Folding wing unmanned aerial vehicle with wing surfaces capable of being reversely folded

Abstract

The utility model provides a folding wing unmanned aerial vehicle with wing surfaces capable of being reversely folded. Comprising a fuselage body, a rotating assembly fixed to one end of the fuselage body, a first wing, a second wing, a driving assembly and a telescopic rod, wherein the rotating assembly is sleeved with the first wing and the second wing, and the first wing and the second wing are overlapped with each other; the driving assembly is contained and fixed in the fuselage body; the telescopic rod is connected with the driving assembly and penetrates through the fuselage body; the driving assembly drives the telescopic rod to stretch out and draw back so as to adjust folding of the first wing and the second wing. Compared with the prior art, the folding wing unmanned aerial vehicle provided by the utility model has the advantages that the wings can be switched from an unfolded state to a folded state, and tasks can be more flexibly executed in an air area and a sea area.

Description

Technical Field

[0001] The utility model is applicable to the technical field of unmanned aerial vehicles, and in particular relates to a folding-wing unmanned aerial vehicle with a wing surface capable of reverse folding. Background Art

[0002] In recent years, due to the small size and light weight of cross-domain amphibious drones, they can freely switch their activity space between the air and the sea and are flexible to operate, so they are widely used to perform missions in amphibious areas.

[0003] In the existing technology, one of the key technologies of cross-domain amphibious UAVs is folding wings, which are required to have high wing surface strength, light weight, small load deformation and other characteristics, and require smooth movement, low friction and impact resistance during wing folding and deformation. The folding wings need to be able to fold in reverse, and the UAV needs to fold its wings after flying in the air and entering underwater. Currently, most folding wing technologies are for changing from a folded state to an unfolded state, while changing from an unfolded state to a folded state is rare. In addition, the folding wings of cross-domain amphibious UAVs require a limit locking mechanism, which not only needs to limit the rotation of the wings when unfolded, but also needs to limit the rotation of the wings after folding.

[0004] Therefore, there is an urgent need for a new folding-wing UAV with reversely foldable wings, which can unfold and fold the wings of the folding-wing UAV to adapt to performing tasks in different areas. Utility Model Content

[0005] The utility model provides a folding-wing UAV with a wing surface that can be folded back and forth. The overall structure is simple, and the wings of the folding-wing UAV can be switched from an unfolded state to a folded state, making it more flexible when performing tasks in air areas and sea areas.

[0006] In order to achieve the above-mentioned purpose, the utility model provides a folding-wing UAV with a wing surface that can be folded back and forth, the folding-wing UAV comprises a fuselage body, a rotating assembly fixed to one end of the fuselage body, a first wing and a second wing sleeved on the rotating assembly and stacked on each other, a driving assembly accommodated and fixed in the fuselage body, and a telescopic rod connected to the driving assembly and passing through the fuselage body; the driving assembly drives the telescopic rod to extend and retract to adjust the folding of the first wing and the second wing;

[0007] The rotating assembly includes a rotating shaft fixed to the fuselage body and perpendicular to the axial direction of the fuselage body;

[0008] The first wing comprises a first wing body, a first through hole penetrating the first wing body, a first metal piece in a circular ring shape and bonded and fixed to the hole wall of the first through hole, and a first stop buckle fixed to one end of the first wing body close to the rotating assembly, the rotating shaft passes through the first through hole and forms a rotational connection between the first wing and the rotating shaft;

[0009] The second wing comprises a second wing body, a second through hole penetrating the second wing body, a second metal piece in a circular ring shape and bonded and fixed to the hole wall of the second through hole, and a second stop buckle fixed to one end of the second wing body close to the rotating assembly, the rotating shaft passes through the second through hole and forms a rotational connection between the second wing and the rotating shaft;

[0010] The first metal component comprises a first metal component body, a first receiving space formed through the first metal component body, and a first groove formed by the first metal component body being recessed along the axial direction of the rotating shaft in a direction away from the second wing, wherein the first groove is in communication with the first receiving space;

[0011] The second metal member comprises a second metal member body, a second receiving space formed through the second metal member body, and a second groove formed by the second metal member body being recessed along the axial direction of the rotating shaft in a direction away from the first wing, wherein the second groove is in communication with the second receiving space;

[0012] The first receiving space and the second receiving space are connected to each other. A torsion spring is provided in the first receiving space and the second receiving space. One end of the torsion spring is arranged in the first groove, and the other end of the torsion spring is arranged in the second groove. The torsion spring is used to provide torsion for folding the first wing and the second wing.

