Flight controller and drone

Abstract

The utility model discloses a flight controller and unmanned aerial vehicle relates to unmanned aerial vehicle technical field, and flight controller includes control panel and power panel, and control panel includes first installation surface and second installation surface of mutual stand arrangement, and first installation surface is used to install main control chip, and power panel includes power installation surface and connecting surface of mutual stand arrangement, and power installation surface is used to install power component, second installation surface and connecting surface weld fixed, control panel with power panel electricity is connected.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a flight controller and a UAV. Background Technology

[0002] As the core control component within a drone, the flight controller performs multiple functions, including flight attitude modification and stabilization, control signal transmission, altitude control, stabilization control, data storage, camera signal transmission, and image transmission. With the increasing variety of drones, especially racing drones, the overall size is shrinking, internal space is decreasing, and the space available for installing and placing external equipment is also shrinking. A large flight controller increases weight and makes installation difficult. Therefore, how to achieve integrated design of the flight controller and reduce its size remains a challenge. Utility Model Content

[0003] The main objective of this invention is to propose a flight controller and a drone, which aims to reduce the size of the flight controller.

[0004] To achieve the above objectives, the present invention proposes a flight controller comprising a control board and a power board. The control board includes a first mounting surface and a second mounting surface disposed opposite to each other. The first mounting surface is used to mount the main control chip. The power board includes a power mounting surface and a connection surface disposed opposite to each other. The power mounting surface is used to mount power components. The second mounting surface is welded and fixed to the connection surface. The control board is electrically connected to the power board.

[0005] In one embodiment, a gyroscope, a storage chip, a video character overlay chip, and a barometer chip are also disposed at intervals on the first mounting surface.

[0006] In one embodiment, a clearance groove is formed circumferentially on the power board, and electronic components are mounted on the second mounting surface of the control board at a position corresponding to the clearance groove.

[0007] In one embodiment, a USB interface, an electronic speed controller socket, and an image transmission module socket are spaced apart on the second mounting surface. The power board is circumferentially spaced with a first clearance slot, a second clearance slot, and a third clearance slot. The USB interface is located in the first clearance slot, the electronic speed controller socket is located in the second clearance slot, and the image transmission module socket is located in the third clearance slot.

[0008] In one embodiment, the power board further forms a fourth air-avoidance slot, and the flight controller further includes a receiver. The receiver includes an antenna mount, an antenna, and a communication chip. The antenna mount and the communication chip are installed at intervals on the first mounting surface corresponding to the fourth air-avoidance slot, and the antenna is connected to the antenna mount.

[0009] In one embodiment, the power board is a rectangular plate, and the first clearance slot, the second clearance slot, the third clearance slot and the fourth clearance slot are respectively distributed on the four sides of the power board.

[0010] In one embodiment, the flight controller further includes a silicone shock absorber, a first mounting hole is formed on the control board, and a second mounting hole is formed on the power board. The first mounting hole and the second mounting hole are correspondingly arranged, and the silicone shock absorber is inserted into the first mounting hole and the second mounting hole.

[0011] In one embodiment, the flight controller further includes a lighting assembly, which includes a light strip pad and a button. The light strip pad is connected to the power mounting surface, and the button is connected to the power mounting surface and electrically connected to the light strip pad.

[0012] This utility model also proposes an unmanned aerial vehicle (UAV), which includes a flight controller. The flight controller includes a control board and a power board. The control board includes a first mounting surface and a second mounting surface on opposite sides. The first mounting surface is used to mount a main control chip. The power board includes a power mounting surface and a connection surface on opposite sides. The power mounting surface is used to mount power components. The second mounting surface is welded and fixed to the connection surface. The control board is electrically connected to the power board.

