Universal unmanned aerial vehicle for teaching

Abstract

The invention relates to the technical field of unmanned aerial vehicles, and particularly discloses a universal unmanned aerial vehicle for teaching, which comprises an undercarriage assembly, a foldable arm group, a rack main body, a positioning assembly and a rotor assembly, the rack main body is arranged on the undercarriage assembly, the foldable arm set comprises folding arms rotationally arranged on the peripheral side of the rack main body, the rotor wing assembly is arranged at the ends, away from the rack main body, of the folding arms, and a mounting platform used for mounting an external intelligent terminal is arranged at the bottom of the rack main body; the rack body comprises a carrier plate, a flight control unit arranged on the carrier plate and a power module electrically connected with the flight control unit, and the flight control unit comprises a circuit board, an SOC chip and an interface module, and the rotor assemblies and an external intelligent terminal mounted on the mounting platform are electrically connected with the flight control unit through an external line and an interface module so as to carry out power transmission and data interaction.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and in particular discloses a general-purpose UAV for teaching purposes. Background Technology

[0002] With the rapid development of drone technology and the expansion of its application areas, drones have shown great potential in agriculture, surveying, security, and aerial photography. However, while there are many types of drones on the market, most focus on a single function. For example, agricultural drones focus on plant spraying, aerial photography drones focus on image capture, and surveying drones focus on data collection. This single-function design leads users to purchase multiple drones for different purposes, increasing equipment costs and learning difficulty, especially for drone pilot training. Drone pilots need to systematically learn various skills such as drone assembly, debugging, aerial photography, and surveying, but currently there is a lack of a general-purpose, multi-functional drone to meet the comprehensive training needs. Summary of the Invention

[0003] In order to overcome the shortcomings and deficiencies of the existing technology, the purpose of this invention is to provide a general-purpose drone that can better help drone pilots to quickly learn and practice drone assembly, debugging, aerial photography and other functions in one go.

[0004] To achieve the above objectives, the present invention provides a general-purpose unmanned aerial vehicle (UAV) for teaching, comprising a landing gear assembly, a foldable arm assembly, a frame body, a positioning assembly, and a rotor assembly; the frame body is disposed on top of the landing gear assembly, the positioning assembly is mounted on the frame body, the foldable arm assembly includes a foldable arm rotatably disposed around the periphery of the frame body, the rotor assembly is disposed at the end of the foldable arm away from the frame body, and the bottom of the frame body is provided with a mounting platform for mounting an external smart terminal.

[0005] Furthermore, the main frame includes a carrier plate, a flight control unit mounted on the carrier plate, and a power module electrically connected to the flight control unit. The flight control unit includes a circuit board, a SOC chip mounted on the circuit board, and an interface module. The rotor assembly and the external intelligent terminal mounted on the mounting platform are electrically connected to the flight control unit via external lines and the interface module for power transmission and data interaction.

[0006] Furthermore, the circuit board is coated with a waterproof coating, which is formed by vapor deposition of a paraffin material, thereby improving the waterproof and corrosion-resistant properties of the flight control unit's circuit board and enabling it to maintain stable operation even in harsh environments.

[0007] Furthermore, the carrier plate is installed on top of the landing gear assembly, and the external intelligent terminal mounted on the mounting platform includes a camera, surveying equipment, or spraying device. The interface module includes a power supply interface, a data transmission interface, a video interface, a wireless communication interface, a control signal interface, and a storage interface for powering the external intelligent terminal and facilitating data interaction.

[0008] Furthermore, the carrier plate is composed of a first rectangular plate and a second rectangular plate connected by bolts, with an installation space between the first and second plates for mounting the power module. Both the first and second plates are made of carbon fiber, which aims to improve the structural strength and rigidity of the fuselage, effectively reduce the overall weight of the fuselage, and improve flight efficiency and endurance.

[0009] Furthermore, the flight control unit is mounted on the top of the second plate via a shock-absorbing assembly. The shock-absorbing assembly includes a shock-absorbing base plate detachably mounted on the top of the second plate, shock-absorbing pads located at the four corners of the base plate, and a shock-absorbing top plate mounted on the shock-absorbing pads. The shock-absorbing pads are integrally molded from silicone material. The shock-absorbing base plate and the shock-absorbing top plate are cut and molded from carbon fiber material.

