rotor drone, which is different from that of Embodiment 1 in that the barometric pressure sensor 14 is a BMP280 high-precision barometric pressure sensor.

[0050] In this embodiment, the pressure sensor 14 uses a BMP280 high-precision barometric pressure sensor. The BMP280 barometric pressure sensor 14 has a high resolution of ±0.12 hPa and low noise characteristics, and can accurately measure the barometric pressure change, so as to provide accurate altitude data, which is suitable for the altitude-keeping flight and precise landing of the drone.

[0051] Embodiment 6: Please refer to Figure 2 , A flight control integrated circuit main board for a multi-rotor drone, which is different from that of Embodiment 1 in that the high-frequency synchronous rectification buck switching module 18 is an MP9943 synchronous rectification BEC.

[0052] In this embodiment, the MP9943 has excellent load and linear regulation performance, which helps to ensure the stable power supply of various electronic components in the drone flight control system, thereby improving the operation efficiency and stability of the entire system. The MP9943 uses a space-saving QFN-83mmx3mm package, which minimizes the number of external components used, makes the layout of the drone flight control integrated circuit main board more flexible, helps to reduce the volume and weight of the drone, improves the flight performance of the drone, and the MP9943 adopts a current control mode to provide fast transient response.

[0053] Embodiment 7: Please refer to Figure 2 , A flight control integrated circuit main board for a multi-rotor drone, which is different from that of Embodiment 1 in that a TVS transient voltage suppression diode 19 is also provided on the lower surface of the PCB circuit board.

[0054] In this embodiment, the TVS transient voltage suppression diode 19 can effectively absorb the surge voltage, protect the circuit from the impact of transient overvoltages such as lightning strikes and electrostatic discharges, and ensure the stable operation of the flight control system. At the same time, the TVS diode has a fast response speed and a small volume, and does not occupy too much space, providing a reliable and compact circuit protection solution for the drone.

[0055] Embodiment 8: Please refer to Figures 5 to 8 , A flight control integrated circuit main board for a multi-rotor drone, which is different from that of Embodiment 1 in that the flight control integrated circuit main board of the multi-rotor drone adopts a four-layer PCB circuit board structure.

[0056] In this embodiment, the four-layer PCB circuit board structure provides a richer signal routing layer and power / signal ground layer, effectively improving signal integrity and power supply stability, reducing electromagnetic interference, and ensuring the accurate transmission and processing of flight control commands. At the same time, it enhances the mechanical strength and heat dissipation performance of the main board, providing a more reliable and stable hardware foundation for UAV flight control.

Claims

1. A multi-rotor UAV flight control integrated circuit motherboard, characterized in that: It comprises a PCB circuit substrate, wherein a data operation main chip (15), a first motion tracking module (16), a second motion tracking module (17), a main chip data transmission interface (13) and an air pressure sensor (14) are mounted at the center of the upper surface of the PCB circuit substrate; an electric adjustment port (10) is arranged at the rear side of the upper surface of the PCB circuit substrate, and a digital image transmission signal module transmission port (11) and a GPS positioning system signal transmission port (12) are arranged at the front side of the upper surface of the PCB circuit substrate; The lower surface of the PCB circuit substrate is provided with two groups of high-frequency synchronous rectification step-down switch conversion modules (18), an analog image transmission OSD module (20), a flight data storage module (21) and a gyroscope power management module (22); the left side of the lower surface of the PCB circuit substrate is provided with a camera input port (1) and an analog signal transmission module transmission port (2); the right side of the lower surface of the PCB circuit substrate is provided with a buzzer power supply port (3) and an LED light color change control and power supply port (4); the front side of the lower surface of the PCB circuit substrate is provided with a remote control signal receiving port, a first steering gear servo control output and power supply port (8) and a second steering gear servo control output and power supply port (9).

2. A multi-rotor UAV flight control integrated circuit motherboard according to claim 1, characterized in that: The remote control signal receiving port comprises an SBUS receiver port (5), a PPM receiver port (6) and an ELRS receiver and CRSF receiver port (7).

3. The multi-rotor UAV flight control integrated circuit motherboard according to claim 1, characterized in that: The first motion tracking module (16) and the second motion tracking module (17) are both ICM42688 gyroscopes or BMI270 gyroscopes.

4. The multi-rotor UAV flight control integrated circuit motherboard according to claim 1, characterized in that: The data computing main chip (15) is an H743 chip, which can be extended with different software firmware and serve as an AI computing mainboard.

5. The multi-rotor UAV flight control integrated circuit motherboard according to claim 1, characterized in that: The air pressure sensor (14) is a BMP280 high-precision air pressure sensor.

6. The multi-rotor UAV flight control integrated circuit motherboard according to claim 1, characterized in that: The high-frequency synchronous rectification step-down switch conversion module (18) is an MP9943 synchronous rectification BEC.

7. The multi-rotor UAV flight control integrated circuit motherboard according to claim 1, characterized in that: A TVS transient suppression diode (19) is also provided on the lower surface of the PCB circuit substrate.

8. The multi-rotor UAV flight control integrated circuit motherboard according to claim 7, characterized in that: It adopts a four-layer PCB circuit board structure.

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