[0013] This invention proposes a flight controller suitable for flight attitude control, navigation and positioning, and mission execution of various types of drones, including multi-rotor and fixed-wing drones. It processes various sensor data through a main control chip and, combined with a power supply board, achieves stable flight and precise control of the drone. The flight controller includes a control board and a power supply board, both of which are PCB boards. The control board has a rectangular structure, forming a first mounting surface and a second mounting surface on opposite sides. The central area of ​​the first mounting surface is used to mount the main control chip, which is a high-performance microprocessor integrating multiple computing cores and peripheral interfaces. It can quickly process various sensor signals and control commands and is the core computing unit of the flight controller. The power supply board forms a power mounting surface and a connection surface on opposite sides, used to mount power management chips, filter capacitors, voltage conversion modules, and other power components. The power components convert the voltage input from the drone battery into a stable voltage required by various electronic components. The second mounting surface of the control board is soldered to the power board via surface-mount pads or pins. Lead-free solder is used at the solder joints to ensure a strong and conductive connection. The control board and power board are electrically connected via soldered wiring. The stable voltage output from the power board is transmitted to the various electronic components on the control board through these wirings. The control signals from the main control chip can also interact with the power supply components via these wirings, enabling monitoring and control of the power supply status. Two independent PCBs ensure that the control section is not interfered with by the power supply section. This board-to-board soldering method reduces the use of connecting cables, shrinks the overall size of the flight controller, improves structural stability, and avoids malfunctions caused by loose cables. Providing power to the chips on the control board independently via the power board helps protect the internal power supply of the flight controller from external influences, such as power outages caused by external equipment failure, without affecting the internal power supply of the flight controller. This maximizes the protection of critical internal chips and ensures the stability of the flight controller. Attached Figure Description

[0014] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0015] Figure 1 A schematic diagram of the structure of an embodiment of the flight controller provided by this utility model; Figure 2 for Figure 1 Exploded view of the flight controller; Figure 3 for Figure 1Exploded view of the control board and power board; Figure 4 for Figure 1 A schematic diagram of the structure on the other side of the flight controller.

[0016] Explanation of icon numbers: 100. Flight Controller; 1. Control Board; 1a. First Mounting Surface; 1b. Second Mounting Surface; 11. Main Control Chip; 12. Gyroscope; 13. Storage Chip; 14. Video Character Overlay Chip; 15. USB Interface; 16. Electronic Speed ​​Controller Socket; 17. Image Transmission Module Socket; 2. Power Board; 2a. First Clearance Slot; 2b. Second Clearance Slot; 2c. Third Clearance Slot; 2d. Fourth Clearance Slot; 3. Receiver; 31. Antenna Mount; 32. Antenna; 33. Communication Chip; 4. Silicone Shock Absorber; 5. Buttons.

[0017] The realization of the purpose, functional features and advantages of this utility model will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0018] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present utility model.

[0019] It should be noted that if the embodiments of this utility model involve directional indicators (such as up, down, left, right, front, back, etc.), the directional indicators are only used to explain the relative positional relationship and movement of the components in a specific posture. If the specific posture changes, the directional indicators will also change accordingly.

[0020] Furthermore, if the embodiments of this utility model involve descriptions such as "first" or "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the use of "and / or" or "and / or" throughout the text includes three parallel solutions. For example, "A and / or B" includes solution A, solution B, or a solution where both A and B are satisfied simultaneously. Furthermore, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed by this utility model.

[0021] As the core control component within a drone, the flight controller performs multiple functions, including flight attitude modification and stabilization, control signal transmission, altitude control, stabilization control, data storage, camera signal transmission, and image transmission. With the increasing variety of drones, especially racing drones, the overall size is shrinking, internal space is decreasing, and the space available for installing and placing external equipment is also shrinking. A large flight controller increases weight and makes installation difficult. Therefore, how to achieve integrated design of the flight controller and reduce its size remains a challenge.

[0022] To solve the above problems, please refer to... Figures 1 to 4 This utility model proposes a flight controller 100, including a control board 1 and a power board 2. The control board 1 includes a first mounting surface 1a and a second mounting surface 1b arranged opposite to each other. The first mounting surface 1a is used to install the main control chip 11. The power board 2 includes a power mounting surface and a connection surface arranged opposite to each other. The power mounting surface is used to install power components. The second mounting surface 1b is welded and fixed to the connection surface. The control board 1 and the power board 2 are electrically connected.

