Wing folding mechanism and unmanned aerial vehicle

Abstract

The utility model belongs to the technical field of unmanned aerial vehicles and provides a wing folding mechanism and an unmanned aerial vehicle. The wing root of the first wing is connected with a first adapter; the wing root of the second wing is connected with a second adapter; the first adapter and the second adapter are rotationally connected and are used for folding the first wing and the second wing; the torsional spring is located between the first adapter and the second adapter, and the two ends of the torsional spring are installed in the first adapter and the second adapter respectively. When the fixed-wing unmanned aerial vehicle is used and the wings need to be folded, the first wing and the second wing are rotated inwards through the rotating shaft, so that the first wing and the second wing are mutually attached and folded to achieve the purpose of convenient transportation, the folded fixed-wing unmanned aerial vehicle can be loaded into a launching cylinder, and when the fixed-wing unmanned aerial vehicle is launched out of the cylinder, the unmanned aerial vehicle can be conveniently transported. The wings are automatically unfolded under the torque action of the torsional springs, and the aim of flexible and convenient launching is achieved.

Description

Technical Field

[0001] This utility model belongs to the field of unmanned aerial vehicle (UAV) technology, and specifically relates to a wing folding mechanism and an UAV. Background Technology

[0002] Fixed-wing drones are widely used in inspection, transportation, reconnaissance, and strike operations due to their advantages such as long endurance, high speed, and high reliability. However, traditional fixed-wing drones are difficult to transport due to their design and flight principles, and their takeoff and landing processes have excessively high requirements for the site. Therefore, it is necessary to develop an automatically deployable wing folding mechanism for fixed-wing drones, enabling them to fold quickly and take off from a launch tube, thus meeting the needs for convenient transportation and flexible takeoff.

[0003] For example, publication number CN221624001U discloses a wing folding mechanism for a fixed-wing unmanned aerial vehicle (UAV). The mechanism includes a first wing and a second wing. Several first and second grooves are provided on the sides of the first and second wing that are close to each other. A fixing block is provided in each of the first and second grooves, and a pressing pin is provided on each fixing block. A rotating groove is provided between the first and second grooves, and a steering device is provided in the rotating groove. A rotating circular hole is provided on one side of the steering device, and a rotating column is provided in the rotating circular hole.

[0004] Although the above technical solutions solve the problem of convenient transportation of fixed-wing UAVs, the solutions still have the following drawbacks:

[0005] The folding mechanism of the above solution cannot automatically unfold the wings of the fixed-wing UAV, and the take-off method of the fixed-wing is still the traditional runway take-off, which has relatively strict requirements for the site during take-off. Utility Model Content

[0006] To address the problems in the background art, this utility model proposes a wing folding mechanism and a drone.

[0007] To achieve the above objectives, the present invention adopts the following technical solution:

[0008] A wing folding mechanism includes: a first wing, a second wing, and a torsion spring;

[0009] A first adapter is connected at the root of the first wing;

[0010] A second adapter is connected at the root of the second wing;

[0011] The first adapter and the second adapter are rotatably connected for folding the first wing and the second wing;

[0012] The torsion spring is located between the first adapter and the second adapter, and its two ends are respectively installed in the first adapter and the second adapter.

[0013] Preferably, the first adapter has a first rotating groove on its surface facing the second adapter, and the first rotating groove is used to install the end of the torsion spring away from the second rotating component;

[0014] The surface of the first adapter is provided with a first rotating circular hole and a first positioning hole located on one side of the first rotating circular hole;

[0015] The first rotating circular hole is located at the rotation center of the first adapter and inside the first rotating groove.

[0016] Preferably, the second adapter has a second rotating groove on its surface facing the first adapter, and the second rotating groove is used to install the end of the torsion spring away from the first adapter;

[0017] The second adapter has a second rotating circular hole on its surface and a second positioning hole located on one side of the second rotating circular hole;

[0018] The second rotating circular hole is located at the rotation center of the second adapter and inside the second rotating groove.