[0010] Furthermore, the data transmission interface includes a USB interface, a UART interface, an I2C interface, an I2S interface, a TYPE-C interface, an SPI interface, and a CAN interface. This design enables the UAV of this invention to be compatible with multiple communication protocols, meeting the needs of high-speed data transmission, low-power communication, and multi-device interconnection, achieving flexible and scalable data interaction, and effectively improving the system's compatibility and applicability. It also allows UAV pilots to conduct multi-functional learning through the UAV.

[0011] Furthermore, the foldable arm assembly also includes a connector and an arm fastener. The arm fastener is rotatably connected to the connector via at least two pivots. The connector is mounted on a carrier plate of the main frame. The folding arm is located at the end of the arm fastener away from the connector. The connector is provided with an adjusting rod for adjusting the rotation angle of the arm fastener. Adjusting knobs are telescopically mounted at both ends of the adjusting rod. The two ends of the adjusting knobs that are close to each other are used to press the two ends of the arm fastener that are far apart from each other against both sides of the connector to adjust its rotation angle.

[0012] Furthermore, the positioning component includes a BeiDou receiver, an antenna module, and a data processing module connected in sequence. The BeiDou receiver is mounted on a carrier plate of the main frame and electrically connected to the flight control unit. The antenna module includes a mounting rod on the top of the carrier plate, a signal transmission cable inside the mounting rod, and an antenna body on the top of the mounting rod. The antenna body is connected to the BeiDou receiver via the signal transmission cable.

[0013] Furthermore, the arm fastener includes a first clamping plate and a second clamping plate for clamping and fixing the end of the folding arm away from the rotor assembly, and the first clamping plate and the second clamping plate are detachably connected.

[0014] Furthermore, the folding arm is cylindrical in shape, and both the first clamping plate and the second clamping plate have arc-shaped grooves for clamping the folding arm.

[0015] Furthermore, the number of foldable arm assemblies is 4, and the 4 foldable arm assemblies are symmetrically arranged around the central axis of the frame body, that is, respectively set at the four corners of the rectangular carrier plate; correspondingly, the rotor assembly is provided in 4 sets, and the 4 rotor assemblies are respectively installed at the end of the folding arm away from the frame body.

[0016] Furthermore, the rotor assembly includes a brushless motor disposed at one end of the folding arm away from the main frame and electrically connected to the flight control unit. The brushless motor includes a housing, a stator disposed within the housing, and a rotor rotatably engaged with the stator. The rotor is disposed between the stator and the housing. One end of the rotor is provided with a heat dissipation bracket. The heat dissipation bracket has heat dissipation holes that communicate with the inner cavity of the housing. A propeller is disposed on the heat dissipation bracket.

[0017] Furthermore, the rotor assembly also includes a quick-release buckle and a motor mounting bracket. The quick-release buckle includes a clamp connected to the motor mounting bracket and a fastening buckle rotatably mounted on the clamp. The brushless motor is mounted on the motor mounting bracket, and the motor mounting bracket is detachably connected to the folding wall via the clamp and the fastening buckle. One end of the fastening buckle is provided with an elastic arm, and the inner end face of the elastic arm is provided with a plurality of inclined ratchet bars. One end of the clamp is provided with a receiving groove for accommodating the elastic arm. The bottom of the receiving groove is recessed from its bottom wall with a plurality of inclined blind grooves for accommodating the ratchet bars. The end of the clamp near the inclined blind groove is recessed with a quick-release groove communicating with the receiving groove.

[0018] Furthermore, the outer casing includes a bottom shell bolted to the top of the motor mounting bracket and a cylindrical protective shell surrounding the bottom shell. The cylindrical protective shell and the bottom shell together form an inner cavity for accommodating the stator and rotor components. The stator component includes a stator core mounted on the bottom shell and coils wound on the stator core, with the stator core being hollow inside. The rotor component includes a magnet bracket rotatably mounted inside the protective shell and located outside the stator component, and multiple magnetic tiles mounted on the magnet bracket. The heat dissipation bracket is connected to the top of the magnet bracket, and has multiple heat dissipation holes arranged around the central axis of the heat dissipation bracket. A column is detachably connected to the middle of the heat dissipation bracket, and this column is located inside the hollow part of the stator core.

[0019] The heat dissipation bracket is connected to the top of the magnet bracket and then to the hollow part inside the stator core via a column, forming a through-type fixing point. This design enhances the overall integrity and resistance to deformation, keeping the motor stable during high-speed operation and reducing vibration deviations. The hollow structure of the stator core not only provides installation space for the heat dissipation column but also optimizes the motor's magnetic circuit design. The hollow core reduces the material resistance inside the core, minimizing eddy current losses and thus improving the motor's efficiency and output performance.

