Four-axis unmanned aerial vehicle

Abstract

The utility model discloses a four-axis unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicle flight, the four-axis unmanned aerial vehicle comprises a fuselage, four flight assemblies are installed on the fuselage, and a battery used for providing electric energy for the flight assemblies is installed at the bottom of the fuselage; the flying assembly comprises a flying motor mounted on the fuselage, a rotating seat is fixedly mounted on an output shaft of the flying motor, and two flying blades which are arranged in a central symmetry manner are distributed at the two ends of the rotating seat; wherein the aircraft body is further provided with an adjusting assembly matched with the flight assembly, the adjusting assembly comprises two adjusting seats, the two adjusting seats are rotationally connected to the two ends of the rotating seat, and the flight blades are installed on the adjusting seats in a one-to-one fastening mode. The four-axis unmanned aerial vehicle solves the technical problem that the attack angles of the flight blades of the four-axis unmanned aerial vehicle in the prior art are difficult to adjust.

Description

Technical Field

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

[0002] A drone is an aircraft controlled by radio remote control or its own programs, capable of autonomous or semi-autonomous flight missions without a pilot. With continuous advancements in flight control systems, sensor technology, battery technology, and communication technology, drones have been widely applied in various fields, including but not limited to aerial photography, agricultural plant protection, power line inspection, traffic monitoring, emergency rescue, environmental monitoring, logistics transportation, and military reconnaissance. In particular, quadcopter drones (quadrotor drones), due to their simple structure, high maneuverability, and outstanding vertical takeoff and landing capabilities, have become the mainstream form of drones in both consumer and industrial applications.

[0003] In existing technologies, quadcopter drones use motors to drive propellers to rotate, thus enabling flight. However, due to the structural limitations of quadcopter drones, the mounting method of their propellers is mostly fixed, making it difficult to adjust the angle of attack of the propellers and consequently, difficult to adjust the drone's flight attitude.

[0004] It is evident that existing quadcopter drones suffer from the technical problem of difficulty in adjusting the angle of attack of their flight blades. Utility Model Content

[0005] The purpose of this invention is to provide a quadcopter drone that solves the technical problem of difficulty in adjusting the angle of attack of the flight blades in existing quadcopter drones.

[0006] To achieve this objective, the present invention adopts the following technical solution:

[0007] A quadcopter drone includes a fuselage with four flight components mounted on it. A battery for providing power to the flight components is installed at the bottom of the fuselage. Each flight component includes a flight motor mounted on the fuselage. A rotating base is fixedly mounted on the output shaft of the flight motor, and two flight blades are centrally symmetrically arranged at both ends of the rotating base.

[0008] The fuselage is also equipped with an adjustment assembly adapted to the flight component. The adjustment assembly includes two adjustment seats, which are rotatably connected to the two ends of the rotating seat. The flight blades are fastened to the adjustment seats one by one.

[0009] Optionally, the adjustment assembly further includes a drive unit and a lifting seat sleeved on the output shaft of the flight motor. Both adjustment seats are hinged to the lifting seat via hinged seats. The drive unit is used to drive the lifting seat to move up and down in a first direction.

[0010] Optionally, the driving component includes a lifting rod sleeved with the lifting seat, a servo motor is mounted on the fuselage, the lifting rod and the servo motor are connected through a transmission component, and the servo motor is used to provide driving power for the movement of the lifting rod according to the flight attitude of the UAV.

[0011] Optionally, the transmission component includes a swing frame rotatably connected to the fuselage, one end of the lifting rod away from the lifting seat is connected to the swing frame, a swing rod is also connected to the swing frame, and a swing seat connected to the swing rod is mounted on the output shaft of the servo motor.

[0012] Optionally, the thickness of each of the flight blades decreases in the width direction.

[0013] Optionally, the machine body is also equipped with a spraying assembly for spraying liquids.

[0014] Optionally, the spraying assembly includes a liquid storage tank, a solenoid valve, and a nozzle connected by interconnected pipelines. The liquid storage tank is fixedly installed in the middle of the machine body, and the solenoid valve is fixedly installed in the machine body and used to control the liquid spraying volume of the nozzle.

