Small folding unmanned aerial vehicle

Abstract

The small-sized folding unmanned aerial vehicle is characterized by comprising a vehicle body, front wings, rear wings and double vertical tails, the machine body is of a front-round rear-round structure. The front wings are arranged above the front part of the fuselage in a foldable manner, and the folded front wings are arranged above the fuselage in a folding and overlapping manner; the rear wings are arranged below the rear portion of the fuselage in a foldable mode, and the folded rear wings are arranged below the fuselage in a folded and overlapped mode. The double vertical fins are foldably arranged on the rear side surface of the tail part of the fuselage; through the arrangement, the wings can be folded at the top of the fuselage and the lower part of the fuselage, so that the whole unmanned aerial vehicle becomes smaller and is convenient to carry, and the technical problem that the unmanned aerial vehicle is inconvenient to carry by working personnel due to the fact that the unmanned aerial vehicle is larger in overall size and occupies larger space is solved.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles (UAVs), in particular to a small foldable UAV. Background Art

[0002] Currently, drones are mainly divided into fixed-wing drones and multi-rotor drones. However, there are many scenarios in which drones are used, and sometimes it is necessary to carry multiple drones for work. However, due to the wings and propellers, the overall size of drones is larger and they occupy a larger space, making it inconvenient for workers to carry them. Utility Model Content

[0003] In view of this, the present application provides a small foldable drone that can be folded. The folded drone is compact and easy to carry.

[0004] According to one aspect of the present application, a small folding drone is provided, comprising a fuselage, front wings, rear wings and double vertical tails; the fuselage has a structure with a round front and a square rear; the front wings are foldably arranged above the front of the fuselage, and after folding, the front wings are folded and overlapped with each other and arranged above the fuselage; the rear wings are foldably arranged below the rear of the fuselage, and after folding, the rear wings are folded and overlapped with each other and arranged below the fuselage; the double vertical tails are foldably arranged on the rear side of the rear of the fuselage.

[0005] In a possible implementation, the front wing is folded backward by rotation, and the rear wing is folded forward by rotation.

[0006] In a possible implementation, the width of the front wing is less than or equal to the width of the fuselage; the width of the rear wing is less than or equal to the width of the fuselage.

[0007] In a possible implementation, the length of the front wing is the same as the length of the fuselage, and the length of the rear wing is smaller than the length of the fuselage.

[0008] In a possible implementation, the twin vertical tails are folded backward by rotation, and are located on both sides of the fuselage after being folded.

[0009] In one possible implementation, the head of the fuselage is circular, and the rear of the fuselage is a rectangular structure; the top of the front wing is an arc-shaped structure, and the bottom of the front wing is a rectangular structure; the top of the rear wing is an arc-shaped structure, and the bottom of the rear wing is a rectangular structure.

[0010] In a possible implementation, it also includes a gimbal camera and a landing gear; the gimbal camera is rotatably arranged at the head of the fuselage; the landing gear is an inverted triangular structure, and there are four landing gears, two of which are detachably arranged at the bottom of both sides of the front position of the fuselage, and the other two landing gears are detachably arranged at the bottom of both sides of the rear position of the fuselage.

[0011] In a possible implementation, a load compartment is further provided in the middle portion of the fuselage.

[0012] In one possible implementation, it also includes a power system and a flight control system; the power system is arranged at the tail of the fuselage for providing power; the flight control system is arranged inside the fuselage, and the aircraft control system includes a customized flight module, which can form a formation of aircraft to ensure that one ground controller can simultaneously control multiple aircraft to perform different tasks; the flight control system is electrically connected to the power system.

[0013] In a possible implementation, a carbon fiber hood is installed at the head of the fuselage to reduce wind resistance.

[0014] The beneficial effects of the present invention are as follows: by arranging a fuselage, front wings, rear wings and double vertical tails; the fuselage has a structure with a round front and a square rear, and such an arrangement is intended to reduce wind resistance; the front wings are foldably arranged above the front part of the fuselage, and after folding, the front wings are folded and overlapped with each other and arranged above the fuselage. When in use, the front wings are opened, and when not in use, the front wings are folded up; the rear wings are foldably arranged below the rear part of the fuselage, and after folding, the rear wings are folded and overlapped with each other and arranged below the fuselage. When in use, the rear wings are opened, and when not in use, the rear wings are folded up; the double vertical tails are foldably arranged on the rear side of the rear fuselage; through the above arrangement, the wings of the present application can be folded at the top and bottom of the fuselage, making the whole smaller and easier to carry.