[0023] This utility model proposes a flight controller 100, suitable for flight attitude control, navigation and positioning, and mission execution of various types of UAVs such as multi-rotor UAVs and fixed-wing UAVs. It processes various sensor data through a main control chip 11, and with the power supply provided by a power board 2, achieves stable flight and precise control of the UAV. The flight controller 100 includes a control board 1 and a power board 2, both of which are PCB boards. The control board 1 has a rectangular plate structure, forming a first mounting surface 1a and a second mounting surface 1b on opposite sides. Both mounting surfaces are copper-plated and have reserved component solder pads and circuit traces. The central area of ​​the first mounting surface 1a is used to mount the main control chip 11. The main control chip 11 is a high-performance microprocessor, integrating multiple computing cores and peripheral interfaces, capable of quickly processing various sensor signals and control commands, and is the core computing unit of the flight controller 100. The power board 2 has power mounting surfaces and connection surfaces on opposite sides. The power mounting surfaces have pre-drilled mounting pads and mounting holes for power components such as power management chips, filter capacitors, and voltage conversion modules. These power components convert the voltage input from the drone battery into a stable voltage required by various electronic components. The second mounting surface 1b of the control board 1 is fixed to the connection surface of the power board 2 via surface mount pads or pins. Lead-free solder is used at the solder joints to ensure a strong and conductive connection. Simultaneously, the control board 1 and power board 2 are electrically connected via soldered lines. The stable voltage output from the power board 2 is transmitted to the various electronic components of the control board 1 through these lines. The control signals from the main control chip 11 can also interact with the power components through these lines, enabling monitoring and control of the power supply status. By combining the control board 1 and power board 2 using surface mount technology, an electrical connection is formed. The two independent PCBs ensure that the control section is not interfered with by the power supply section. This board-to-board welding method reduces the use of connecting cables, shrinks the overall size of the flight controller 100, improves structural stability, and avoids malfunctions caused by loose cables. The tight integration of the power board 2 and the control board 1 shortens the power supply path, reduces voltage loss and electromagnetic interference, and ensures power supply stability and signal transmission efficiency, providing a reliable foundation for the stable flight of the UAV. Furthermore, by supplying power to the chips on the control board 1 independently through the power board 2, the internal power supply of the flight controller 100 is protected from external influences. For example, if external equipment malfunctions and causes power supply abnormalities, it will not affect the internal power supply of the flight controller 100, maximizing the protection of the critical internal chips and ensuring the stability of the flight controller 100.

[0024] Furthermore, in one embodiment, please refer to Figure 1 and Figure 2 The first mounting surface 1a is also provided with a gyroscope 12, a storage chip 13, a video character overlay chip 14 and a barometer chip at intervals.

[0025] On the first mounting surface 1a of the control board 1, there are also gyroscopes 12, storage chips 13 (storage ICs), video character overlay chips 14 (video character overlay ICs), and barometer chips (barometer ICs) spaced apart. Each chip is soldered onto a preset pad using surface mount technology and is electrically connected to the main control chip 11 via on-board wiring. The spaced layout avoids electromagnetic interference and heat dissipation conflicts between chips. The gyroscope 12 can adopt a MEMS (Micro-Electro-Mechanical System) architecture, which can detect the angular velocity and attitude changes of the UAV in real time, convert physical motion into electrical signals, and transmit them to the main control chip 11 to provide data support for the main control chip 11 to adjust the flight attitude. The storage chip 13 uses flash memory chips, which have non-volatile storage characteristics and can store flight control programs, parameter configuration data, and flight logs, ensuring that data is not lost after power failure, facilitating later debugging and fault analysis. The video character overlay chip 14 can convert key information such as flight altitude, speed, battery level, and GPS coordinates into character signals and overlay them onto the video footage captured by the UAV, realizing the synchronous recording and transmission of flight data and video. The barometer chip calculates the relative altitude of the drone by detecting changes in the air pressure of the surrounding environment. Its measurement data is fused with data from the gyroscope 12, improving the accuracy of altitude measurement and providing a basis for the main control chip 11 to achieve altitude-hold flight. All chips work collaboratively with the main control chip 11. The gyroscope 12 and barometer chip collect flight status data in real time, the storage chip 13 records key information, the video character overlay chip 14 expands the data display function, and the main control chip 11 centrally processes all data and outputs control commands, forming a complete flight control data chain. This significantly improves the functional completeness and control accuracy of the flight controller 100, meeting the needs of complex drone flight missions. In other embodiments, other types of chips can also be added according to actual usage requirements.