[0015] Optionally, the number of the solenoid valve and the nozzle is set to four, and the solenoid valve, the nozzle and the flight component correspond one-to-one.

[0016] Compared with the prior art, the present invention has the following beneficial effects:

[0017] This invention provides a quadcopter drone that, through the setting of two adjustment seats, allows the flight blades to flexibly adjust their angle of attack as needed, thereby enabling more precise control of the drone's flight attitude and improving flight stability and maneuverability. The introduction of the adjustment components not only allows the angle of attack of the flight blades to be adjusted according to changes in flight attitude, but also optimizes the aerodynamic characteristics of the flight blades during flight, thus improving the drone's flight stability in complex environments. Especially in flight missions with strong winds or complex conditions, adjusting the blade angle of attack can effectively cope with external disturbances and improve flight control precision. Due to the adjustable angle of attack, the quadcopter drone of this invention has stronger adaptability in various complex environments. Whether for agricultural plant protection, power line inspection, emergency rescue, or environmental monitoring, the angle of attack of the flight blades can be adjusted in real time according to different flight requirements to ensure efficient mission completion. Therefore, this invention solves the technical problem of difficulty in adjusting the angle of attack of flight blades in existing quadcopter drones. Attached Figure Description

[0018] 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 these drawings without creative effort.

[0019] The structures, proportions, sizes, etc., shown in the accompanying drawings of this specification are only for the purpose of assisting those skilled in the art in understanding and reading the content disclosed in the specification, and are not intended to limit the implementation conditions of this utility model. Therefore, they have no substantial technical significance. Any modifications to the structure, changes in the proportions, or adjustments to the size, without affecting the effects and purposes that this utility model can produce, should still fall within the scope of the technical content disclosed in this utility model.

[0020] Figure 1 One of the three-dimensional structural schematic diagrams of a quadcopter drone provided for an embodiment of this utility model;

[0021] Figure 2 A second three-dimensional structural schematic diagram of a quadcopter drone provided for an embodiment of this utility model;

[0022] Figure 3 A schematic diagram of the connection structure between the flight component and the adjustment component in a quadcopter drone provided in this embodiment of the present invention;

[0023] Figure 4 An exploded structural diagram of the flight component and adjustment component in a quadcopter drone provided for an embodiment of this utility model;

[0024] Figure 5 This is a three-dimensional structural diagram of a spraying component in a quadcopter drone, provided as an embodiment of the present invention.

[0025] Illustration:

[0026] 10. Fuselage;

[0027] 20. Flight components; 21. Flight motor; 22. Rotary mount; 23. Flight blades;

[0028] 30. Battery;

[0029] 40. Adjustment assembly; 41. Adjustment seat; 42. Drive component; 421. Lifting rod; 422. Servo motor; 423. Transmission component; 4231. Swing frame; 4232. Swing rod; 4233. Swing seat; 43. Lifting seat; 44. Hinge seat; 45. Hinge frame;

[0030] 50. Spraying assembly; 51. Liquid storage tank; 52. Solenoid valve; 53. Spray nozzle. Detailed Implementation

[0031] To make the utility model's objectives, features, and advantages more apparent and understandable, the technical solutions in the embodiments of the utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the embodiments described below are only some embodiments of the utility model, not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the utility model without creative effort are within the scope of protection of the utility model.

[0032] In the description of this utility model, it should be understood that the terms "upper," "lower," "top," "bottom," "inner," and "outer," etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model. It should be noted that when a component is considered to be "connected" to another component, it can be directly connected to the other component or there may be a component centrally located at the same time.

[0033] The technical solution of this utility model will be further described below with reference to the accompanying drawings and specific embodiments.

