Four-rotor unmanned aerial vehicle

Abstract

The four-rotor unmanned aerial vehicle comprises a vehicle body shell, the vehicle body shell comprises a left vehicle body and a right vehicle body, an upper cabin cover is arranged at the upper end of the vehicle body shell, and a central vehicle body structure is arranged in the vehicle body shell and the upper cabin cover; the four sets of arm folding parts are arranged and connected to the four corners of the aircraft body shell, arm carbon tubes are arranged at the other ends of the arm folding parts, an electronic speed controller is arranged at the other ends of the arm carbon tubes, a motor is arranged at one end of the electronic speed controller, propeller clamps are arranged at the output ends of the motor and the motor, and propellers are arranged in the propeller clamps. And the number of the undercarriage structures is two, and the two undercarriage structures are located on the two sides of the lower end of the aircraft body shell. Compared with the prior art, the foldable unmanned aerial vehicle has the advantages of being good in operability and stability, high in space utilization rate and capable of reducing storage space due to the fact that the vehicle arms can be folded.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a four-rotor unmanned aerial vehicle. Background Art

[0002] Existing drones generally have problems such as taking up too much space when not in use or when transporting, being inconvenient to carry, having a short battery life, or having a small load capacity. Therefore, how to reduce the footprint of drones when not in use, increase their portability, ensure their battery life, and increase their load capacity is an important issue currently facing the research of rotary-wing drones. Utility Model Content

[0003] The technical problem to be solved by the utility model is to overcome the above technical defects and provide a four-rotor unmanned aerial vehicle with good operability and stability, high space utilization, and foldable arms to reduce storage space.

[0004] In order to solve the above problems, the technical solution of the utility model is: a four-rotor drone, comprising:

[0005] A fuselage shell, the fuselage shell comprising a left fuselage and a right fuselage, an upper hatch being provided at the upper end of the fuselage shell, and a central fuselage structure being provided inside the fuselage shell and the upper hatch;

[0006] Arm folding parts, there are four groups of arm folding parts, the arm folding parts are connected to the four corners of the body shell, the other end of the arm folding parts is provided with an arm carbon tube, the other end of the arm carbon tube is provided with an electric regulator, one end of the electric regulator is provided with a motor, the motor, the output end of the motor is provided with a propeller clamp, and the propeller clamp is provided with a propeller;

[0007] The landing gear structure has two groups, and the two groups of landing gear structures are located on both sides of the lower end of the fuselage shell.

[0008] Further, the arm folding member comprises:

[0009] The fuselage is connected to the carbon plate, one end of which is plugged into the interior of the fuselage shell, and the other end of which is connected to the cylinder;

[0010] An adjusting wrench, one end of which is hingedly connected to one side of the connecting tube, and the other end of which is hingedly provided with a connecting rod;

[0011] A connecting carbon tube, one end of which is hinged to the other side of the connecting tube, the other end of which is hinged to one end of the connecting rod, and the arm carbon tube is plugged into the interior of the connecting carbon tube.

[0012] Further, the landing gear structure comprises:

[0013] A landing gear connecting piece, wherein the landing gear connecting piece is provided with a hand screw;

[0014] A landing gear vertical carbon tube, one end of which is plugged into the interior of the landing gear connector;

[0015] The landing gear transverse carbon tube is provided with a carbon tube connector on its surface, and the other end of the landing gear vertical carbon tube is plugged into the carbon tube connector.

[0016] Furthermore, the central body structure includes a carbon plate, which has five layers. Pillars are provided between the five layers of the carbon plates, and a landing gear supporting carbon plate and a cabin body supporting carbon plate are provided on the upper ends of the carbon plates.

[0017] Furthermore, a mission payload quick-release part is provided at the lower end of the fuselage shell, a hatch is provided around the fuselage shell, an omnidirectional obstacle avoidance radar is provided at the upper end of the fuselage shell, antennas are provided on both sides of the omnidirectional obstacle avoidance radar, and the electric controller is provided with a motor indicator light.