[0013] Preferably, the driving assembly includes a telescopic rod guide block, a connecting rod, a rocker arm and a steering gear, the telescopic rod guide block is fixed in the fuselage body and is provided with a groove, the telescopic rod is inserted in the groove of the telescopic rod guide block, one end of the connecting rod is fixedly connected to the telescopic rod, the other end of the connecting rod is fixedly connected to one end of the rocker arm, the other end of the rocker arm is fixedly connected to the steering gear, and the steering gear drives the rocker arm to rotate to drive the telescopic rod to perform telescopic movement along the groove of the telescopic rod guide block.

[0014] Preferably, the first metal component and the second metal component are both made of aluminum alloy.

[0015] Preferably, the rotating assembly further comprises a bearing, wherein the bearing is sleeved on the rotating shaft and abuts against a side of the second metal component away from the fuselage body.

[0016] Preferably, the rotating assembly further comprises a clamping plate, and the clamping plate is fixed to a side of the bearing away from the fuselage body.

[0017] Preferably, a first limiting groove is provided at one end of the first wing body away from the first through hole, and a second limiting groove is provided at one end of the second wing body away from the second through hole;

[0018] The folding-wing UAV also includes a limiting column, which is fixed to one end of the fuselage body away from the rotating assembly. When the first wing and the second wing are in a folded state, the limiting column abuts against the first wing and the second wing respectively, and is respectively engaged in the first limiting groove and the second limiting groove.

[0019] Preferably, soft rubber is provided in both the first limiting groove and the second limiting groove.

[0020] Compared with the prior art, the folding-wing UAV with wing surfaces that can be folded in reverse provided by the utility model drives the rocker arm to rotate through the servo to drive the telescopic rod to perform telescopic movement. When the first wing and the second wing are unfolded, the torsion spring is in a compressed state to provide torque for the first wing and the second wing. Since the telescopic rod rises to the maximum position and abuts against the first limit buckle and the second limit buckle, the torsion generated by the torsion spring is offset, and the wings of the folding-wing UAV are maintained in the unfolded state. When the first wing and the second wing are folded, the telescopic rod descends and no longer abuts against the first limit buckle and the second limit buckle. The first wing and the second wing are affected by the torsion of the torsion spring, so that the first wing and the second wing are folded. The folding-wing UAV with wing surfaces that can be folded in reverse provided by the utility model has a simple overall structure, and the wings can be switched from an unfolded state to a folded state, which is more flexible when performing tasks in air areas and sea areas. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The utility model is described in detail below in conjunction with the accompanying drawings. The above and other aspects of the utility model will become clearer and easier to understand through the detailed description made in conjunction with the following drawings. In the accompanying drawings:

[0022] Figure 1 It is a structural schematic diagram of a folding-wing UAV provided by an embodiment of the utility model, in which the wing surface in the unfolded state can be folded back;

[0023] Figure 2 is along Figure 1 Sectional view along line AA;

[0024] Figure 3 This is a schematic diagram of the partial structure of the first wing of a folding-wing UAV with a wing surface that can be folded back in reverse provided by an embodiment of the utility model;

[0025] Figure 4This is a schematic diagram of the partial structure of the second wing of a folding-wing drone with a reversely foldable wing surface provided by an embodiment of the utility model;

[0026] Figure 5 It is a structural schematic diagram of a folding-wing UAV provided by an embodiment of the utility model, in which the wing surface of the wing is foldable in a reverse direction in a folded state;

[0027] Figure 6 is along Figure 5 Cross-sectional view along line BB.