[0034] This utility model embodiment provides a quadcopter drone, such as Figures 1 to 5As shown, the device includes a fuselage 10, on which four flight components 20 are mounted. A battery 30 for providing power to the flight components 20 is mounted at the bottom of the fuselage 10. Each flight component 20 includes a flight motor 21 mounted on the fuselage 10. A rotating base 22 is fixedly mounted on the output shaft of the flight motor 21. Two flight blades 23 are centrally symmetrically arranged at both ends of the rotating base 22. The thickness of each flight blade 23 decreases in the width direction.

[0035] The fuselage 10 is also equipped with an adjustment assembly 40 adapted to the flight assembly 20. The adjustment assembly 40 includes two adjustment seats 41, which are rotatably connected to the two ends of the rotating seat 22. The flight blades 23 are fastened to the adjustment seats 41 one by one.

[0036] It should be noted that the quadcopter drone provided by this utility model, through the setting of two adjustment seats 41, allows the flight blades 23 to flexibly adjust their angle of attack as needed, thereby enabling more precise control of the drone's flight attitude and improving flight stability and maneuverability. The introduction of the adjustment component 40 not only allows the angle of attack of the flight blades 23 to be adjusted according to changes in flight attitude, but also optimizes the aerodynamic characteristics of the flight blades 23 during flight, thereby improving the drone's flight stability in complex environments. Especially in flight missions with strong winds or complex conditions, adjusting the blade angle of attack can effectively cope with external disturbances and improve flight control precision. Due to the adjustable angle of attack, the quadcopter drone of this invention has stronger adaptability in various complex environments. Whether it is agricultural plant protection, power line inspection, emergency rescue, or environmental monitoring, the angle of the flight blades 23 can be adjusted in real time according to different flight requirements to ensure efficient mission completion. Therefore, this utility model solves the technical problem of difficulty in adjusting the angle of attack of the flight blades 23 in existing quadcopter drones.

[0037] like Figures 1 to 4 As shown, the adjustment assembly 40 also includes a drive member 42 and a lifting seat 43 sleeved on the output shaft of the flight motor 21. Both adjustment seats 41 are hinged to the lifting seat 43 through a hinge seat 44. The drive member 42 is used to drive the lifting seat 43 to move up and down in the first direction.

[0038] In practical implementation, two adjusting seats 41 are hinged to the lifting seat 43, and the lifting seat 43 is moved up and down in the first direction by the driving component 42. This allows the two adjusting seats 41 to rotate synchronously during the movement of the lifting seat 43, thereby achieving coordinated adjustment of the angle of attack of the two flight blades 23. This structural design avoids the complexity of setting independent adjustment devices for each flight blade 23, improving the overall consistency and reliability of the system. Since the driving component 42 can precisely drive the lifting seat 43, it can drive the flight blades 23 to achieve fine angle adjustments. This allows the UAV to respond quickly to attitude control commands during flight and accurately adjust its flight state, thereby improving the overall flight control accuracy and flight stability. It is particularly suitable for flight environments with frequent wind speed changes or requiring precise operation. In different mission scenarios (such as high-speed flight, hovering, and load transportation), the angle of attack of the flight blades 23 can be adjusted in real time by the driving component 42 to achieve dynamic adjustment of thrust output, thereby optimizing power distribution and attitude control strategies. This technology enables the UAV to have stronger adaptability in complex environments, significantly improving flight flexibility and mission execution efficiency.

[0039] like Figures 1 to 4 As shown, the drive unit 42 includes a lifting rod 421 that is sleeved with the lifting seat 43. A servo motor 422 is mounted on the fuselage 10. The lifting rod 421 and the servo motor 422 are connected through a transmission component 423. The servo motor 422 is used to provide driving power for the movement of the lifting rod 421 according to the flight attitude of the UAV. In this embodiment, the flight attitude of the UAV can be detected by an angle sensor or other detection equipment, which will not be described in detail here.