[0015] Other features and aspects of the present application will become apparent from the following detailed description of exemplary embodiments with reference to the attached drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The accompanying drawings, which are incorporated in and constitute a part of the specification, illustrate exemplary embodiments, features, and aspects of the application and, together with the description, serve to explain the principles of the application.

[0017] Figure 1 A diagram showing the unfolded structure of a small foldable drone capable of forming a formation according to an embodiment of the present application;

[0018] Figure 2A folding diagram showing a small foldable drone capable of forming a formation according to an embodiment of the present application. DETAILED DESCRIPTION

[0019] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0020] Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar symbols throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, and should not be construed as limiting the present invention.

[0021] In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like to indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention or simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation to the present invention.

[0022] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature specified as "first" or "second" may explicitly or implicitly include one or more of such features. In the description of this utility model, "plurality" means two or more, unless otherwise specifically defined.

[0023] In this utility model, unless otherwise expressly specified or limited, terms such as "installed," "connected," "connect," "fixed," "joined," and "hinge" should be understood in a broad sense. For example, they may refer to fixed or detachable connections, or integration; they may refer to mechanical or electrical connections; they may refer to direct connections or indirect connections through an intermediate medium; they may refer to internal communication between two components or the interaction between two components. Those skilled in the art will be able to understand the specific meanings of the above terms in this utility model based on specific circumstances.

[0024] like Figures 1 to 2As shown, the small foldable UAV includes a fuselage 100, a front wing 210, a rear wing 220 and a double vertical tail 300; the fuselage 100 has a structure with a round front and a square rear; the front wing 210 is foldably arranged above the front of the fuselage 100, and after folding, the front wings 210 are folded and overlapped and arranged above the fuselage 100; the rear wing 220 is foldably arranged below the rear of the fuselage 100, and after folding, the rear wings 220 are folded and overlapped and arranged below the fuselage 100; the double vertical tail 300 is foldably arranged on the rear side of the rear of the fuselage 100.

[0025] Specifically, the fuselage 100 is configured to have a front-round and rear-square structure, which is capable of reducing wind resistance. In order to reduce the overall size of the drone, the front wings 210 are foldably arranged above the front of the fuselage 100, and the rear wings 220 are foldably arranged below the rear of the fuselage 100. When not in use, the front wings 210 are folded up, with the front wings 210 folded above the fuselage 100 and the rear wings 220 folded below the fuselage 100, forming a long strip shape after folding.

[0026] In a possible implementation, the front wing 210 is folded backward by rotating, and the rear wing 220 is folded forward by rotating.

[0027] Specifically, in order to make the volume of the drone smaller after folding, the front wing 210 is folded backward and above the fuselage 100 after folding, and the rear wing 220 is folded forward and below the fuselage 100 after folding.

[0028] In a possible implementation, the width of the front wing 210 is less than or equal to the width of the fuselage 100 ; and the width of the rear wing 220 is less than or equal to the width of the fuselage 100 .

[0029] Specifically, such as Figure 2 As shown, the width of the front wing 210 is set to be less than or equal to the width of the fuselage 100, so that the front wing 210 does not exceed the width of the fuselage 100 after folding, and the width of the rear wing 220 is set to be less than or equal to the width of the fuselage 100, so that the rear wing 220 does not exceed the width of the fuselage 100 after folding.

[0030] In a possible implementation, the length of the front wing 210 is the same as the length of the fuselage 100 , and the length of the rear wing 220 is less than the length of the fuselage 100 .

[0031] Specifically, such as Figure 2As shown, the length of the front wing 210 is set to be the same as the length of the fuselage 100. This setting ensures that the length of the front wing 210 after folding does not exceed the length of the fuselage 100. The length of the rear wing 220 is set to be smaller than the length of the fuselage 100. This setting ensures that the length of the rear wing 220 after folding does not exceed the length of the fuselage 100, making the folded drone have a long strip shape.