[0018] The advantages of the utility model compared with the existing technology are:

[0019] (1) The foldable arms of the utility model can greatly reduce the size of the drone, making it easier to carry and store. The foldable arms can reduce the protruding parts of the drone when it is not in operation, reducing the risk of collision with the environment and other objects. The foldable arms make it easier to repair, replace and upgrade the parts of the drone. The design of the foldable arms can add more functions to the drone, such as additional cameras, sensors, etc., thereby improving the diversity and adaptability of the drone.

[0020] (2) The utility model adopts a quad-rotor as the power of the UAV, which has good stability, simple operation, and is easy to control and fly. Carbon plates are used as the main load-bearing components, and aluminum columns made of aluminum materials are selected between the carbon plates to connect the carbon plates. Carbon fiber materials have very high strength and rigidity, so that the structural parts made of carbon fiber can maintain good strength and rigidity under large loads, thereby improving stability;

[0021] (3) The utility model has a large cargo space and multiple mission payload hanging points: UAVs will be used in many different scenarios and will carry different mission payloads during use. When carrying different mission payloads, it is necessary to have a cargo platform with sufficient space and multiple mission payload hanging points so that the UAV can switch mission scenarios more easily. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a stereogram of a four-rotor unmanned aerial vehicle of the present utility model.

[0023] Figure 2 It is an exploded view of a four-rotor unmanned aerial vehicle of the present utility model.

[0024] Figure 3 The utility model is a three-dimensional diagram of a folding arm of a four-rotor unmanned aerial vehicle.

[0025] Figure 4 The utility model is an exploded diagram of the landing gear structure of a four-rotor unmanned aerial vehicle.

[0026] Figure 5 The utility model is a three-dimensional diagram of the central body structure of a four-rotor unmanned aerial vehicle.

[0027] As shown in the figure: 1. Fuselage shell; 2. Left fuselage; 3. Right fuselage; 4. Upper hatch; 5. Center fuselage structure; 6. Folding arm; 7. Carbon tube of the arm; 8. Electric adjustment; 9. Motor; 10. Propeller clamp; 11. Propeller; 12. Landing gear structure; 13. Fuselage connecting carbon plate; 14. Connecting tube; 15. Adjusting wrench; 16. Connecting rod; 17. Connecting carbon tube; 18. Landing gear connecting piece; 19. Thumb screw; 20. Vertical carbon tube of landing gear; 21. Horizontal carbon tube of landing gear; 22. Connecting piece; 23. Carbon plate; 24. Pillar; 25. Landing gear supporting carbon plate; 26. Cabin supporting carbon plate; 27. Mission payload quick-release parts; 28. Hatch; 29. ​​Radar; 30. Antenna; 31. Motor indicator light. DETAILED DESCRIPTION

[0028] The specific implementation of the utility model is further described below in conjunction with the accompanying drawings, wherein the same parts are represented by the same reference numerals.

[0029] It should be noted that the words "front", "rear", "left", "right", "up" and "down" used in the following description refer to directions in the drawings, and the words "inside" and "outside" refer to directions toward or away from the geometric center of a specific component, respectively.

[0030] In order to make the contents of the present invention more clearly understood, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention.

[0031] Embodiment 1

[0032] like Figures 1 to 5 As shown, a quad-rotor UAV includes a body shell 1, the body shell 1 includes a left fuselage 2 and a right fuselage 3, an upper hatch 4 is installed on the upper end of the body shell 1, a mission payload quick-release part 27 is installed on the lower end of the body shell 1, a hatch 28 is installed around the body shell 1, an omnidirectional obstacle avoidance radar 29 is installed on the upper end of the body shell 1, and antennas 30 are installed on both sides of the omnidirectional obstacle avoidance radar 29.

[0033] A central fuselage structure 5 is installed inside the fuselage shell 1 and the upper hatch 4. The central fuselage structure 5 includes a carbon plate 23. The carbon plate 23 has five layers. Support pillars 24 are installed between the five layers of carbon plates 23. A landing gear supporting carbon plate 25 and a cabin supporting carbon plate 26 are installed on the upper end of the carbon plate 23.

