Unmanned aerial vehicle with wings capable of being folded and automatically unfolded

Abstract

The unmanned aerial vehicle with the wings capable of being folded and automatically unfolded comprises a vehicle body, a left main wing and a right main wing are arranged on the vehicle body and arranged on the left side and the right side of the front portion of the vehicle body respectively, and a left auxiliary wing and a right auxiliary wing are arranged on the rear portion of the vehicle body. The left auxiliary wing and the right auxiliary wing are arranged on the left side and the right side of the rear portion of the fuselage respectively, main wing folding mechanisms are arranged at the connecting positions of the left main wing and the fuselage and the connecting positions of the right main wing and the fuselage, and the left main wing and the right main wing are rotationally folded towards the fuselage with the main wing folding mechanisms as shafts. An auxiliary wing folding mechanism is arranged at the junction of the left auxiliary wing and the right auxiliary wing on the fuselage, and the left auxiliary wing and the right auxiliary wing are rotationally folded towards the fuselage by taking the auxiliary wing folding mechanism as a shaft. And meanwhile, the storage space is reduced, and the use scene and the use reliability are improved. Meanwhile, the folding mechanism is simple, and the wings are folded by the same folding mechanism, so that the difficulty in assembly is avoided.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle with foldable and automatically deployable wings. Background Art

[0002] At present, in the field of unmanned aerial vehicles, in order to ensure the flight stability and convenient operation of unmanned aerial vehicles, unmanned aerial vehicles may be designed with longer wings. When the unmanned aerial vehicle is stored, the wings that expand left and right and up and down will occupy a large space. Therefore, at present, it is necessary to fold the wings of the unmanned aerial vehicle for easy storage. The patent 2020114135724 that has been publicly disclosed proposes a folding mechanism for a folding-wing unmanned aerial vehicle, which uses a single torsion spring drive method to achieve folding and unfolding, has a simple structure, is easy to install, occupies less space, has good synchronism, adopts an embedded cylindrical pin design, has a simple structure and reliable locking, and adopts a split structure design. When a problem occurs in the folding mechanism or a certain component of the wing, the problem component can be quickly replaced, greatly saving costs. Therefore, currently, those skilled in the art are all committed to the research and development of unmanned aerial vehicle folding technology. However, the current folding unmanned aerial vehicles have the following deficiencies: 1. The folding mechanism is complex, and the folding is completed through a complex structure, which increases the cost and precision of the product; 2. The assembly difficulty is large. Due to the complex structure, it is difficult to assemble during manufacturing, and assembly problems are likely to occur; 3. The reliability is poor. During storage, due to the large assembly difficulty, assembly problems are likely to occur, further resulting in the folding mechanism being unable to complete the folding work normally. Summary of the Utility Model

[0003] The purpose of the utility model is to provide an unmanned aerial vehicle with foldable and automatically deployable wings, which is composed of a fuselage, 2 main wings, 2 auxiliary wings, 2 tail wings, 1 main wing folding mechanism, 1 auxiliary wing folding mechanism, and 2 tail wing folding mechanisms. It can realize the folding of the main wings, auxiliary wings, and tail wings. After being released, the main wings, auxiliary wings, and tail wings can be automatically deployed through the springs in the folding mechanisms, solving the problems existing in the current folding unmanned aerial vehicles.

[0004] The utility model provides an unmanned aerial vehicle with foldable and automatically deployable wings, including a fuselage. A left main wing and a right main wing are arranged on the fuselage. The left main wing and the right main wing are respectively arranged on the left and right sides of the front part of the fuselage. A left auxiliary wing and a right auxiliary wing are arranged at the rear part of the fuselage. The left auxiliary wing and the right auxiliary wing are respectively arranged on the left and right sides of the rear part of the fuselage. A main wing folding mechanism is arranged at the connection between the left main wing and the right main wing and the fuselage. The left main wing and the right main wing are rotated and folded towards the fuselage with the main wing folding mechanism as the axis. A sub-wing folding mechanism is arranged at the junction of the left sub-wing and the right sub-wing and the fuselage. The left sub-wing and the right sub-wing are rotated and folded towards the fuselage with the sub-wing folding mechanism as the axis.

[0005] A further improvement lies in that: left and right tail fins are provided above the left and right auxiliary wings, the left tail fin is arranged on the left side of the fuselage through a left tail fin folding structure, and the right tail fin is arranged on the right side of the fuselage through a right tail fin folding structure.