[0026] In one embodiment, please refer to Figure 3 and Figure 4 The power board 2 has a clearance groove formed around its circumference, and electronic components are installed on the second mounting surface 1b of the control board 1 at the position corresponding to the clearance groove.

[0027] The power board 2 has a circumferential clearance groove, which is a rectangular or arc-shaped notch recessed inward from the edge of the power board 2. This groove is formed using PCB engraving technology, and its size and position are designed according to the layout of electronic components on the control board 1. Electronic components are mounted on the second mounting surface 1b of the control board 1, corresponding to the clearance groove. These components are fixed to the second mounting surface 1b using surface mounting or through-hole mounting methods, ensuring that the electronic components do not interfere with the power board 2 after the control board 1 is soldered to it. The clearance groove design fully utilizes the gap between the power board 2 and the control board 1, allowing for the reasonable arrangement of electronic components on the second mounting surface 1b of the control board 1 without increasing the board area, thus achieving a miniaturized design of the flight controller 100. Simultaneously, the clearance groove creates a certain heat dissipation gap between the electronic components and the power board 2, which is beneficial for heat dissipation and prevents performance degradation due to high temperatures. Furthermore, the clearance groove also avoids the power supply components on the power board 2, reducing electromagnetic coupling between electronic components on different boards, lowering electromagnetic interference, ensuring the normal operation of each component, and improving the overall reliability of the flight controller 100.

[0028] Specifically, a USB interface 15, an electronic speed controller socket 16, and an image transmission module socket 17 are spaced apart on the second mounting surface 1b. The power board 2 is circumferentially spaced with a first clearance slot 2a, a second clearance slot 2b, and a third clearance slot 2c. The USB interface 15 is located in the first clearance slot 2a, the electronic speed controller socket 16 is located in the second clearance slot 2b, and the image transmission module socket 17 is located in the third clearance slot 2c.

[0029] On the second mounting surface 1b of the control board 1, there are spaced USB interfaces 15, electronic speed controller sockets 16, and image transmission module sockets 17. Each component is fixed to its preset position by welding or bolting and is electrically connected to the main control chip 11 via onboard wiring. The spaced layout ensures sufficient heat dissipation space and signal isolation for each component. The USB interface 15 uses a standard Type-C or Micro-USB interface, providing data transmission and charging functions. It can be used for burning flight control programs, exporting flight logs, and providing temporary power to external devices. The electronic speed controller socket 16 connects to the electronic speed controller, which integrates a power transistor and control circuit. It receives signals from the main control chip 11, adjusts the speed of the drone's motors, and thus controls the drone's flight attitude and speed. It is a key component connecting the main control chip 11 and the motors. The image transmission module socket 17 connects to an external 2.4G or 5.8G image transmission module. The image transmission module has a communication chip or wireless transmission chip to transmit image signals captured by the drone's camera to the ground receiving equipment in real time, enabling real-time monitoring of the flight footage. The power board 2 has three circumferentially spaced clearance slots: a first clearance slot 2a, a second clearance slot 2b, and a third clearance slot 2c. These three clearance slots correspond one-to-one with the positions of the USB interface 15, the electronic speed controller socket 16, and the image transmission module socket 17, respectively. Their dimensions are adapted to the shape of each component, ensuring that each component can be completely accommodated in its corresponding clearance slot after installation without interfering with the power board 2. This adaptive design allows the control board 1 and the power board 2 to fit tightly together, further reducing the overall size. At the same time, each component obtains independent installation space through the clearance slots, reducing mechanical collisions and electromagnetic interference between them. The reasonable layout of the USB interface 15, the electronic speed controller socket 16, and the image transmission module socket 17 clearly defines the functional areas, facilitating later maintenance and debugging, and improving the practicality and maintainability of the flight controller 100.