[0020] Furthermore, the rotor assembly also includes an electronic speed controller connected between the flight control unit and the brushless motor. The electronic speed controller is used to control the speed of the brushless motor according to the flight control commands from the flight control unit, thereby achieving attitude and altitude control.

[0021] Furthermore, the landing gear assembly, carrier plate, mounting platform, and folding arm are all manufactured using carbon fiber through a cutting process. Manufacturing the landing gear assembly, carrier plate, mounting platform, and folding arm using carbon fiber through a cutting process offers advantages such as light weight, high strength, and corrosion resistance. This significantly reduces the overall weight of the equipment, improves structural strength and impact resistance, and enhances the UAV's endurance and durability, enabling it to adapt to complex environments and high-intensity mission requirements.

[0022] Furthermore, the landing gear assembly includes two first support rods connected to the bottom of the carrier plate. The two first support rods extend outward from the bottom of the carrier plate at an angle. The bottom of each of the two first support rods is connected to a second support rod, and the second support rod is fitted with a sponge sleeve for shock absorption.

[0023] Furthermore, the first support rod is telescopically connected to the bottom of the carrier plate via a telescopic structure, and the second support rod is detachably connected to the bottom of the first support rod.

[0024] Furthermore, the mounting platform includes four positioning columns connected to the bottom of the carrier plate and a bearing plate set on the positioning columns, the bearing plate having multiple slots for mounting bolts.

[0025] Furthermore, the general-purpose drone used for teaching also includes a rain cover mounted on the carrier plate of the main frame. The rain cover includes a bottom shell mounted on the flight control unit, the bottom shell having a cavity for accommodating the flight control unit, and a rain shield rotatably mounted on the bottom shell. The rain shield has an arc-shaped convex surface for guiding external rainwater to the outside of the flight control unit.

[0026] This invention achieves multifunctionality and versatility for drones through a foldable arm design, a modular frame body, and highly compatible mounting interfaces. The frame body integrates a flight control unit, SOC chip, and interface modules, enabling power supply and data exchange with various external intelligent terminals (such as cameras, surveying equipment, and spraying devices). Simultaneously, the arm and rotor assemblies feature a detachable and quick-release design, combined with a unibody structure made of carbon fiber, giving the drone excellent characteristics of easy folding, assembly, and disassembly, and enhancing the equipment's portability and reliability.

[0027] The beneficial effects of this invention are as follows: The general-purpose drone for teaching, through the aforementioned structural improvements, meets the needs of multi-functional comprehensive training. Its modular structure and highly compatible interfaces lower the learning threshold, facilitating the learning of drone pilots' skills in assembly, debugging, aerial photography, and surveying. Compared to traditional single-purpose drones, this invention is compact, easy to operate, and supports flexible configuration of sensors and mounted equipment, greatly improving training efficiency. It is suitable for systematic skills training of drone pilots and simulation exercises for multi-scenario tasks. Attached Figure Description

[0028] Figure 1 This is a schematic diagram of the overall structure of the general-purpose unmanned aerial vehicle (UAV) for teaching purposes according to the present invention; Figure 2 for Figure 1 A magnified structural diagram of part A in the middle; Figure 3 This is a schematic diagram of the foldable arm assembly of the present invention; Figure 4 This is a schematic diagram of the rotor assembly of the present invention in an explosion state; Figure 5 This is a three-dimensional structural diagram of the quick-release buckle of the present invention after partial cross-section; Figure 6 This is a schematic diagram of the internal structure of the flight control unit of the present invention; Figure 7 This is a schematic diagram of the structure of the shock absorption component of the present invention; Figure 8 This is a structural schematic diagram of the landing gear assembly, carrier plate, and mounting platform of the present invention. Figure 9 This is a schematic diagram of the power module of the main frame of the present invention; Figure 10 This is a schematic diagram of the structure of the rain cover of the present invention.