[0006] A further improvement lies in that: a main wing storage groove is provided at the upper end of the fuselage, and the left and right main wings are retracted and stored in the main wing storage groove under the drive of a main wing folding mechanism.

[0007] A further improvement lies in that: an auxiliary wing storage groove is provided at the lower end of the rear part of the fuselage, and the left and right auxiliary wings are retracted and stored in the auxiliary wing storage groove under the drive of an auxiliary wing folding mechanism.

[0008] A further improvement lies in that: tail fin storage grooves are provided on both sides of the rear part of the fuselage, and the folded left and right tail fins are accommodated through the tail fin storage grooves.

[0009] A further improvement lies in that: limit blocks are provided beside the left tail fin folding structure and the right tail fin folding structure, and the rebound positions of the left and right tail fins are limited through the limit blocks.

[0010] A further improvement lies in that: adjusting wing plates are provided on both the left and right auxiliary wings, and the air flow angles of the left and right auxiliary wings are changed by changing the angles of the adjusting wing plates.

[0011] Advantages of the present utility model: It is convenient for the unmanned aerial vehicle to take off by using an ejection tube, while reducing the storage space, improving the usage scenarios and reliability of this type of folding-wing unmanned aerial vehicle. At the same time, due to its simple folding mechanism and the wings being folded by the same folding mechanism, it avoids the difficulty in assembly, has a low manufacturing cost, and the cost of the whole product will not increase too much, and it is reliable and practical. When the wings are stored, the wings are all placed in the corresponding storage grooves, avoiding damage caused by the wings protruding from the fuselage. Description of the Drawings

[0012] Figure 1 is a schematic diagram of the present utility model.

[0013] Figure 2 is a left side view of the structure of the present utility model.

[0014] Figure 3 is a bottom schematic diagram of the present utility model.

[0015] Figure 4 is a folding schematic diagram of the present utility model.

[0016] Wherein: 1 - fuselage, 2 - left main wing, 3 - right main wing, 4 - left auxiliary wing, 5 - right auxiliary wing, 6 - main wing folding mechanism, 7 - auxiliary wing folding mechanism, 8 - left tail wing, 9 - right tail wing, 10 - left tail wing folding structure, 11 - right tail wing folding structure, 12 - main wing storage groove, 13 - auxiliary wing storage groove, 14 - tail wing storage groove, 15 - limit stop, 16 - adjusting wing plate. Detailed implementation mode

[0017] In order to deepen the understanding of the present utility model, the present utility model will be further described in detail below in conjunction with embodiments. These embodiments are only used to explain the present utility model and do not constitute a limitation on the protection scope of the present utility model.

[0018] As Figures 1-4 shown, this embodiment provides a brand-new design of an unmanned aerial vehicle with foldable and automatically deployable wings. It includes a fuselage 1, on which a left main wing 2 and a right main wing 3 are arranged. The left main wing 2 and the right main wing 3 are respectively arranged on the left and right sides of the front part of the fuselage 1. On the rear part of the fuselage 1, a left auxiliary wing 4 and a right auxiliary wing 5 are arranged. The left auxiliary wing 4 and the right auxiliary wing 5 are respectively arranged on the left and right sides of the rear part of the fuselage 1. At the connection between the left main wing 2 and the right main wing 3 and the fuselage 1, a main wing folding mechanism 6 is provided. Taking the main wing folding mechanism 6 as an axis, the left main wing 2 and the right main wing 3 are rotated and folded towards the fuselage 1. At the junction of the left auxiliary wing 4 and the right auxiliary wing 5 and the fuselage 1, an auxiliary wing folding mechanism 7 is provided. Taking the auxiliary wing folding mechanism 7 as an axis, the left auxiliary wing 4 and the right auxiliary wing 5 are rotated and folded towards the fuselage 1. Above the left auxiliary wing 4 and the right auxiliary wing 5, a left tail wing 8 and a right tail wing 9 are arranged. The left tail wing 8 is arranged on the left side of the fuselage 1 through a left tail wing folding structure 10, and the right tail wing 9 is arranged on the right side of the fuselage 1 through a right tail wing folding structure 11. On the upper end of the fuselage 1, a main wing storage groove 12 is provided. The left main wing 2 and the right main wing 3 are retracted and stored in the main wing storage groove 12 under the drive of the main wing folding mechanism 6. At the lower end of the rear part of the fuselage 1, an auxiliary wing storage groove 13 is provided. The left auxiliary wing 4 and the right auxiliary wing 5 are retracted and stored in the auxiliary wing storage groove 13 under the drive of the auxiliary wing folding mechanism 7. On both sides of the rear part of the fuselage 1, tail wing storage grooves 14 are provided to accommodate the folded left tail wing 8 and right tail wing 9. Limit stops 15 are arranged beside the left tail wing folding structure 10 and the right tail wing folding structure 11 to limit the rebound positions of the left tail wing 8 and the right tail wing 9. Adjusting wing plates 16 are arranged on both the left auxiliary wing 4 and the right auxiliary wing 5 to change the airflow flow angles of the left auxiliary wing 4 and the right auxiliary wing 5 by changing the angles of the adjusting wing plates 16.