[0032] In a possible implementation, the twin vertical tails 300 are folded backward by rotation and are located on both sides of the fuselage 100 after being folded.

[0033] Specifically, such as Figure 2 As shown, in order to make the drone occupy a smaller space after being folded, the double vertical tails 300 are also set to be foldable, so that the double vertical tails 300 can be folded backward by rotation and are on both sides of the fuselage 100 after being folded.

[0034] In one possible implementation, the head of the fuselage 100 is circular, and the rear of the fuselage 100 is a rectangular structure; the top of the front wing 210 is an arc-shaped structure, and the bottom of the front wing 210 is a rectangular structure; the top of the rear wing 220 is an arc-shaped structure, and the bottom of the rear wing 220 is a rectangular structure.

[0035] Specifically, such as Figure 1 As shown, in order to make the front wing 210 and the rear wing 220 fit more closely to the fuselage 100 after being folded, the top of the front wing 210 is an arc-shaped structure, and the bottom of the front wing 210 is a rectangular structure; the top of the rear wing 220 is an arc-shaped structure, and the bottom of the rear wing 220 is a rectangular structure. The front wing 210 and the rear wing 220 are set to such a structure in order to reduce wind resistance.

[0036] In a possible implementation, it also includes a gimbal camera 120 and a landing gear 130; the gimbal camera 120 is rotatably set at the head of the fuselage 100; the landing gear 130 is set in four numbers, two of which are detachably set at the bottom of both sides of the front position of the fuselage 100, and the other two landing gears 130 are detachably set at the bottom of both sides of the rear position of the fuselage 100.

[0037] Specifically, such as Figures 1 to 2 As shown, in order to complete the shooting, a gimbal camera 120 is provided at the head of the fuselage 100. The gimbal camera 120 is rotatable at the head of the fuselage 100 to fully capture the picture.

[0038] In one possible implementation, a payload compartment 110 is further provided in the middle portion of the fuselage 100.

[0039] Specifically, such as Figures 1 to 2As shown, the payload compartment can carry any small payload weighing 1.25 kg, including but not limited to radar, surveying equipment, etc.

[0040] In one possible implementation, it also includes a power system and a flight control system; the power system is arranged at the tail of the fuselage 100 to provide power; the flight control system is arranged inside the fuselage 100, and the aircraft control system includes a customized flight module, which can form a formation of aircraft; the flight control system and the power system are electrically connected.

[0041] Specifically, the power system is arranged at the tail of the fuselage 100 for providing power; the flight control system is arranged in the fuselage 100, and the aircraft control system is electrically connected to the power system. Such an arrangement can provide power to the aircraft control system so that the aircraft can fly. The aircraft control system includes a customized flight module, which can form a formation of aircraft to ensure that a ground controller can control multiple aircraft to perform different tasks at the same time. The aircraft can also work independently after the mission is planned without ground control, and the control program can be used to ensure that multiple aircraft do not interfere with each other; the power system includes a brushless motor, a brushless electric regulator and a ducted three-blade propeller 410; the ducted three-blade propeller The propeller 410 is electrically connected to the brushless motor and the brushless electronic regulator; when the three-blade propeller 410 rotates, a vortex is generated, and an anti-rotation plate is added to the fuselage 100 to overcome the spin generated by the three-blade propeller 410; in order to control the direction of flight, a control rudder 221 is provided on the rear wing 220, and two control rudders 221 are provided, which are respectively installed on the two rear wings 220; the aircraft control system also includes a GPS module, a data transmission module, a power distribution board, a receiver, and a servo; the customized flight module, GPS module and data transmission module are electrically connected to the power distribution board; the power distribution board is electrically connected to the receiver and the servo; the servo is electrically connected to the rudder 221.

[0042] Specifically, such as Figures 1 to 2 As described above, the brushless motor, brushless ESC and ducted three-blade propeller 410 are all arranged at the tail of the fuselage 100. After the drone is powered on, the three-blade propeller 410 starts to rotate. The built-in design of the ducted three-blade propeller 410 greatly improves the power of the drone and increases the endurance of the drone.