[0029] The reference numerals in the figures include: 1. Landing gear assembly; 11. First support rod; 12. Second support rod; 13. Foam sleeve; 2. Foldable arm assembly; 21. Folding arm; 22. Connector; 23. Arm fastener; 231. First clamping plate; 232. Second clamping plate; 24. Rotary shaft; 25. Adjusting rod; 26. Adjusting knob; 3. Frame body; 31. Carrier plate; 311. First plate; 312. Second plate; 32. Flight control unit; 321. Circuit board; 322. SOC chip; 323. Interface module; 3231. Power supply interface; 3232. Data transmission interface; 3233. Video interface; 3234. Wireless communication interface; 3235. Control signal interface; 3236. Storage interface; 33. Power module; 4. Positioning assembly; 41. North 42. Receiver; 421. Antenna module; 422. Mounting rod; 422. Antenna body; 5. Rotor assembly; 51. Quick-release buckle; 511. Clamp; 512. Fastening buckle; 513. Flexible arm; 514. Inclined ratchet; 515. Receiving slot; 516. Inclined blind slot; 517. Easy-release slot; 52. Motor mounting bracket; 53. Brushless motor; 531. Housing; 532. Rotor component; 533. Stator component; 534. Heat dissipation bracket; 535. Heat dissipation hole; 536. Propeller; 6. Mounting platform; 61. Positioning post; 62. Bearing plate; 63. Slot hole; 7. Vibration damping assembly; 71. Vibration damping base plate; 72. Vibration damping pad; 73. Vibration damping top plate; 8. Rain cover; 81. Bottom shell; 82. Rain shield; 83. Arc-shaped convex surface. Detailed Implementation

[0030] To facilitate understanding by those skilled in the art, the present invention will be further described below with reference to embodiments and accompanying drawings. The content mentioned in the embodiments is not intended to limit the present invention.

[0031] Please see Figures 1 to 10As shown, this invention discloses a general-purpose unmanned aerial vehicle (UAV) for teaching, comprising a landing gear assembly 1, foldable arm assemblies 2, a frame body 3, a positioning assembly 4, and a rotor assembly 5. The frame body 3 is fixedly mounted on top of the landing gear assembly 1, and uses a carbon fiber carrier plate 31 as the basic structure of the frame body 3 to improve fuselage strength and reduce overall weight. A flight control unit 32 and a power module 33 are mounted on the frame body 3. The flight control unit 32 consists of a circuit board 321, which integrates a SOC chip 322 and a multi-functional interface module 323 (including a power supply interface 3231, a data transmission interface 3232, and a control signal interface 3235) for power transmission and data interaction using various communication protocols. The foldable arm assemblies 2 are connected to the frame body 3 via pivots 24 and fastening devices. Each foldable arm 21 has a rotor assembly 5 at its end, including a brushless motor 53 and a propeller 536. The brushless motor 53 is connected to the flight control unit 32 via an electronic speed controller (ESC) to control its rotation speed in response to flight control commands. The mounting platform 6 at the bottom of the main frame 3 mounts a smart terminal (such as a camera, surveying instrument, or spraying equipment) via positioning posts 61 and a support plate 6231. The smart terminal is connected to the interface module 323 for data acquisition, processing, and task execution. The antenna of the positioning component 4 is mounted on the top of the support plate 31, and the receiver is connected to the flight control unit 32 via a signal line to achieve high-precision real-time positioning and navigation.

[0032] This solution enhances the versatility and ease of learning of drones through modular design. It features multi-functional expandability, easy maintenance, and high-precision flight control capabilities, making it suitable for various scenarios such as photography, surveying, and agricultural spraying. It meets the needs of complex tasks and can better help drone pilots quickly learn the practical skills of drone assembly, debugging, and aerial photography in one go.

[0033] Specifically, the carrier plate 31 is fixed to the top of the landing gear assembly 1 with screws, providing a stable mounting base for the frame body 3. The mounting platform 6 is used to mount various external intelligent terminals, such as cameras for aerial photography, monitoring, or environmental monitoring; surveying equipment for terrain surveying, precise positioning, or 3D modeling; and spraying devices for pesticide spraying or vegetation maintenance in agricultural scenarios. This satisfies the multi-functional learning needs of drone pilots. The mounting platform 6 is detachably mounted on the bottom of the carrier plate 31 with screws, and the power supply and data communication of the intelligent terminals are realized through the flight control unit 32 and the interface module 323.

[0034] Specifically, the interface module 323 is designed as a multi-functional expansion interface, including the following specific functional interfaces: a power supply interface 3231 provides a stable power supply for the intelligent terminal; a data transmission interface 3232 supports high-speed data interaction between external devices and the flight control unit 32; a video interface 3233 is used for real-time transmission of images captured by cameras or other imaging devices; a wireless communication interface 3234 supports wireless communication between the UAV and ground stations or other control terminals, enabling remote control and mission command transmission; a control signal interface 3235 receives and sends operation commands from external intelligent terminals; and a storage interface 3236 supports connection to external storage devices for local storage or backup of mission data. These interfaces are uniformly managed by the SOC chip 322 on the circuit board 321, ensuring the collaborative operation of the flight control unit 32 and the intelligent terminal.