[0028] In the figure, 100, a folding-wing UAV, 1, a fuselage body, 2, a rotating assembly, 21, a rotating shaft, 22, a bearing, 23, a clamping plate, 3, a driving assembly, 31, a telescopic rod guide block, 32, a connecting rod, 33, a rocker arm, 34, a servo, 4, a first wing, 41, a first wing body, 42, a first limiting buckle, 43, a first through hole, 44, a first limiting groove, 5, a second wing, 51, a second wing body, 52, a second limiting buckle, 53, a second through hole, 54, a second limiting groove, 6, a first metal part, 61, a first metal part body, 62, a first receiving space, 63, a first groove, 7, a second metal part, 71, a second metal part body, 72, a second receiving space, 73, a second groove, 8, a torsion spring, 9, a telescopic rod, 10, a limiting column. DETAILED DESCRIPTION

[0029] In order to make the purpose, technical solution and advantages of the utility model more clear, the utility model is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the utility model and are not used to limit the utility model.

[0030] It should be noted that, in this article, the terms "include", "comprises" or any other variations thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, an element defined by the sentence "comprises a ..." does not exclude the existence of other identical elements in the process, method, article or device including the element.

[0031] Please refer to Figure 1-Figure 6The utility model provides a folding-wing UAV 100 with a wing surface that can be folded reversely. The folding-wing UAV 100 includes a fuselage body 1, a rotating assembly 2 fixed to one end of the fuselage body 1, a first wing 4 and a second wing 5 sleeved on the rotating assembly 2 and stacked on each other, a driving assembly 3 accommodated and fixed in the fuselage body 1, and a telescopic rod 9 connected to the driving assembly 3 and passing through the fuselage body 1; the driving assembly 3 drives the telescopic rod 9 to extend and retract to adjust the folding of the first wing 4 and the second wing 5.

[0032] The rotating assembly 2 includes a rotating shaft 21 fixed to the fuselage body 1 and perpendicular to the axial direction of the fuselage body 1 .

[0033] The first wing 4 includes a first wing body 41, a first through hole 43 penetrating the first wing body 41, a first metal part 6 in a circular ring shape bonded and fixed to the hole wall of the first through hole 43, and a first limiting buckle 42 fixed to one end of the first wing body 41 close to the rotating component 2. The rotating shaft 21 passes through the first through hole 43 and forms a rotational connection between the first wing 4 and the rotating shaft 21.

[0034] The second wing 5 includes a second wing 5 body, a second through hole 53 penetrating the second wing body 51, a second metal part 7 in a circular ring shape bonded and fixed to the hole wall of the second through hole 53, and a second limiting buckle 52 fixed to one end of the second wing body 51 close to the rotating component 2. The rotating shaft 21 passes through the second through hole 53 and forms a rotational connection between the second wing 5 and the rotating shaft 21.

[0035] The first metal member 6 includes a first metal member body 61, a first receiving space 62 formed through the first metal member body 61, and a first groove 63 formed by the first metal member body 61 being recessed along the axial direction of the rotating shaft 21 in a direction away from the second wing 5, and the first groove 63 is connected to the first receiving space 62;

[0036] The second metal member 7 includes a second metal member body 71, a second receiving space 72 formed through the second metal member body 71, and a second groove 73 formed by the second metal member body 71 being recessed along the axial direction of the rotating shaft 21 away from the first wing 4, and the second groove 73 is connected to the second receiving space 72;

[0037] The first receiving space 62 and the second receiving space 72 are connected to each other. A torsion spring 8 is provided in the first receiving space 62 and the second receiving space 72. One end of the torsion spring 8 is arranged in the first groove 63, and the other end of the torsion spring 8 is arranged in the second groove 73. The torsion spring 8 is used to provide torsion for the folding of the first wing 4 and the second wing 5.

[0038] Specifically, the driving assembly 3 drives the telescopic rod 9 to gradually move upward to reach the highest point, and the first limiting buckle 42 and the second limiting buckle 52 abut against the telescopic rod 9. At this time, the torsion spring 8 is in a compressed state, and because the telescopic rod 9 restricts the first wing 4 and the second wing 5, the first wing 4 and the second wing 5 will not be folded due to the torsion of the torsion spring 8, so that the first wing 4 and the second wing 5 remain in the unfolded state.

[0039] When the first wing 4 and the second wing 5 are to be switched to a folded state, the driving assembly 3 moves the telescopic rod 9 downward, and the telescopic rod 9 is no longer in contact with the first limit buckle 42 and the second limit buckle 52. Due to the torsion of the torsion spring 8, the first wing 4 and the second wing 5 are prompted to rotate back, so that the first wing 4 and the second wing 5 are in a folded state, thereby realizing the switching of the folding-wing UAV 100 from the unfolded state to the folded state. If the folding-wing UAV 100 needs to be switched to the unfolded state in a subsequent process, the first wing 4 and the second wing 5 can be manually pushed to the unfolded state.

