Unmanned aerial vehicle wing folding device

Abstract

The utility model discloses an unmanned aerial vehicle wing folding device which comprises a main wing, an auxiliary wing and a folding mechanism connected between the main wing and the auxiliary wing, and the folding mechanism comprises a rotating assembly connected between the main wing and the auxiliary wing and a buffering assembly connected between the main wing and the auxiliary wing; compared with the prior art, the unmanned aerial vehicle has the beneficial effects that the buffer structure is arranged between the main wing and the auxiliary wing, and when the auxiliary wing is unfolded, the driving mechanism can drive the spring plate to be inserted into the connecting groove of the auxiliary wing, so that in the flight process of the unmanned aerial vehicle, when the auxiliary wing generates small-amplitude swing under the action of wind power, the auxiliary wing is unfolded. And the spring plate can generate elastic deformation, so that the wind resistance load is effectively absorbed and dispersed, and the wing connecting structure is protected from being influenced by excessive stress.

Description

Technical Field

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

[0002] In the field of drone design, the folding and unfolding mechanism of the wing is one of the key technologies for improving the portability and storage efficiency of drones. Existing drone wing folding devices are generally completely fixed after unfolding. For example, the drone wing folding structure disclosed in Chinese Utility Model Patent Application No. 201920215171.4 involves installing the drone wing onto the drone, rotating the auxiliary wing downwards by rotating the axial direction, making the fixing through holes on the main wing and the auxiliary wing parallel to each other. By pushing the connecting push block, the positioning link installed in the fixing through hole passes through the fixing through hole and enters the auxiliary wing. It is fixed by the connection between the fixing block at the front end and the mounting slot on the connecting fixing seat inside the auxiliary wing.

[0003] With the existing technology, drones need to withstand huge aerodynamic loads during flight. Although the traditional fully fixed method can ensure the stability of the wings during flight, it lacks the necessary buffering mechanism, making the connecting structure prone to damage under continuous high stress.

[0004] In view of this, the purpose of this utility model is to propose a wing folding device for unmanned aerial vehicles (UAVs) to solve the above problems. Utility Model Content

[0005] The purpose of this invention is to address the shortcomings of existing technologies by providing a drone wing folding device to solve the problems in the background art.

[0006] This utility model provides the following technical solution: a drone wing folding device, including a main wing, a secondary wing, and a folding mechanism connected between the main wing and the secondary wing, wherein the folding mechanism includes a rotating component connected between the main wing and the secondary wing and a buffer component connected between the main wing and the secondary wing;

[0007] The rotating assembly includes a fixed base, a rotating base, and a rotating shaft. The fixed base and the rotating base are fixedly connected to the main wing and the aileron, respectively. The rotating shaft is fixedly connected to the fixed base and rotatably connected to the aileron.

[0008] The buffer assembly includes an elastic component, which is connected between the bottom of the main wing and the connecting end of the aileron. Specifically, the elastic component is configured to undergo elastic deformation when one end of the aileron rotates around the rotation axis.

[0009] Preferably, the elastic component comprises a spring plate, the auxiliary wing is provided with a connecting groove near one end of the main wing, and the main wing is provided with a driving mechanism for driving the spring plate to be inserted into the connecting groove.

[0010] Preferably, the driving mechanism is an electric telescopic rod structure.

[0011] Preferably, the upper and lower surfaces of the spring plate are both provided with pulleys.

[0012] Preferably, the elastic component comprises a spring, one end of the spring is fixed to the main wing, and the other end of the spring is detachably fixed to the auxiliary wing.

[0013] Preferably, the connecting end of the spring and the auxiliary wing is fixed with a connecting lug, the auxiliary wing is fixed with a connecting seat, and the connecting lug and the connecting seat are fixed through a pin shaft.

[0014] Preferably, the pin shaft is an electric bolt.

[0015] Compared with the prior art, the utility model has the beneficial effects that: the utility model sets up the buffer structure between the main wing and the auxiliary wing, when the auxiliary wing is unfolded, the driving mechanism can drive the spring plate to be inserted into the connecting groove of the auxiliary wing, when the auxiliary wing is subjected to the wind force and produces small amplitude swing in the unmanned aerial vehicle flight process, the spring plate can be elastically deformed, thereby effectively absorbing and dispersing the wind resistance load, and protecting the wing connecting structure from excessive stress. BRIEF DESCRIPTION OF DRAWINGS

[0016] Figure 1 It is a structural schematic view of the utility model embodiment one.