[0035] Specifically, the carrier plate 31, a key component of this general-purpose UAV used for teaching, is composed of a first plate 311 and a second plate 312 with rectangular structures, connected by bolts. A specially designed installation space between these two plates is used to accommodate the power module 33, ensuring a stable and reliable power system. The first plate 311 and the second plate 312, made of carbon fiber, not only significantly improve the structural strength and rigidity of the fuselage but also effectively reduce the overall weight, which is crucial for improving flight efficiency and extending endurance. The choice of carbon fiber not only gives the UAV higher flight stability and maneuverability during missions but also significantly reduces energy consumption, enabling it to perform missions efficiently under various environmental conditions.

[0036] Specifically, the flight control unit 32 is mounted on top of the second plate 312 via a shock-absorbing assembly 7. The shock-absorbing assembly 7 includes a removable shock-absorbing base plate 71, which is secured to the top of the second plate 312, and silicone shock-absorbing pads 72 at its four corners, as well as shock-absorbing top plates 73 mounted on the shock-absorbing pads 72. These shock-absorbing pads 72, through their one-piece molding of silicone material, effectively reduce interference from vibrations and impacts during flight on the flight control unit 32, ensuring stable operation and accurate data acquisition of the flight control unit 32.

[0037] Specifically, the data transmission interface 3232 includes interfaces such as USB, UART, I2C, I2S, TYPE-C, SPI, and CAN. This design allows the drone to be compatible with multiple communication protocols, meeting the needs of high-speed data transmission, low-power communication, and multi-device interconnection. For example, the USB interface is used for high-speed data transmission, the UART and I2C interfaces are suitable for low-power communication, the SPI interface is suitable for peripheral connections, and the CAN interface is used for multi-node communication. This multi-interface design enhances the system's flexibility and scalability, enabling the drone to efficiently interconnect with various external devices and systems.

[0038] Specifically, the foldable arm assembly 2 includes a connector 22 and an arm fastener 23. The arm fastener 23 is connected to the connector 22 via two pivots 24, and the connector 22 is mounted on the carrier plate 31 of the frame body 3. One end of the arm fastener 23 is connected to the folding arm 21, which is positioned away from the connector 22. An adjusting rod 25 is provided on the connector 22, with telescopic adjusting knobs 26 at both ends for adjusting the position of the arm fastener 23 and limiting its rotation angle by tightening it. This design allows for the folding and unfolding of the arm, facilitating the transport and storage of the UAV while ensuring the stability and safety of the arm during flight. This arm design greatly enhances the portability and operational flexibility of the UAV, allowing users to quickly fold or unfold the arm to adapt to different mission requirements and space constraints, while ensuring structural stability and safety during flight.

[0039] Specifically, the positioning component 4 includes a BeiDou receiver 41, an antenna module 42, and a data processing module. The BeiDou receiver 41 is mounted on the carrier plate 31 of the main frame 3 and is electrically connected to the flight control unit 32. The antenna module 42 consists of a mounting rod 421, a signal transmission cable, and an antenna body 422. The mounting rod 421 is located on the top of the carrier plate 31, and the signal transmission cable is internally connected to the antenna body 422 and externally connected to the BeiDou receiver 41. This design ensures that the UAV can accurately obtain positioning and navigation information provided by the BeiDou satellite system, supporting the flight control system to adjust the flight path and attitude in real time.

[0040] Specifically, the arm fastener 23 is designed with a first clamping plate 231 and a second clamping plate 232 for securing the folding arm 21 away from the rotor assembly 5. The first clamping plate 231 and the second clamping plate 232 can be detached for easy maintenance and adjustment of the arm's installation position. The folding arm 21 has a cylindrical design, while the first clamping plate 231 and the second clamping plate 232 have special arc-shaped grooves for firmly clamping the folding arm 21, ensuring its structural stability and safety during flight. This arm fastener 23 design simplifies the installation and disassembly process of the arm while improving the overall structural strength and stability of the fuselage, adapting to diverse flight mission requirements. By optimizing the fixing method of the folding arm 21, vibration and deformation during flight are further reduced, improving the operational reliability and flight performance of the UAV.