[0034] The connection between the carbon plates 23 is an assembly connection, in which a protruding structure on one carbon plate 23 is inserted into a hole of another carbon plate 23 connected thereto for assembly.

[0035] The arm folding part 6 has four groups. The arm folding part 6 is connected to the four corners of the body shell 1. The arm carbon tube 7 is installed at the other end of the arm folding part 6. The electric adjustment 8 is installed at the other end of the arm carbon tube 7. The electric adjustment 8 is installed with a motor indicator light 31. The motor 9 is installed at one end of the electric adjustment 8. The propeller clamp 10 is installed at the output end of the motor 9. The propeller 11 is installed inside the propeller clamp 10. The connection between the arm carbon tube 7 and the motor 9 and the arm folding part 6 is plug-in. The arm carbon tube 7 is inserted into the hole reserved in the motor 9. Screw holes are reserved on the motor 9. In order to prevent the arm carbon tube 7 from deviating or falling, the connection is locked with screws.

[0036] The arm folding member 6 includes a fuselage connecting carbon plate 13, one end of the fuselage connecting carbon plate 13 is inserted into the body shell 1, the other end of the fuselage connecting carbon plate 13 is connected to the tube 14, one end of the adjusting wrench 15 is hinged to one side of the connecting tube 14, the other end of the adjusting wrench 15 is hinged to the installation connecting rod 16, one end of the connecting carbon tube 17 is hinged to the other side of the connecting tube 14, the other end of the connecting carbon tube 17 is hinged to one end of the connecting rod 16, the arm carbon tube 7 is inserted into the interior of the connecting carbon tube 17, and the arm folding member 6 includes a fuselage connecting carbon plate 13, one end of the fuselage connecting carbon plate 13 is inserted into the interior of the body shell 1, and the other end of the fuselage connecting carbon plate 13 is connected to the tube 14. When the arm carbon tube 7 is opened, the arm carbon tube 7 is bent outward so that the axis of the arm carbon tube 7 and the arm folding part 6 are in a straight line, and then the adjusting wrench 15 is tightened inward with force, and the arm carbon tube 7 is unfolded; when the arm carbon tube 7 is folded, one hand is used to force the adjusting wrench 15 outward, and the other hand is used to bend the arm carbon tube 7 inward. When the adjusting wrench 15 is unfolded, the arm carbon tube 7 is bent until it is perpendicular to the side of the body shell 1, and the folding of the arm carbon tube 7 is completed.

[0037] The landing gear structure 12 has two groups. The two groups of landing gear structures 12 are located on both sides of the lower end of the fuselage shell 1. The landing gear structure 12 includes a landing gear connector 18. The landing gear connector 18 is installed at the lower end of the fuselage shell 1. The landing gear connector 18 is installed with a hand screw 19. One end of the landing gear vertical carbon tube 20 is plugged into the inside of the landing gear connector 18 and fixed by the hand screw 19. The carbon tube connector 22 is installed on the surface of the landing gear transverse carbon tube 21, and the other end of the landing gear vertical carbon tube 20 is plugged into the inside of the carbon tube connector 22.

[0038] Embodiment 2

[0039] Described on the basis of the first embodiment, when installing the landing gear structure 12, the landing gear connecting piece 18 is limited in the front, rear, left and right directions. At this time, the landing gear vertical carbon tube 20 can also move up and down. The landing gear vertical carbon tube 20 is moved to a suitable position, and then the hand screw 19 is tightened. The hand screw 19 presses the groove of the landing gear connecting piece 18. At this time, the displacement of the landing gear vertical carbon tube 20 in three directions is limited, and the landing gear structure 12 is installed; when disassembling the landing gear structure 12, loosen the hand screw 19, pull out the landing gear vertical carbon tube 20, and the landing gear structure 12 is disassembled.

