1. The utility model provides an unmanned aerial vehicle wing quick assembly disassembly mechanism, its characterized in that, unmanned aerial vehicle wing quick assembly disassembly mechanism includes:

the base (10), the said base (10) is fixed on fuselage of unmanned aerial vehicle;

the trapezoidal lead screw (20), the said trapezoidal lead screw (20) is set up on the said base (10) rotatably;

the lead screw sleeve (30) is in threaded fit connection with the trapezoidal lead screw (20), and the trapezoidal lead screw (20) can drive the lead screw sleeve (30) to move along a first direction in a rotating mode;

a first connecting rod (40) and a second connecting rod (50), wherein one end of the first connecting rod (40) is rotatably arranged on one side of the screw rod sleeve (30), and one end of the second connecting rod (50) is rotatably arranged on the other side of the screw rod sleeve (30);

a first slider assembly (60) and a second slider assembly (70), wherein the first slider assembly (60) and the second slider assembly (70) are movably arranged on the base (10), the first slider assembly (60) is rotatably connected with the other end of the first connecting rod (40), the first connecting rod (40) can drive the first slider assembly (60) to move along a second direction, the second slider assembly (70) is rotatably connected with the other end of the second connecting rod (50), and the second connecting rod (50) can drive the second slider assembly (70) to move along a second direction, and the second direction is perpendicular to the first direction;

a first locking lever set (80) and a second locking lever set (90), the first locking lever set (80) being fixedly disposed on the first slider assembly (60), the second locking lever set (90) being fixedly disposed on the second slider assembly (70);

the first fuselage connector (100) is fixedly arranged at one end of the base (10), the second fuselage connector (110) is fixedly arranged at the other end of the base (10), the first fuselage connector (100) is provided with a first fuselage fitting hole (100a), and the second fuselage connector (110) is provided with a second fuselage fitting hole (110 a);

the first wing joint (120) and the second wing joint (130) are fixedly arranged on the wings of the unmanned aerial vehicle at intervals, the first wing joint (120) is provided with a first wing matching hole (120a), and the second wing joint (130) is provided with a second wing matching hole (130 a);

when the wings of the unmanned aerial vehicle and the body of the unmanned aerial vehicle need to be locked, the trapezoidal lead screw (20) positively rotates around a first direction to drive the first locking rod group (80) to be matched with the first body matching hole (100a) and the first wing matching hole (120a) respectively and drive the second locking rod group (90) to be matched with the second body matching hole (110a) and the second wing matching hole (130a) respectively; when needing to unblock unmanned aerial vehicle wing and unmanned aerial vehicle fuselage, trapezoidal lead screw (20) are around first direction antiport in order to drive first locking lever group (80) with first wing mating holes (120a) phase separation and drive second locking lever group (90) with second wing mating holes (130a) phase separation.

2. The unmanned aerial vehicle wing quick assembly disassembly mechanism of claim 1, wherein the base (10) comprises a pedestal assembly (11), a first guide rail (12) and a second guide rail (13), the first guide rail (12) is fixedly arranged on one side of the pedestal assembly (11), the second guide rail (13) is fixedly arranged on the other side of the pedestal assembly (11), and the first guide rail (12) and the second guide rail (13) are both arranged along a second direction; the first slider assembly (60) has a first guide slot that cooperates with the first guide rail (12), and the second slider assembly (70) has a second guide slot that cooperates with the second guide rail (13).

3. The unmanned aerial vehicle wing quick assembly disassembly mechanism of claim 2, wherein the base frame assembly (11) comprises a base frame (111), a first lug (112) and a second lug (113), the first lug (112) and the second lug (113) are fixedly arranged on the base frame (111) at intervals, one end of the trapezoidal lead screw (20) is rotatably arranged on the first lug (112), and the other end of the trapezoidal lead screw (20) is rotatably arranged on the second lug (113).