[0030] For further details, please refer to... Figure 3 and Figure 4 The power board 2 also forms a fourth air-avoidance slot 2d. The flight controller 100 also includes a receiver 3, which includes an antenna mount 31, an antenna 32, and a communication chip 33. The antenna mount 31 and the communication chip 33 are installed at intervals on the first mounting surface 1a at positions corresponding to the fourth air-avoidance slot 2d. The antenna 32 is connected to the antenna mount 31.

[0031] The power board 2 also has a fourth clearance slot 2d, which has the same structure as the other clearance slots and is distributed along the circumferential edge of the power board 2. Its position corresponds to the reserved mounting position on the first mounting surface 1a of the control board 1. The flight controller 100 also includes a receiver 3, which is a wireless signal receiving module used to receive control commands sent by the ground remote controller. It includes an antenna mount 31, an antenna 32, and a communication chip 33. The antenna mount 31 is made of metal and is fixedly connected to the first mounting surface 1a of the control board 1 at the position corresponding to the fourth clearance slot 2d by threads or welding. The antenna mount 31 has a signal transmission line inside, which is electrically connected to the main control chip 11. The antenna 32 can be a flexible or rigid radio frequency antenna with an omnidirectional radiation design. It is connected to the top of the antenna mount 31 and can receive wireless signals 360 degrees. Its length is matched with the operating frequency to ensure signal reception sensitivity. In this embodiment, antenna 32 is a T-shaped antenna, and antenna mount 31 is an IPEX1 antenna mount. Antenna 32 includes a WiFi antenna and a 2.4G antenna. Communication chip 33 includes a wireless transceiver chip (wireless transceiver IC) and a Bluetooth chip (Bluetooth IC). In other embodiments, these can be selected according to actual needs. The fourth clearance slot 2d provides independent installation space for antenna mount 31, preventing the power components on power board 2 from blocking or interfering with the antenna signal. Antenna mount 31 is mounted on the first mounting surface 1a on control board 1, allowing antenna 32 to extend outside the flight controller 100, reducing the shielding of the board and other components on the signal, and improving signal reception distance and stability. After receiving instructions from the ground remote controller through antenna 32, receiver 3 converts them into electrical signals and transmits them to main control chip 11. Main control chip 11 adjusts the flight state according to the instructions to ensure that the UAV can respond accurately to control. This design improves the remote control distance and control accuracy of flight controller 100 and is suitable for long-distance flight missions.

[0032] In one embodiment, please refer to Figure 3 and Figure 4 The power board 2 is a rectangular plate, and the first clearance slot 2a, the second clearance slot 2b, the third clearance slot 2c and the fourth clearance slot 2d are respectively distributed on the four sides of the power board 2.

[0033] The power board 2 is a rectangular board. The rectangular structure facilitates compatibility with the control board 1 and the UAV mounting base. Its four corners are rounded to prevent sharp edges from scratching other components or cables. The first clearance slot 2a, the second clearance slot 2b, the third clearance slot 2c, and the fourth clearance slot 2d are distributed around the perimeter of the power board 2, with one clearance slot on each side, forming a symmetrical layout. This symmetrical layout of the rectangular power board 2 ensures that the clearance slots are positioned evenly, matching the distribution of the USB interface 15, electronic speed controller socket 16, image transmission module socket 17, and receiver 3 on the control board 1. This ensures even stress distribution and structural stability after the control board 1 and power board 2 are assembled. The four clearance slots distributed around the perimeter fully utilize the edge space of the power board 2, avoiding encroachment on the core area of ​​the power supply mounting surface and ensuring sufficient installation space for the power components. Simultaneously, the symmetrical design keeps the center of gravity of the flight controller 100 central, reducing attitude instability caused by center of gravity shift during UAV flight and improving the structural rationality and flight adaptability of the flight controller 100.