[0041] Specifically, there are four sets of foldable arm assemblies 2 and four sets of rotor assemblies 5. These arm assemblies and rotor assemblies 5 are symmetrically arranged about the central axis of the frame body 3 and are respectively installed at the four corners of the rectangular carrier plate 31. Each foldable arm assembly 2 consists of a folding arm 21 and a corresponding arm fastener 23. The folding arm 21 is set on the carrier plate 31 of the frame body 3, and the arm fastener 23 is fixed by an adjusting rod 25 and an adjusting knob 26 to ensure the stability and reliability of the arm. The four sets of rotor assemblies 5 are installed at the far end of each folding arm 21, so that the UAV can fly in a quadcopter configuration after unfolding. By symmetrically arranging the arms and rotor assemblies 5, the balance and flight control efficiency during flight are improved, and the arms can be quickly folded when needed for storage and transportation.

[0042] Specifically, the rotor assembly 5 is designed to include a brushless motor 53 mounted on the end of the folding arm 21 away from the frame body 3. Each brushless motor 53 includes a housing 531, a stator 533, and a rotor 532. The stator 533 is mounted inside the housing 531, while the rotor 532 rotates between the stator 533 and the housing 531. One end of the rotor 532 is provided with a heat dissipation bracket 534, which has a heat dissipation structure with through-holes 535 for effective heat dissipation. A propeller 536 is also mounted on the heat dissipation bracket 534 as a thrust generator, connected to the motor to generate lift.

[0043] Specifically, in addition to the brushless motor 53, the rotor assembly 5 also includes a quick-release buckle 51 and a motor mounting bracket 52. The quick-release buckle 51 consists of a clamp 511 and a fastening buckle 512, with the fastening buckle 512 rotatably mounted on the clamp 511 and connected to the motor mounting bracket 52. The brushless motor 53 is mounted on the motor mounting bracket 52 and detachably connected to the folding arm 21 via the clamp 511 and the fastening buckle 512. One end of the fastening buckle 512 has an elastic arm 513, and its inner end face has multiple inclined ratchet bars 514. One end of the clamp 511 has a receiving groove 515, and the inclined blind groove 516 at the bottom of the receiving groove 515 matches the inclined ratchet bars 514. The fastening buckle 512 and the clamp 511, through the engaging engagement of the inclined ratchet bars 514 and the inclined blind groove 516, form a closed annular structure that secures the motor mounting bracket 52 to the end of the folding arm 21. In addition, the end of the clamp 511 near the inclined blind slot 516 is recessed with a disassembly groove 517 to facilitate the placement of the driver's fingers or external disassembly tools. This design simplifies the installation and disassembly process of the motor and rotor assembly 5, improving maintenance efficiency and ease of operation.

[0044] Specifically, the outer casing 531 of the rotor assembly 5 includes a bottom shell 81 and a cylindrical protective shell surrounding the bottom shell 81, which is bolted to the top of the motor mounting bracket 52. The bottom shell 81 and the cylindrical protective shell together form an inner cavity for accommodating the stator component 533 and the rotor component 532. The stator component 533 includes a stator core mounted on the bottom shell 81, which is hollow inside and has coils wound on the outside. The rotor component 532 consists of a magnet bracket and multiple magnet tiles on the magnet bracket, which are rotatably mounted inside the protective shell and located outside the stator component 533.

[0045] A heat dissipation bracket 534 is connected to the top of the magnet bracket. The heat dissipation bracket 534 has multiple heat dissipation holes 535 arranged around the central axis of the heat dissipation bracket 534 for effective heat dissipation. A column is detachably connected to the middle of the heat dissipation bracket 534. The column is located in the hollow part of the stator core, which further supports the stability of the structure and thermal management.

[0046] Specifically, in addition to the brushless motor 53 and the outer casing 531, the rotor assembly 5 also integrates an electronic speed controller (ESC) connected between the flight control unit 32 and the brushless motor 53. The main function of the ESC is to precisely control the speed of the brushless motor 53 according to flight control commands sent by the flight control unit 32, thereby achieving precise control of flight attitude and altitude. The ESC adjusts the motor speed by receiving PWM signals or other speed control commands from the flight control unit 32 to ensure stable flight, precise hovering, and the execution of various flight missions for the UAV.

[0047] Specifically, the landing gear assembly 1, carrier plate 31, mounting platform 6, and folding arm 21 are all made of carbon fiber and precisely manufactured through a cutting process. Carbon fiber, with its lightweight, high strength, and corrosion resistance, significantly reduces the overall weight of the equipment while enhancing structural strength and impact resistance. This material selection and manufacturing process not only improves the UAV's flight performance and operational safety but also effectively extends its endurance and durability, enabling it to perform exceptionally well in complex environments and high-intensity missions.