[0040] In this embodiment, the driving assembly 3 includes a telescopic rod guide block 31, a connecting rod 32, a rocker arm 33 and a steering gear 34. The telescopic rod guide block 31 is fixed in the fuselage body 1 and is provided with a groove. The telescopic rod 9 is inserted in the groove of the telescopic rod guide block 31. One end of the connecting rod 32 is fixedly connected to the telescopic rod 9, and the other end of the connecting rod 32 is fixedly connected to one end of the rocker arm 33. The other end of the rocker arm 33 is fixedly connected to the steering gear 34. The steering gear 34 drives the rocker arm 33 to rotate to drive the telescopic rod 9 to perform telescopic movement along the groove of the telescopic rod guide block 31 in an axial direction perpendicular to the fuselage body 1.

[0041] In this embodiment, the first metal member 6 and the second metal member 7 are both made of aluminum alloy, which effectively improves the reliability and overall strength of the folding-wing UAV 100 and improves the stability of the first wing 4 and the second wing 5 when rotating.

[0042] In this embodiment, the rotating assembly 2 further includes a bearing 22 . The bearing 22 is sleeved on the rotating shaft 21 and abuts against a side of the second metal component 7 away from the main body 1 .

[0043] In this embodiment, the rotating assembly 2 further includes a clamping plate 23 , which is fixed to a side of the bearing 22 away from the fuselage body 1 . The clamping plate 23 covers the rotating shaft 21 , so that the rotating assembly 2 has a more stable structure.

[0044] In this embodiment, a first limiting groove 44 is provided at one end of the first wing 4 body away from the first through hole 43, and a second limiting groove 54 is provided at one end of the second wing 5 body away from the second through hole 53;

[0045] The folding-wing UAV 100 also includes a limiting column 10, which is fixed to one end of the fuselage body 1 away from the rotating assembly 2. When the first wing 4 and the second wing 5 are in a folded state, the limiting column 10 abuts against the first wing 4 and the second wing 5 respectively, and is respectively engaged in the first limiting groove 44 and the second limiting groove 54.

[0046] In this embodiment, soft rubber is disposed in both the first limiting groove 44 and the second limiting groove 54 .

[0047] Specifically, when the first wing 4 and the second wing 5 are folded, affected by the torsion of the torsion spring 8, the first wing 4 and the second wing 5 rotate backward, and the first limiting groove 44 and the second limiting groove 54 collide with the limiting column 10. Due to the presence of the soft rubber, the impact force is effectively alleviated, and the limiting column 10 effectively prevents the first wing 4 and the second wing 5 from continuing to rotate due to the remaining torsion, so that the folding-wing UAV 100 with reversely foldable wing surfaces maintains a streamlined folding state as a whole, turning into an unmanned submarine that can freely navigate underwater.

[0048] Compared with the prior art, the folding-wing UAV with wing surfaces that can be folded in reverse provided by the utility model drives the rocker arm to rotate through the servo to drive the telescopic rod to perform telescopic movement. When the first wing and the second wing are unfolded, the torsion spring is in a compressed state to provide torque for the first wing and the second wing. Since the telescopic rod rises to the maximum position and abuts against the first limit buckle and the second limit buckle, the torsion generated by the torsion spring is offset, and the wings of the folding-wing UAV are maintained in the unfolded state. When the first wing and the second wing are folded, the telescopic rod descends and no longer abuts against the first limit buckle and the second limit buckle. The first wing and the second wing are affected by the torsion of the torsion spring, so that the first wing and the second wing are folded. The folding-wing UAV with wing surfaces that can be folded in reverse provided by the utility model has a simple overall structure, and the wings can be switched from an unfolded state to a folded state, which is more flexible when performing tasks in air areas and sea areas.