[0019] Preferably, the first adapter and the second adapter are rotatably connected by a rotating shaft; the rotating shaft is assembled in the first rotating hole and the second rotating hole, and is located inside the torsion spring.

[0020] Preferably, the end of the rotating shaft is further provided with a plurality of first bolt holes, the first bolt holes being used to connect and fasten washers by bolts, the fastening washers being installed on the surface of the first adapter that is away from the second adapter;

[0021] One end of the rotating shaft is provided with a stepped surface, and a plurality of second bolt holes are provided on the stepped surface. The second bolt holes are used to connect to the drone fuselage by bolts.

[0022] Preferably, both the first bolt hole and the second bolt hole are countersunk holes.

[0023] Preferably, the surface of the first adapter away from the second adapter has a countersunk groove, which is used to install the fastening gasket.

[0024] Preferably, it also includes a spring pin;

[0025] The spring pin is assembled in the first positioning hole and the second positioning hole to restrict the relative rotation of the first adapter and the second adapter.

[0026] Preferably, after the first wing and the second wing are deployed, the first positioning hole is aligned with the second positioning hole.

[0027] A drone equipped with the aforementioned wing folding mechanism.

[0028] The beneficial effects of this utility model are:

[0029] 1. When this utility model is used, if the wings need to be folded, the first wing and the second wing are rotated inward by the pivot axis, so that the first wing and the second wing fit together and fold, so as to facilitate transportation. The folded fixed-wing UAV can be put into the launch tube. When the fixed-wing UAV is ejected from the tube, the wings are automatically unfolded by the torque of the torsion spring, so as to achieve the purpose of flexible and convenient launch.

[0030] 2. By incorporating a spring pin, this utility model can limit the relative rotation of the first and second wings after the wings have automatically deployed under the torque of the torsion spring.

[0031] Other features and advantages of this invention will be set forth in the description which follows, and will be apparent in part from the description, or may be learned by practicing the invention. The objectives and other advantages of this invention can be realized and obtained through the structures pointed out in the description and the accompanying drawings. Attached Figure Description

[0032] 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 some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0033] Figure 1 An exploded view of the wing folding mechanism of this utility model is shown;

[0034] Figure 2 A front view of the wing folding mechanism of this utility model is shown;

[0035] Figure 3 A schematic diagram of the structure of the first adapter of this utility model is shown;

[0036] Figure 4 A schematic diagram of the structure of the second adapter of this utility model is shown;

[0037] Figure 5 A schematic diagram of the rotating shaft of this utility model is shown.

[0038] In the diagram: 1. First wing; 2. Second wing; 3. First adapter; 301. First rotating groove; 302. First rotating hole; 303. First positioning hole; 4. Second adapter; 401. Second rotating groove; 402. Second rotating hole; 403. Second positioning hole; 5. Fastening washer; 6. Torsion spring; 7. Shaft; 701. First bolt hole; 702. Second bolt hole; 8. Spring pin. Detailed Implementation

[0039] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of this utility model.

[0040] A wing folding mechanism, such as Figure 1 As shown, the aircraft includes a first wing 1, a second wing 2, a first adapter 3, a second adapter 4, a fastening washer 5, a torsion spring 6, a pivot 7, and a spring pin 8. The first adapter 3 is fixedly connected to the root of the first wing 1, and the second adapter 4 is fixedly connected to the root of the second wing 2. The first adapter 3 and the second adapter 4 are rotatably connected via the pivot 7. During folding, the first wing 1 and the second wing 2 rotate around the pivot 7, causing most of the area of ​​the first wing 1 and the second wing 2 to overlap, thus enabling folding.

[0041] It should be noted that the torsion spring 6, which is the part that mates with the rotating shaft 7, may suffer fatigue damage during rotation. Therefore, it can be replaced to reduce maintenance costs.

[0042] Furthermore, the torsion spring 6 is located between the first adapter 3 and the second adapter 4, with its two ends respectively installed in the first adapter 3 and the second adapter 4. Specifically, the torsion spring 6 is located outside the rotating shaft 7 and is coaxially arranged with the rotating shaft 7. When the first adapter 3 and the second adapter 4 rotate relative to each other, the torsion spring 6 will contract or rebound in the direction of their rotation. For example, when it is necessary to fold the first wing 1 and the second wing 2, the torsion spring 6 will gradually contract as they rotate; and when it is necessary to unfold the first wing 1 and the second wing 2, the torsion spring 6 will gradually unfold as they rotate.