[0048] Specifically, the landing gear assembly 1 includes two first support rods 11 connected to the bottom of the carrier plate 31, which extend outward from the bottom of the carrier plate 31. Each first support rod 11 is connected to a second support rod 12 at its bottom, and the second support rod 12 is fitted with a foam sleeve 13 to provide shock absorption.

[0049] Each first support rod 11 is telescopically connected to the bottom of the carrier plate 31 via a telescopic structure, allowing adjustment of the landing gear height and position as needed. A second support rod 12 is detachably connected to the bottom of the first support rod 11 for easy maintenance and replacement. This design not only provides excellent structural support and shock absorption but also enhances the stability and safety of the UAV during ground and air operations.

[0050] Specifically, the mounting platform 6 includes four positioning posts 61 connected to the bottom of the carrier plate 31 and a carrier plate 6231 mounted on the positioning posts 61 for supporting external smart terminals. These positioning posts 61 ensure the stable installation and precise positioning of the carrier plate 6231, enabling it to reliably support and secure the external smart terminals. The carrier plate 6231 has multiple slots 63 for installing and adjusting bolt positions to accommodate smart terminal devices of different types and sizes.

[0051] Specifically, the rain cover 8 is designed to protect the flight control unit 32, mounted on the carrier plate 31 of the frame body 3, from environmental influences. The rain cover 8 includes a base shell 81 with a cavity for housing and protecting the flight control unit 32. A rotatable rain shield 82 is mounted on the base shell 81. The rain shield 82 has an external arc-shaped convex surface 83, designed to effectively guide and block rainwater to protect the flight control unit 32 from rain damage. The rotatable design of the rain shield 82 facilitates the pilot's maintenance and monitoring of the operational status of the flight control unit 32.

[0052] This general-purpose teaching drone achieves flight control and payload operation through an integrated frame body 3, folding arm assembly, and rotor assembly 5. The frame body 3 houses the flight control unit 32 and power module 33, connecting to external smart terminals via various interfaces, enhancing the drone's versatility and reducing the learning, control, assembly, and testing costs for drone pilots. The fuselage is made of carbon fiber, combined with optimized landing gear and mounting platforms 6, improving flight efficiency and system durability. The rotor assembly 5 includes a heat dissipation bracket 534 for optimized heat dissipation and an electronic speed controller for precise flight control. A rain cover 8 further protects critical electronic equipment from environmental impacts, enabling it to adapt to various complex missions and harsh environmental conditions.

[0053] The above description is only a preferred embodiment of the present invention. For those skilled in the art, there will be changes in the specific implementation and application scope based on the ideas of the present invention. The content of this specification should not be construed as a limitation of the present invention.

Claims

1. A general-purpose UAV for teaching, characterized by: The invention comprises a landing gear assembly (1), a foldable arm assembly (2), a frame body (3), a positioning assembly (4) and a rotor assembly (5); the landing gear assembly (1) is arranged on the lower end of the frame body (3), the positioning assembly (4) is mounted on the frame body (3), the foldable arm assembly (2) comprises a folding arm (21) rotatably arranged on the peripheral side of the frame body (3), the rotor assembly (5) is arranged at one end of the folding arm (21) away from the frame body (3), and a mounting platform (6) for mounting an external intelligent terminal is provided at the bottom of the frame body (3).

2. The general-purpose UAV for teaching according to claim 1, characterized in that: The frame body (3) comprises a carrier board (31), a flight control unit (32) arranged on the carrier board (31), and a power module (33) electrically connected to the flight control unit (32); the flight control unit (32) comprises a circuit board (321), a SOC chip (322) arranged on the circuit board (321), and an interface module (323); the rotor assembly (5) and an external intelligent terminal mounted on the mounting platform (6) are electrically connected to the flight control unit (32) via an external line and the interface module (323) to perform power transmission and data interaction.

3. The general-purpose UAV for teaching according to claim 2, characterized in that: The carrier plate (31) is mounted on the top of the landing gear assembly (1); the external intelligent terminal mounted on the mounting platform (6) comprises one or more combinations of a camera, a surveying and mapping device, and a spraying device; the interface module (323) comprises a power supply interface (3231) for supplying power to the external intelligent terminal and interacting with data, a data transmission interface (3232), a video interface (3233), a wireless communication interface (3234), a control signal interface (3235), and a storage interface (3236).