[0019] Each folding mechanism is built with a rotating shaft and a torsion spring. When an external force is used to rotate the wings and tail along the rotating shaft of the folding mechanism, all the wings and tail can be rotated and folded within the outer surface of the fuselage. When the external force is released, all the wings and tail will automatically unfold under the action of the built-in spring of the folding mechanism.

Claims

1. A drone with foldable and automatically unfoldable wings, comprising a fuselage (1), the fuselage (1) being provided with a left main wing (2) and a right main wing (3), the left main wing (2) and the right main wing (3) being respectively arranged on the left and right sides of the front of the fuselage (1), the fuselage (1) being provided with a left auxiliary wing (4) and a right auxiliary wing (5), the left auxiliary wing (4) and the right auxiliary wing (5) being respectively arranged on the left and right sides of the rear of the fuselage (1), characterized in that: A main wing folding mechanism (6) is provided at the connection between the left main wing (2) and the right main wing (3) and the fuselage (1), and the left main wing (2) and the right main wing (3) are rotated and folded toward the fuselage (1) with the main wing folding mechanism (6) as an axis; and an auxiliary wing folding mechanism (7) is provided at the junction of the left auxiliary wing (4) and the right auxiliary wing (5) with the fuselage (1), and the left auxiliary wing (4) and the right auxiliary wing (5) are rotated and folded toward the fuselage (1) with the auxiliary wing folding mechanism (7) as an axis.

2. The unmanned aerial vehicle with foldable and automatically unfoldable wings as claimed in claim 1, characterized in that: A left tail wing (8) and a right tail wing (9) are arranged above the left auxiliary wing (4) and the right auxiliary wing (5); the left tail wing (8) is arranged on the left side of the fuselage (1) via a left tail wing folding structure (10), and the right tail wing (9) is arranged on the right side of the fuselage (1) via a right tail wing folding structure (11).

3. The unmanned aerial vehicle with foldable and automatically unfoldable wings as claimed in claim 1, characterized in that: A main wing storage groove (12) is provided at the upper end of the fuselage (1), and the left main wing (2) and the right main wing (3) are folded and stored in the main wing storage groove (12) under the drive of the main wing folding mechanism (6).

4. The unmanned aerial vehicle with foldable and automatically unfoldable wings as claimed in claim 1, characterized in that: The lower rear end of the fuselage (1) is provided with an auxiliary wing storage slot (13); the left auxiliary wing (4) and the right auxiliary wing (5) are folded and stored in the auxiliary wing storage slot (13) under the drive of the auxiliary wing folding mechanism (7).

5. The unmanned aerial vehicle with foldable and automatically unfoldable wings as claimed in claim 2, characterized in that: Tail wing storage grooves (14) are provided on both sides of the rear portion of the fuselage (1), and the folded left tail wing (8) and right tail wing (9) are accommodated through the tail wing storage grooves (14).

6. A UAV with foldable and automatically unfoldable wings as claimed in claim 2 or 5, characterized in that: Limiting blocks (15) are provided beside the left tail folding structure (10) and the right tail folding structure (11), and the rebound positions of the left tail (8) and the right tail (9) are limited by the limiting blocks (15).

7. A UAV with foldable and automatically unfoldable wings as claimed in any one of claims 1 to 5, characterized in that: The left auxiliary wing (4) and the right auxiliary wing (5) are both provided with an adjusting wing plate (16), and the airflow angles of the left auxiliary wing (4) and the right auxiliary wing (5) are changed by changing the angle of the adjusting wing plate (16).

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