[0040] In practical implementation, the core of the drive unit 42 is that the servo motor 422 drives the elevator 421 to rise and fall. The servo motor 422 automatically adjusts the height of the elevator 43 according to the flight attitude, thereby precisely adjusting the angle of attack of the flight blades 23. The high-precision control of the servo motor 422 can adjust the flight status in real time according to the flight mission, ensuring the sensitivity and accuracy of attitude adjustment during flight. Through the cooperation of the servo motor 422 and the elevator 421, the UAV can dynamically adjust the blade angle during flight. By sensing the flight attitude and automatically driving the rise and fall of the elevator 43, the angle of attack of the flight blades 23 is kept optimally matched with the flight attitude, effectively improving the stability and adaptability of the UAV. Especially in complex environments (such as airflow changes, obstacle avoidance, etc.), the servo motor 422 can provide real-time adjustments, allowing the UAV to always maintain an ideal flight attitude.

[0041] like Figures 1 to 4As shown, the transmission component 423 includes a swing frame 4231 rotatably connected to the fuselage 10. One end of the lifting rod 421, away from the lifting seat 43, is connected to the swing frame 4231. A swing rod 4232 is also connected to the swing frame 4231. A swing seat 4233 connected to the swing rod 4232 is mounted on the output shaft of the servo motor 422. In this embodiment, a hinge frame 45 is fixedly mounted on the fuselage 10, and the swing frame 4231 is rotatably connected to the hinge frame 45.

[0042] In practical implementation, the use of the swing frame 4231 and the lifting rod 421 in conjunction allows the lifting rod 421 to move up and down within a wider range, providing a broader adjustment space. Through the linkage between the swing frame 4231 and the swing rod 4232, the drive of the servo motor 422 can be transmitted to the lifting seat 43 more precisely, realizing fine adjustment of the angle of attack of the flight blade 23, thereby improving the accuracy and response speed of flight attitude adjustment.

[0043] It should be noted that the servo motor 422 drives the swing seat 4233 to move, which in turn causes the swing rod 4232 to drive the swing frame 4231 to swing. Since the swing frame 4231 is connected to the lifting rod 421, the swing frame 4231 drives the lifting rod 421 to move up and down. Since the lifting rod 421 is sleeved with the lifting seat 43, the lifting seat 43 moves up and down in the first direction, causing the adjusting seat 41 to rotate on the rotating seat 22, thereby adjusting the angle of attack of the flight blade 23.

[0044] like Figure 1 and Figure 5 As shown, a spraying assembly 50 for spraying liquid is also installed on the fuselage 10. The spraying assembly 50 includes a liquid storage tank 51, a solenoid valve 52, and a nozzle 53 connected by interconnected pipelines. The liquid storage tank 51 is fixedly installed in the middle of the fuselage 10, and the solenoid valve 52 is fixedly installed on the fuselage 10 and is used to control the liquid spraying volume of the nozzle 53. In this embodiment, the number of solenoid valves 52 and nozzles 53 is set to four, and the solenoid valves 52, nozzles 53, and flight assembly 20 correspond one-to-one.

[0045] It should be noted that since each solenoid valve 52 and nozzle 53 in the spraying assembly 50 corresponds one-to-one with the flight assembly 20, the drone can control the opening and closing of each nozzle 53 according to the flight status, thereby achieving precise control of the spraying range and spray volume. Compared with the traditional uniform spraying method, this structure has higher spraying flexibility and precision, and is particularly suitable for scenarios such as agricultural plant protection and precision pest control. Since the liquid storage tank 51 is located in the middle of the fuselage 10, it helps to center the center of gravity, making the flight more stable. At the same time, the four nozzles 53 are distributed throughout the fuselage 10 and spray evenly, effectively avoiding problems such as uneven spraying and omissions, and significantly improving the uniformity of operation and spray coverage. Because the spraying assembly 50 has good modularity and independent control capabilities, the drone can flexibly adapt to different spraying tasks (such as pesticides, disinfectants, liquid fertilizers, etc.) and adjust the spraying strategy according to task requirements (such as fixed-point spraying, intermittent spraying, or quantitative spraying), expanding the application scope of drones in agriculture, public health, environmental protection and other fields. The solenoid valve 52 enables dynamic adjustment of the sprayed liquid, which can work with the flight control system to adjust the spray volume in real time according to parameters such as terrain, speed, and altitude, so as to achieve the purpose of spraying on demand, improve spraying accuracy, reduce resource waste, and improve operation efficiency.