[0043] Combination Figure 1 and Figure 2 It is known that the fastening gasket 5 is installed on the surface of the first wing 1, and it can be connected to the pivot 7 that passes through the first wing 1 and the second wing 2 to prevent the first wing 1 and the second wing 2 from separating.

[0044] like Figure 3 As shown, the surface of the first adapter 3 facing the second adapter 4 has a first rotating groove 301, which is adapted to the end of the torsion spring 6 and can fix the end of the torsion spring 6 away from the second adapter 4. In addition, the surface of the first adapter 3 has a first rotating circular hole 302 and a first positioning hole 303 located on one side of the first rotating circular hole 302; the first rotating circular hole 302 is located at the rotation center of the first adapter 3 and is located inside the first rotating groove 301.

[0045] like Figure 4 As shown, the second adapter 4 has a second rotating groove 401 on its surface facing the first adapter 3. The second rotating groove 401 is used to install the end of the torsion spring 6 away from the first adapter 3. The second adapter 4 has a second rotating circular hole 402 on its surface and a second positioning hole 403 located on one side of the second rotating circular hole 402. The second rotating circular hole 402 is located at the rotation center of the second adapter 4 and is located inside the first rotating groove 301.

[0046] Combination Figure 1 , Figure 3 and Figure 4 It can be seen that the rotating shaft 7 is assembled in the first rotating circular hole 302 and the second rotating circular hole 402, and the spring pin 8 is assembled in the first positioning hole 303 and the second positioning hole 403 to restrict the relative rotation of the first adapter 3 and the second adapter 4. After the first wing 1 and the second wing 2 are deployed, the first positioning hole 303 and the second positioning hole 403 are aligned. Specifically, the spring pin 8 can be fixed in the first positioning hole 303 or the second positioning hole 403 during installation. For example, the head of the spring pin 8 can be fixed in the first positioning hole 303, and the tail end can face the second positioning hole 403. When it is necessary to fold the first wing 1 and the second wing 2, the tail end of the spring pin 8 can be pushed back into the first positioning hole 303. Then, the first adapter 3 and the second adapter 4 can be rotated (the first wing 1 and the second wing 2 rotate accordingly) to make the first positioning hole 303 and the second positioning hole 403 misaligned. Finally, when unfolded, the first wing 1 and the second wing 2 spring back to their original positions under the action of the torsion spring 6. After that, the first positioning hole 303 and the second positioning hole 403 are aligned, and the tail end of the spring pin 8 returns to its original position and enters the second positioning hole 403 under the action of the spring force, thereby restricting the relative rotation of the first adapter 3 and the second adapter 4.

[0047] Combination Figure 1 and Figure 5 It can be seen that the end of the rotating shaft 7 is also provided with several first bolt holes 701, which are used to connect and fasten the washer 5 by bolts. The fastening washer 5 is installed on the surface of the first adapter 3 away from the second adapter 4; one end of the rotating shaft 7 is provided with a stepped surface, and several second bolt holes 702 are provided on the stepped surface. The second bolt holes 702 are used to connect to the fuselage of the UAV by bolts.。

[0048] It should be noted that in some alternative embodiments, both the first bolt hole 701 and the second bolt hole 702 can be countersunk holes. A countersunk groove can be provided on the surface of the first adapter 3 away from the second adapter 4, which is used to install the fastening washer 5.

[0049] For example, Figure 1 The wing folding mechanism can be installed in a fixed-wing UAV, and the assembly and operation process of the wing folding mechanism in a fixed-wing UAV is as follows:

[0050] During assembly, according to Figure 1 The first adapter 3, the second adapter 4, the torsion spring 6, and the rotating shaft 7 are connected in a certain way. Then, a fastening washer 5 is installed on the top of the first adapter 3 and fixed to the rotating shaft 7 with bolts, thereby completing the assembly of the entire wing mechanism.