[0043] In one possible implementation, a carbon fiber hood is installed at the head of the fuselage 100 to reduce wind resistance.

[0044] The present application sets the fuselage 100 into a structure with a front rounded shape and a rear rounded shape by setting a power system and an aircraft control system. This structure can reduce wind resistance. In order to reduce the overall size of the drone, the front wings 210 are foldably arranged above the front of the fuselage 100, and the rear wings 220 are foldably arranged below the rear of the fuselage 100. When not in use, the front wings 210 are folded up, with the front wings 210 folded above the fuselage 100 and the rear wings 220 folded below the fuselage 100, forming a long strip shape when folded.

[0045] The use of a ducted three-blade propeller 410 built-in design greatly improves the power and endurance of the drone. An anti-rotation plate is set in the fuselage 100 to overcome the spin caused by the three-blade propeller 410. The payload compartment 110 is provided to carry any small payload weighing 1.25kg. It can carry a variety of mission payloads according to customer needs and meet multi-task operation requirements.

[0046] Through the above arrangement, the present application enables the wings to be folded at the top and bottom of the fuselage, making the overall unit smaller and easier to carry, thus solving the technical problem that the overall size of the drone is large, which occupies a large space and causes inconvenience to the crew members in carrying it.

[0047] The above description is only a preferred specific implementation method of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field, within the scope disclosed by the present invention, who makes equivalent replacements or changes based on the technical solution and concept of the present invention, should be covered by the protection scope of the present invention.

Claims

1. A small foldable drone, characterized in that: Including fuselage, front wing, rear wing and twin vertical tails; The fuselage has a structure with a round front and a square rear; The front wings are foldably arranged above the front portion of the fuselage, and after folding, the front wings are folded and overlapped with each other and arranged above the fuselage; The rear wings are foldably arranged below the rear portion of the fuselage, and after folding, the rear wings are folded and overlapped with each other and arranged below the fuselage; The double vertical tails are foldably arranged on the rear side of the tail of the fuselage.

2. The small foldable drone according to claim 1, characterized in that: The front wing is folded backward by rotating, and the rear wing is folded forward by rotating.

3. The small foldable drone according to claim 2, characterized in that: The width of the front wing is less than or equal to the width of the fuselage; The width of the rear wing is less than or equal to the width of the fuselage.

4. The small foldable drone according to claim 3, characterized in that: The length of the front wing is the same as the length of the fuselage, and the length of the rear wing is smaller than the length of the fuselage.

5. The small foldable drone according to any one of claims 1 to 4, characterized in that: The double vertical tails are folded backwards by rotation and are located on both sides of the fuselage after being folded.

6. The small foldable drone according to any one of claims 1 to 4, characterized in that: The head of the fuselage is circular, and the rear of the fuselage is a rectangular parallelepiped structure; The top of the front wing is an arc-shaped structure, and the bottom of the front wing is a rectangular structure; The top of the rear wing is an arc-shaped structure, and the bottom of the rear wing is a rectangular structure.

7. The small foldable drone according to any one of claims 1 to 4, characterized in that: Also included are the gimbal camera and landing gear; The pan-tilt camera is rotatably arranged on the head of the fuselage; The landing gear is an inverted triangular structure, and there are four landing gears. Two of the landing gears are detachably arranged at the bottom on both sides of the front position of the fuselage, and the other two landing gears are detachably arranged at the bottom on both sides of the rear position of the fuselage.

8. The small foldable drone according to any one of claims 1 to 4, characterized in that: A load compartment is also provided in the middle portion of the fuselage.

9. The small foldable drone according to any one of claims 1 to 4, characterized in that: It also includes power systems and flight control systems; The power system is arranged at the tail of the fuselage and is used to provide power; The flight control system is arranged in the fuselage, and the flight control system includes a customized flight module, which can form a formation of aircraft to ensure that one ground controller can control multiple aircraft to perform different tasks at the same time; The flight control system is electrically connected to the power system.

10. The small foldable drone according to any one of claims 1 to 3, characterized in that: A carbon fiber hood is installed at the head of the fuselage to reduce wind resistance.

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