4. The general-purpose UAV for teaching according to claim 1, characterized in that: The foldable arm assembly (2) further comprises a connecting member (22) and an arm fastener (23); the connecting member (22) is arranged on a carrier plate (31) of the frame body (3); the arm fastener (23) is rotatably connected to the connecting member (22) via at least two rotating shafts (24); the foldable arm (21) is arranged at an end of the arm fastener (23) away from the connecting member (22); an adjusting rod (25) for adjusting the rotation angle of the arm fastener (23) is arranged on the connecting member (22); adjusting knobs (26) are telescopically arranged at both ends of the adjusting rod (25); the two ends of the adjusting knob (26) close to each other are used to press the two ends of the arm fastener (23) away from each other against two sides of the connecting member (22) to adjust the rotation angle thereof.

5. The general-purpose UAV for teaching according to claim 1, characterized in that: The positioning assembly (4) comprises a Beidou receiver (41), an antenna module (42) and a data processing module which are connected in sequence; the Beidou receiver (41) is mounted on a carrier board (31) of a frame body (3) and is electrically connected to a flight control unit (32); the antenna module (42) comprises a mounting rod (421) arranged on the top of the carrier board (31), a signal transmission cable arranged inside the mounting rod (421), and an antenna body (422) arranged on the top of the mounting rod (421); the antenna body (422) is connected to the Beidou receiver (41) via the signal transmission cable.

6. The general-purpose UAV for teaching according to claim 1, characterized in that: The number of the foldable arm groups (2) is a plurality, and the plurality of foldable arm groups (2) are evenly spaced around the central axis of the frame body (3); the number of the rotor assemblies (5) is a plurality, and the rotor assemblies (5) and the foldable arm groups (2) are arranged in a one-to-one correspondence, and the number of the rotor assemblies (5) is consistent with the number of the foldable arm groups (2).

7. The general-purpose UAV for teaching according to claim 1, characterized in that: The rotor assembly (5) comprises a brushless motor (53) arranged at one end of the folding arm (21) away from the frame body (3) and electrically connected to the flight control unit (32); the brushless motor (53) comprises an outer shell (531), a stator component (533) arranged in the outer shell (531), and a rotor component (532) rotatably matched with the stator component (533); the rotor component (532) is arranged between the stator component (533) and the outer shell (531); a heat dissipation bracket (534) is provided at one end of the rotor component (532); a heat dissipation hole (535) communicating with the inner cavity of the outer shell (531) is provided through the heat dissipation bracket (534); and a propeller (536) is provided on the top of the heat dissipation bracket (534).

8. The general-purpose UAV for teaching according to claim 7, characterized in that: The rotor assembly (5) further comprises a quick-release buckle (51) and a motor mounting bracket (52); the quick-release buckle (51) comprises a clamp (511) connected to the motor mounting bracket (52) and a fastening buckle (512) rotatably disposed on the clamp (511); an outer housing (531) of the brushless motor (53) is disposed on the motor mounting bracket (52); the motor mounting bracket (52) is detachably connected to the folding arm (21) via the clamp (511) and the fastening buckle (512); the fastening buckle (511) is disposed on the outer housing (531) of the brushless motor (53) and is disposed on the motor mounting bracket (52); 12) is provided with an elastic arm (513) at one end, and a plurality of inclined ratchet strips (514) are convexly provided on the inner end surface of the elastic arm (513); a receiving groove (515) for accommodating the elastic arm (513) is provided at one end of the clamp (511); a plurality of inclined blind grooves (516) for accommodating the inclined ratchet strips (514) are concavely provided at the bottom of the receiving groove (515) from the bottom wall thereof; and a convenient disassembly groove (517) communicating with the receiving groove (515) is concavely provided at one end of the clamp (511) close to the inclined blind groove (516).

9. The general-purpose UAV for teaching according to claim 1, characterized in that: The landing gear assembly (1), the carrier plate (31), the mounting platform (6) and the folding arm (21) are all made of carbon fiber material.

10. The general-purpose UAV for teaching according to claim 1, characterized in that: The general-purpose unmanned aerial vehicle for teaching further comprises a rain cover (8) arranged above the carrier plate (31) of the frame body (3), the rain cover (8) comprising a bottom shell (81) arranged on the flight control unit (32), a rain shield (82) being rotatably arranged on the bottom shell (81), the rain shield (82) having an arc-shaped outer convex surface (83) for guiding external rainwater to the outside of the flight control unit (32).

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