[0051] In use, when it is necessary to fold the first wing 1 and the second wing 2, push the spring pin 8 back to the first positioning hole 303 or the second positioning hole 403, and rotate the first wing 1 and the second wing 2 inward through the pivot 7, so that the first wing 1 and the second wing 2 are folded together (at this time, the first positioning hole 303 and the second positioning hole 403 are misaligned), which facilitates the transportation of the fixed-wing UAV. The folded fixed-wing UAV can be put into the launch tube. When the fixed-wing UAV is ejected from the tube, the wings automatically unfold under the torque of the torsion spring 6. At the same time, the spring pin 8 rebounds and falls into the first positioning hole 303 and the second positioning hole 403 to prevent the wings from rebounding. The fixed-wing UAV can take off in a more convenient way.

[0052] Although the present invention 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; and these 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 the present invention.

Claims

1. A wing folding mechanism, characterized in that, include: First wing (1), second wing (2), torsion spring (6); The first wing (1) is connected to the root of the first adapter (3); The second wing (2) is connected to a second adapter (4) at its root; The first adapter (3) and the second adapter (4) are rotatably connected for folding the first wing (1) and the second wing (2); The torsion spring (6) is located between the first adapter (3) and the second adapter (4), and its two ends are respectively installed in the first adapter (3) and the second adapter (4).

2. The wing folding mechanism according to claim 1, characterized in that: The first adapter (3) has a first rotating groove (301) on its surface facing the second adapter (4). The first rotating groove (301) is used to install the end of the torsion spring (6) away from the second adapter (4). The surface of the first adapter (3) is provided with a first rotating circular hole (302) and a first positioning hole (303) located on one side of the first rotating circular hole (302); The first rotating circular hole (302) is located at the rotation center of the first adapter (3) and inside the first rotating groove (301).

3. The wing folding mechanism according to claim 2, characterized in that: The second adapter (4) has a second rotating groove (401) on its surface facing the first adapter (3). The second rotating groove (401) is used to install the end of the torsion spring (6) away from the first adapter (3). The second adapter (4) has a second rotating circular hole (402) on its surface and a second positioning hole (403) located on one side of the second rotating circular hole (402); The second rotating circular hole (402) is located at the rotation center of the second adapter (4) and inside the second rotating groove (401).

4. The wing folding mechanism according to claim 3, characterized in that: The first adapter (3) and the second adapter (4) are rotatably connected by a rotating shaft (7); the rotating shaft (7) is assembled in the first rotating hole (302) and the second rotating hole (402) and is located inside the torsion spring (6).

5. A wing folding mechanism according to claim 4, characterized in that: The end of the rotating shaft (7) is also provided with a plurality of first bolt holes (701), the first bolt holes (701) are used to connect and fasten the washer (5) by bolts, and the fastening washer (5) is installed on the surface of the first adapter (3) away from the second adapter (4); One end of the rotating shaft (7) is provided with a stepped surface, and a plurality of second bolt holes (702) are provided on the stepped surface. The second bolt holes (702) are used to connect to the fuselage of the UAV by bolts. 。 6. A wing folding mechanism according to claim 5, characterized in that: Both the first bolt hole (701) and the second bolt hole (702) are countersunk holes.

7. A wing folding mechanism according to claim 5, characterized in that, The first adapter (3) has a countersunk groove on its surface away from the second adapter (4), and the countersunk groove is used to install the fastening gasket (5).

8. A wing folding mechanism according to claim 3, characterized in that: It also includes spring pins (8); The spring pin (8) is assembled in the first positioning hole (303) and the second positioning hole (403) to restrict the relative rotation of the first adapter (3) and the second adapter (4).

9. A wing folding mechanism according to claim 8, characterized in that, After the first wing (1) and the second wing (2) are deployed, the first positioning hole (303) is aligned with the second positioning hole (403).

10. A drone, characterized in that, The aircraft is equipped with a wing folding mechanism as described in any one of claims 1-9.

Images