[0040] When the arm carbon tube 7 is opened, the arm carbon tube 7 is bent outward so that the axis of the arm carbon tube 7 and the arm folding part 6 are in a straight line, and then the adjusting wrench 15 is tightened inward with force, and the arm carbon tube 7 is unfolded; when the arm carbon tube 7 is folded, one hand is used to force the adjusting wrench 15 outward, and the other hand is used to bend the arm carbon tube 7 inward. When the adjusting wrench 15 is unfolded, the arm carbon tube 7 is bent until it is perpendicular to the side of the body shell 1, and the folding of the arm carbon tube 7 is completed.

[0041] The above description of the utility model and its implementation methods is not restrictive. The drawings show only one implementation method of the utility model, and the actual structure is not limited thereto. In short, if ordinary technicians in this field are inspired by it and design structural methods and embodiments similar to the technical solution without creativity without departing from the purpose of the invention of the utility model, they should all fall within the protection scope of the utility model.

Claims

1. A quad-rotor drone, characterized in that: include: A fuselage shell (1), the fuselage shell (1) comprising a left fuselage (2) and a right fuselage (3), an upper hatch (4) being provided at the upper end of the fuselage shell (1), and a central fuselage structure (5) being provided inside the fuselage shell (1) and the upper hatch (4); An arm folding member (6), wherein the arm folding member (6) has four groups, and the arm folding member (6) is connected to the four corners of the body shell (1); the other end of the arm folding member (6) is provided with an arm carbon tube (7); the other end of the arm carbon tube (7) is provided with an electric regulator (8); one end of the electric regulator (8) is provided with a motor (9); the motor (9); a propeller clamp (10) is provided at the output end of the motor (9); a propeller (11) is provided inside the propeller clamp (10); A landing gear structure (12), wherein the landing gear structure (12) has two groups, and the two groups of the landing gear structure (12) are located on both sides of the lower end of the fuselage shell (1).

2. A quadrotor drone according to claim 1, characterized in that: The machine arm folding member (6) comprises: A fuselage connecting carbon plate (13), one end of the fuselage connecting carbon plate (13) is plugged into the interior of the fuselage shell (1), and the other end of the fuselage connecting carbon plate (13) is connected to the cylinder (14); An adjusting wrench (15), one end of the adjusting wrench (15) is hingedly connected to one side of the connecting tube (14), and the other end of the adjusting wrench (15) is hingedly provided with a connecting rod (16); A connecting carbon tube (17) is provided, wherein one end of the connecting carbon tube (17) is hinged to the other side of the connecting tube (14), the other end of the connecting carbon tube (17) is hinged to one end of the connecting rod (16), and the machine arm carbon tube (7) is plugged into the interior of the connecting carbon tube (17).

3. A quad-rotor drone according to claim 1, characterized in that: The landing gear structure (12) comprises: A landing gear connecting piece (18), wherein the landing gear connecting piece (18) is provided with a hand screw (19); A landing gear vertical carbon tube (20), one end of which is plugged into the interior of a landing gear connecting piece (18); A landing gear transverse carbon tube (21), wherein a carbon tube connector (22) is sleeved on the surface of the landing gear transverse carbon tube (21), and the other end of the landing gear vertical carbon tube (20) is plugged into the interior of the carbon tube connector (22).

4. A quad-rotor drone according to claim 1, characterized in that: The central body structure (5) comprises a carbon plate (23), wherein the carbon plate (23) has five layers, pillars (24) are arranged between the five layers of the carbon plates (23), and a landing gear supporting carbon plate (25) and a cabin supporting carbon plate (26) are arranged at the upper end of the carbon plate (23).

5. The quad-rotor drone according to claim 1, characterized in that: The lower end of the body shell (1) is provided with a mission load quick-release part (27), the body shell (1) is provided with a hatch (28) around it, the upper end of the body shell (1) is provided with an omnidirectional obstacle avoidance radar (29), antennas (30) are provided on both sides of the omnidirectional obstacle avoidance radar (29), and the electric regulator (8) is provided with a motor indicator light (31).

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