[0034] In one embodiment, please refer to Figure 1 and Figure 2 The flight controller 100 also includes a silicone shock absorber 4. A first mounting hole is formed on the control board 1, and a second mounting hole is formed on the power board 2. The first mounting hole and the second mounting hole are correspondingly set, and the silicone shock absorber 4 is inserted into the first mounting hole and the second mounting hole.

[0035] The flight controller 100 also includes silicone shock absorber pillars 4. These pillars are made of highly elastic silicone, providing excellent shock absorption and insulation. They are cylindrical with protruding positioning heads at both ends. Multiple first mounting holes are formed along the edge of the control board 1, and multiple second mounting holes are formed on the power board 2 corresponding to the first mounting holes. A positioning groove is formed in the inner wall of the silicone shock absorber pillar 4. The silicone shock absorber pillar 4 is inserted into the first mounting holes of the control board 1 and the second mounting holes of the power board 2, securing the boards at the first mounting holes on the control board 1 and the second mounting holes on the power board 2 within the positioning groove. This prevents the control board 1 and power board 2 from axially detaching from the silicone shock absorber pillar 4 after installation. The silicone structures on the upper and lower sides of the positioning groove provide support and protection for the control board 1 and power board 2. The silicone shock absorber pillar 4 absorbs vibration energy through its elastic deformation, reducing the impact of vibration on the electronic components on the control board 1 and power board 2, and preventing solder joint detachment, chip damage, or sensor data distortion caused by vibration. Furthermore, a through-hole is formed in the middle of the silicone damping column 4, allowing the silicone damping column 4 to be fitted onto the mounting column inside the UAV and fixed, thus elevating the flight controller 100 for installation. Since electronic components are mounted on opposite sides of the flight controller 100, this elevated installation method avoids interference between the electronic components on both sides of the flight controller 100 and the internal structure of the UAV. Simultaneously, the elevated installation method also facilitates heat dissipation for the electronic components on the flight controller 100. This vibration damping design improves the operational stability and service life of the flight controller 100 in complex vibration environments, ensuring reliable operation of the UAV under harsh flight conditions.

[0036] In one embodiment, please refer to Figure 3 and Figure 4 The flight controller 100 also includes a lighting assembly, which includes a light strip pad and a button 5. The light strip pad is connected to the power mounting surface, and the button 5 is connected to the power mounting surface and electrically connected to the light strip pad.

[0037] The flight controller 100 also includes a lighting assembly, which comprises a light strip pad and a button 5. The light strip pad is a copper foil pad on the PCB board, formed by etching, and connected to the power mounting surface of the power board 2. It is electrically connected to the power assembly via on-board wiring. LED beads can be soldered onto the light strip pad to form indicator lights. The button 5 is a tactile switch, connected to the power mounting surface of the power board 2 via surface mount technology, and electrically connected to the light strip pad via wiring. The trigger end of the button 5 is exposed on the edge of the power board 2 for easy user operation. The light strip pad is used for connecting external LED light strips. Users can set the color of the LED light strip according to their needs, changing the color once per button press, supporting a total of 7 color transitions. The button 5 controls the color change of the external LED light strip, allowing users to distinguish different aircraft by color. The button 5 can be used to switch lighting modes, turn the lights on or off, and can also serve as a function shortcut key for quick triggering of specific control commands. The lighting assembly provides the flight controller 100 with a status indication function, allowing users to quickly determine the equipment's operating status on the ground. The addition of button 5 improves ease of operation, especially in debugging or emergency situations, enabling a quick response, expanding the functionality and practicality of the flight controller 100, and enhancing the user experience.