[0017] Figure 2 It is a three-dimensional structural schematic view of the utility model.

[0018] Figure 3 It is a structural schematic view of the utility model embodiment two.

[0019] Figure 4 It is a three-dimensional structural schematic view of the utility model Figure 3 It is an enlarged structural schematic view of A in the utility model.

[0020] Figure 5 It is a connecting lug and connecting seat connecting structure schematic view of the utility model.

[0021] In the drawing: 1, main wing; 2, auxiliary wing; 3, rotating assembly; 31, fixed seat; 32, rotating seat; 33, rotating shaft; 41, elastic component; 41a, spring plate; 42a, driving mechanism; 43a, pulley; 41b, spring; 42b, connecting lug; 43b, connecting seat; 44b, pin shaft. DETAILED DESCRIPTION

[0022] The technical solutions in the embodiments of the utility model will be apparently and completely described in connection with the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all the other embodiments obtained by the ordinary skilled in the art without creative labor belong to the scope of protection of the utility model.

[0023] Please refer to Figures 1-5 .

[0024] Embodiment one

[0025] The unmanned aerial vehicle wing folding device, comprising a main wing 1, a sub-wing 2 and a folding mechanism connected between the main wing 1 and the sub-wing 2, the folding mechanism comprising a rotating assembly 3 connected between the main wing 1 and the sub-wing 2 and a buffer assembly 4 connected between the main wing 1 and the sub-wing 2, through the setting of the rotating assembly 3, the sub-wing 2 can be folded together with the main wing 1, reducing the occupied space of the wing, facilitating the storage of the unmanned aerial vehicle, through the setting of the buffer assembly 4, the buffer between the sub-wing 2 and the main wing 1 can be carried out, and the connecting structure between the main wing 1 and the sub-wing 2 is protected.

[0026] In the embodiment, the rotating assembly 3 comprises a fixed seat 31, a rotating seat 32 and a rotating shaft 33, the fixed seat 31 and the rotating seat 32 are fixedly connected with the main wing 1 and the sub-wing 2 respectively, the rotating shaft 33 is fixedly connected with the fixed seat 31, and the rotating shaft 33 is rotatably connected with the sub-wing 2, through the rotatable connection between the sub-wing 2 and the rotating shaft 33, the main wing 1 and the sub-wing 2 can be folded when the unmanned aerial vehicle is not used.

[0027] Specifically, the buffer assembly 4 comprises a elastic assembly 41, the elastic assembly 41 is connected between the bottom of the connecting end of the main wing 1 and the sub-wing 2, and the elastic assembly 41 is specifically set as: when one end of the sub-wing 2 rotates around the rotating shaft 33, the elastic assembly 41 elastically deforms.

[0028] Through the setting of the elastic assembly 41, when the unmanned aerial vehicle flies, the sub-wing 2 can swing up and down with a small amplitude relative to the main wing 1 under the action of wind force, when the sub-wing 2 swings up and down, the elastic assembly 41 elastically deforms, and the buffering effect is achieved.

[0029] Please refer to Figure 1In this embodiment, the elastic component 41 is a spring plate 41a. The end of the auxiliary wing 2 near the main wing 1 is provided with a connecting groove 21. The main wing 1 is equipped with a driving mechanism 42a for driving the spring plate 41a to be inserted into the connecting groove 21. After the auxiliary wing 2 and the main wing 1 are unfolded, the driving mechanism 42a drives the spring plate 41a to be inserted into the connecting groove 21. In this way, when the auxiliary wing 2 and the main wing 1 rotate slightly under the action of wind, the spring plate 41a can be bent. When the spring plate 41a bends, it plays a buffering role. Conversely, when the drone is not in use, the driving mechanism 42a can drive the spring plate 41a to be pulled out from the inside of the connecting groove 21. The wings can be folded by rotating the auxiliary wing 2 and the main wing 1 upwards.