[0049] The embodiments of the present invention are described above in conjunction with the accompanying drawings. What is disclosed is only the preferred embodiments of the present invention. However, the present invention is not limited to the above-mentioned specific implementation methods. The above-mentioned specific implementation methods are merely illustrative and not restrictive. Under the enlightenment of the present invention, ordinary technicians in this field can also make many forms of equivalent changes without departing from the scope of protection of the purpose of the present invention and the claims, which are all within the protection of the present invention.

Claims

1. A folding-wing drone with wing surfaces that can be folded back, characterized in that: The folding-wing drone comprises a fuselage body, a rotating assembly fixed at one end of the fuselage body, a first wing and a second wing sleeved on the rotating assembly and stacked on each other, a driving assembly accommodated and fixed in the fuselage body, and a telescopic rod connected to the driving assembly and passing through the fuselage body; the driving assembly drives the telescopic rod to extend and retract to adjust the folding of the first wing and the second wing; The rotating assembly includes a rotating shaft fixed to the fuselage body and perpendicular to the axial direction of the fuselage body; The first wing includes a first wing body, a first through hole penetrating the first wing body, a first metal piece in an annular shape bonded and fixed to the hole wall of the first through hole, and a first stop buckle fixed to one end of the first wing body close to the rotating assembly, the rotating shaft passes through the first through hole and the first wing is rotatably connected to the rotating shaft; The second wing comprises a second wing body, a second through hole penetrating the second wing body, a second metal piece in a circular ring shape and bonded and fixed to the hole wall of the second through hole, and a second stop buckle fixed to one end of the second wing body close to the rotating assembly, the rotating shaft passes through the second through hole and forms a rotational connection between the second wing and the rotating shaft; The first metal component comprises a first metal component body, a first receiving space formed through the first metal component body, and a first groove formed by the first metal component body being recessed along the axial direction of the rotating shaft in a direction away from the second wing, wherein the first groove is in communication with the first receiving space; The second metal member comprises a second metal member body, a second receiving space formed through the second metal member body, and a second groove formed by the second metal member body being recessed along the axial direction of the rotating shaft in a direction away from the first wing, wherein the second groove is in communication with the second receiving space; The first receiving space and the second receiving space are connected to each other. A torsion spring is provided in the first receiving space and the second receiving space. One end of the torsion spring is arranged in the first groove, and the other end of the torsion spring is arranged in the second groove. The torsion spring is used to provide torsion for folding the first wing and the second wing.

2. The folding-wing drone with reversibly foldable wings as claimed in claim 1, characterized in that: The driving assembly includes a telescopic rod guide block, a connecting rod, a rocker arm and a steering gear. The telescopic rod guide block is fixed in the fuselage body and is provided with a groove. The telescopic rod is inserted in the groove of the telescopic rod guide block. One end of the connecting rod is fixedly connected to the telescopic rod, and the other end of the connecting rod is fixedly connected to one end of the rocker arm. The other end of the rocker arm is fixedly connected to the steering gear. The steering gear drives the rocker arm to rotate to drive the telescopic rod to perform telescopic movement along the groove of the telescopic rod guide block in an axial direction perpendicular to the fuselage body.

3. The folding-wing drone with reversibly foldable wings as claimed in claim 2, characterized in that: The first metal component and the second metal component are both made of aluminum alloy.

4. The folding-wing drone with reversibly foldable wings as claimed in claim 1, characterized in that: The rotating assembly further comprises a bearing, which is sleeved on the rotating shaft and abuts against a side of the second metal component away from the fuselage body.

5. The folding-wing drone with reversibly foldable wings as claimed in claim 4, characterized in that: The rotating assembly also includes a pressing plate, and the pressing plate is fixed to a side of the bearing away from the fuselage body.

6. The folding-wing drone with reversely foldable wings as claimed in claim 1, characterized in that: A first limiting groove is provided at one end of the first wing body away from the first through hole, and a second limiting groove is provided at one end of the second wing body away from the second through hole; The folding-wing drone with reversely foldable wing surface also includes a limiting column, which is fixed to one end of the fuselage body away from the rotating assembly. When the first wing and the second wing are in a folded state, the limiting column abuts against the first wing and the second wing respectively, and is respectively engaged in the first limiting groove and the second limiting groove.

7. The folding-wing UAV with reversibly foldable wings as claimed in claim 6, characterized in that: Soft rubber is arranged in the first limiting groove and the second limiting groove.

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