[0046] Working Principle: This invention provides a quadcopter drone that, through the setting of two adjustment seats 41, allows the flight blades 23 to flexibly adjust their angle of attack as needed, thereby enabling more precise control of the drone's flight attitude and improving flight stability and maneuverability. The introduction of the adjustment component 40 not only allows the angle of attack of the flight blades 23 to be adjusted according to changes in flight attitude, but also optimizes the aerodynamic characteristics of the flight blades 23 during flight, thus improving the drone's flight stability in complex environments. Especially in flight missions with strong winds or complex conditions, adjusting the blade angle of attack can effectively cope with external disturbances and improve flight control precision. Due to the adjustable angle of attack, the quadcopter drone of this invention has stronger adaptability in various complex environments. Whether it is agricultural plant protection, power line inspection, emergency rescue, or environmental monitoring, the angle of the flight blades 23 can be adjusted in real time according to different flight requirements to ensure efficient mission completion. Therefore, this invention solves the technical problem of difficulty in adjusting the angle of attack of the flight blades 23 in existing quadcopter drones.

[0047] The above-described embodiments are only used to illustrate the technical solutions of this utility model, and are not intended to limit it. Although this utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this utility model.

Claims

1. A quadcopter drone, characterized in that, The device includes a fuselage (10) on which four flight components (20) are mounted. A battery (30) for providing power to the flight components (20) is installed at the bottom of the fuselage (10). Each flight component (20) includes a flight motor (21) mounted on the fuselage (10). The output shaft of the flight motor (21) is fixedly mounted with a rotating base (22). Two flight blades (23) are distributed at both ends of the rotating base (22) in a centrally symmetrical arrangement. The fuselage (10) is also equipped with an adjustment assembly (40) adapted to the flight assembly (20). The adjustment assembly (40) includes two adjustment seats (41), which are rotatably connected to the two ends of the rotating seat (22). The flight blades (23) are fastened to the adjustment seats (41).

2. The quadcopter drone according to claim 1, characterized in that, The adjustment assembly (40) also includes a drive unit (42) and a lifting seat (43) sleeved on the output shaft of the flight motor (21). Both adjustment seats (41) are hinged to the lifting seat (43) through a hinge seat (44). The drive unit (42) is used to drive the lifting seat (43) to move up and down in a first direction.

3. The quadcopter drone according to claim 2, characterized in that, The drive unit (42) includes a lifting rod (421) sleeved with the lifting seat (43). A servo motor (422) is installed on the fuselage (10). The lifting rod (421) and the servo motor (422) are connected through a transmission component (423). The servo motor (422) is used to provide driving power for the movement of the lifting rod (421) according to the flight attitude of the UAV.

4. The quadcopter drone according to claim 3, characterized in that, The transmission component (423) includes a swing frame (4231) rotatably connected to the fuselage (10), and the end of the lifting rod (421) away from the lifting seat (43) is connected to the swing frame (4231). A swing rod (4232) is also connected to the swing frame (4231), and a swing seat (4233) connected to the swing rod (4232) is mounted on the output shaft of the servo motor (422).

5. The quadcopter drone according to claim 1, characterized in that, The thickness of each of the flight blades (23) decreases in the width direction.

6. The quadcopter drone according to any one of claims 1 to 5, characterized in that, The fuselage (10) is also equipped with a spraying assembly (50) for spraying liquid.

7. The quadcopter drone according to claim 6, characterized in that, The spraying assembly (50) includes a liquid storage tank (51), a solenoid valve (52), and a nozzle (53) connected by interconnected pipelines. The liquid storage tank (51) is fixedly installed in the middle of the body (10), and the solenoid valve (52) is fixedly installed on the body (10) and used to control the liquid spraying volume of the nozzle (53).

8. The quadcopter drone according to claim 7, characterized in that, The number of the solenoid valve (52) and the nozzle (53) is set to four, and the solenoid valve (52), the nozzle (53) and the flight component (20) correspond one-to-one.

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