[0038] This utility model also proposes a drone, which includes a flight controller 100. The specific structure of the flight controller 100 is as described in the above embodiments. Since this drone adopts all the technical solutions of all the above embodiments, it has at least all the beneficial effects brought about by the technical solutions of the above embodiments, which will not be described in detail here. The drone also includes components such as the fuselage, motors, propellers, batteries, and cameras. The flight controller 100 is fixedly installed at the center of the fuselage by bolts or shock-absorbing brackets and is electrically connected to the motors, batteries, cameras, and other components. As the core control unit of the drone, the flight controller 100 receives electrical energy provided by the battery and converts it into a stable voltage for the operation of each component through the power board 2. The main control chip 11 receives data from sensors such as the gyroscope 12 and the barometer chip, and combines it with the remote control commands received by the receiver 3 to output control signals to the electronic speed controller socket 16 to adjust the motor speed, thereby controlling the propeller thrust and realizing the drone's takeoff, landing, hovering, turning, and other flight attitude adjustments. At the same time, the flight controller 100 transmits the images captured by the camera to the ground terminal through the image transmission module socket 17 and realizes data interaction and program updates through the USB interface 15. The miniaturized design of the Flight Controller 100 is adapted to the compact layout of the UAV, the shock-absorbing structure improves the stability of the UAV in complex flight environments, and the rich interfaces and modules expand the functional adaptability of the UAV, enabling the UAV to meet the mission requirements of different scenarios, and significantly improving the flight performance, reliability and ease of operation of the UAV.

[0039] The above description is merely an exemplary embodiment of the present utility model and does not limit the patent scope of the present utility model. Any equivalent structural transformations made based on the technical concept of the present utility model and the contents of the present utility model specification and drawings, or direct / indirect applications in other related technical fields, are included within the patent protection scope of the present utility model.

Claims

1. A flight controller characterized by, The flight controller includes a control board and a power board. The control board includes a first mounting surface and a second mounting surface that are arranged opposite to each other. The first mounting surface is used to install the main control chip. The power board includes a power mounting surface and a connection surface that are arranged opposite to each other. The power mounting surface is used to install power components. The second mounting surface is welded and fixed to the connection surface. The control board is electrically connected to the power board.

2. The flight controller of claim 1, wherein, The first mounting surface is also provided with gyroscopes, storage chips, video character overlay chips and barometer chips at intervals.

3. The flight controller of claim 1, wherein, The power board has a circumferential clearance groove, and electronic components are installed on the second mounting surface of the control board at a position corresponding to the clearance groove.

4. The flight controller of claim 1, wherein, The second mounting surface is provided with a USB interface, an electronic speed controller socket, and an image transmission module socket at intervals. The power board is provided with a first clearance slot, a second clearance slot, and a third clearance slot at intervals in its circumference. The USB interface is located in the first clearance slot, the electronic speed controller socket is located in the second clearance slot, and the image transmission module socket is located in the third clearance slot.

5. The flight controller of claim 4, wherein, The power board also forms a fourth air-avoidance slot, and the flight controller also includes a receiver. The receiver includes an antenna mount, an antenna, and a communication chip. The antenna mount and the communication chip are installed at intervals on the first mounting surface corresponding to the fourth air-avoidance slot, and the antenna is connected to the antenna mount.

6. The flight controller of claim 5, wherein, The power board is a rectangular plate, and the first clearance slot, the second clearance slot, the third clearance slot and the fourth clearance slot are respectively distributed on the four sides of the power board.

7. The flight controller of any one of claims 1 to 6, wherein, The flight controller also includes silicone shock absorbers. A first mounting hole is formed on the control board, and a second mounting hole is formed on the power board. The first mounting hole and the second mounting hole are correspondingly arranged, and the silicone shock absorbers are inserted into the first mounting hole and the second mounting hole.

8. The flight controller of claim 7, wherein, The flight controller also includes a lighting assembly, which includes a light strip pad and a button. The light strip pad is connected to the power mounting surface, and the button is connected to the power mounting surface and electrically connected to the light strip pad.

9. A drone, characterized in that, Includes the flight controller as described in any one of claims 1 to 8.

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