[0030] The drive mechanism 42a can be an electric telescopic rod structure, which facilitates the insertion of the drive spring plate 41a into the connecting groove 21 or the removal of the drive spring plate 41a from the connecting groove 21.

[0031] In order to reduce the friction between the spring plate 41a and the inner wall of the connecting groove 21, pulleys 43a are installed on both the upper and lower surfaces of the spring plate 41a.

[0032] Example 2

[0033] Example 2 has a structure that is largely the same as Example 1, except that:

[0034] Please see Figure 4 In this embodiment, the elastic component 41 includes a spring 41b. One end of the spring 41b is fixed to the main wing 1, and the other end of the spring 41b is detachably fixed to the auxiliary wing 2. After the auxiliary wing 2 and the main wing 1 are deployed, the spring 41b connects the bottom of the auxiliary wing 2 and the main wing 1. When the drone is flying, under the action of wind, the upper end of the auxiliary wing 2 and the main wing 1 swing slightly, causing the spring 41b to extend and retract, thus playing a buffering role.

[0035] Specifically, a connecting lug 42b is welded and fixed to the connection end of the spring 41b and the aileron 2. The aileron 2 is fixed with a connecting seat 43b. The connecting seat 43b is provided with a slot for the connecting lug 42b to be inserted. When the aileron 2 is deployed, the connecting lug 42b is inserted into the slot. The connecting lug 42b and the connecting seat 43b are fixed together by a pin 44b.

[0036] Pin 44b is an electric latch; please refer to [link / reference]. Figure 5 The electric latch includes a pin and an electric telescopic cylinder 45b. The electric telescopic cylinder 45b is fixed to the connecting seat 43b by a bracket. The electric telescopic cylinder 45b drives the pin to move. After the connecting ear 42b is inserted into the slot of the connecting seat 43b, the electric telescopic cylinder 45b drives the pin to insert into the connecting ear 42b, thereby fixing the connecting ear 42b.

[0037] While the embodiments of the present application have been illustrated and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the spirit and scope of the application, which is defined by the appended claims and their equivalents.

Claims

1. A drone wing folding apparatus, characterized by: The utility model provides a folding wing aircraft, including main wing (1), auxiliary wing (2) and the folding mechanism that is connected between main wing (1) and auxiliary wing (2), the folding mechanism includes rotating assembly (3) that is connected between main wing (1) and auxiliary wing (2) and buffer assembly that is connected between main wing (1) and auxiliary wing (2), Rotating assembly (3) includes fixed seat (31), rotating seat (32) and rotating shaft (33), fixed seat (31), rotating seat (32) are fixedly connected with main wing (1) and auxiliary wing (2) respectively, rotating shaft (33) is fixedly connected with fixed seat (31), and rotating shaft (33) is rotatably connected with auxiliary wing (2), Buffer assembly includes elastic component (41), elastic component (41) is connected between the bottom of main wing (1) and auxiliary wing (2) connecting end, and elastic component (41) is specifically set as: when one end of auxiliary wing (2) rotates around rotating shaft (33), elastic component (41) occurs elastic deformation.

2. The wing folding device of claim 1, wherein: Elastic component (41) includes spring plate (41a), one end of auxiliary wing (2) near main wing (1) is equipped with connecting groove (21), and main wing (1) is equipped with drive mechanism (42a) for driving spring plate (41a) to insert into connecting groove (21).

3. The wing folding device of claim 2, wherein: Drive mechanism (42a) is electric telescopic rod structure.

4. The wing folding device of claim 3, wherein: The upper and lower surfaces of spring plate (41a) are equipped with pulley (43a).

5. The wing folding device of claim 1, wherein: Elastic component (41) includes spring (41b), one end of spring (41b) is fixed with main wing (1), and the other end of spring (41b) is detachably fixed with auxiliary wing (2).

6. The wing folding device of claim 5, wherein: The connecting end of spring (41b) and auxiliary wing (2) is fixed with connecting lug (42b), auxiliary wing (2) is fixed with connecting seat (43b), and connecting lug (42b) and connecting seat (43b) are fixed through pin shaft (44b).

7. The wing folding device of claim 6, wherein: Pin shaft (44b) is electric bolt.

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