4. The unmanned aerial vehicle wing quick-attach-detach mechanism according to any one of claims 1 to 3, wherein the first slider assembly (60) comprises a first slider body (61) and a first pressing piece (62), the first slider body (61) is provided with the first guide groove and a first locking hole group, the first locking rod group (80) is matched with the first locking hole group, and the first pressing piece (62) is used for fixedly arranging the first locking rod group (80) on the first slider body (61); the second slider assembly (70) comprises a second slider body (71) and a second pressing piece (72), the second slider body (71) is provided with the second guide groove and a second locking hole group, the second locking rod group (90) is matched with the second locking hole group, and the second pressing piece (72) is used for fixedly arranging the second locking rod group (90) on the second slider body (71).

5. The mechanism of claim 4, wherein the first set of locking bars (80) comprises a plurality of first locking bars arranged at intervals, the first set of locking holes comprises a plurality of first locking holes arranged at intervals, and the plurality of first locking bars are matched with the plurality of first locking holes in a one-to-one correspondence manner; the second locking rod group (90) comprises a plurality of second locking rods arranged at intervals, the second locking hole group is provided with a plurality of second locking holes arranged at intervals, and the plurality of second locking rods are matched with the plurality of second locking holes in a one-to-one correspondence mode.

6. The unmanned aerial vehicle wing quick assembly disassembly mechanism of claim 5, wherein the free rod end of any locking lever adopts a chamfer design.

7. The fast dismounting mechanism of unmanned aerial vehicle wing according to claim 4, characterized in that, the first slider body (61) comprises a first slider (611) and a third lug (612), the first slider (611) has the first guide slot and the first locking hole set, the third lug (612) is fixedly arranged on the first slider (611), and the other end of the first link (40) is rotatably connected with the third lug (612); the second slider body (71) includes a second slider (711) and a fourth lug (712), the second slider (711) has the second guide groove and the second locking hole set, the fourth lug (712) is fixedly disposed on the second slider (711), and the other end of the second link (50) is rotatably connected to the fourth lug (712).

8. The unmanned aerial vehicle wing quick detach mechanism of claim 5, characterized in that the lead screw sleeve (30) comprises a sleeve body (31), a fifth lug (32) and a sixth lug (33), the sleeve body (31) is in threaded fit connection with the trapezoidal lead screw (20), the fifth lug (32) is fixedly arranged on one side of the sleeve body (31), the sixth lug (33) is fixedly arranged on the other side of the sleeve body (31), one end of the first connecting rod (40) is rotatably connected with the fifth lug (32), and one end of the second connecting rod (50) is rotatably connected with the sixth lug (33).

9. The fast dismounting and mounting mechanism for wings of unmanned aerial vehicle as claimed in claim 1, wherein the first body joint (100) comprises a first fitting plate, a first connecting plate and a second fitting plate which are connected in sequence, the first fitting plate and the second fitting plate are arranged in parallel, and the first fitting plate and the second fitting plate are provided with the first body fitting hole (100 a); the second machine body joint (110) comprises a third matching plate, a second connecting plate and a fourth matching plate which are sequentially connected, the third matching plate and the fourth matching plate are arranged in parallel, and the third matching plate and the fourth matching plate are provided with second machine body matching holes (110 a); when the unmanned aerial vehicle wing is in the locking state with the unmanned aerial vehicle fuselage, first wing joint (120) set up first cooperation board with between the second cooperation board, second wing joint (130) set up third cooperation board with between the fourth cooperation board.

10. An unmanned aerial vehicle, characterized in that, unmanned aerial vehicle includes fuselage (2000), wing (3000) and unmanned aerial vehicle wing quick assembly disassembly structure (1000), unmanned aerial vehicle wing quick assembly disassembly structure (1000) be any one of claims 1 to 9 unmanned aerial vehicle wing quick assembly disassembly structure (1000), wing (3000) pass through unmanned aerial vehicle wing quick assembly disassembly structure (1000) realize with the quick assembly disassembly of fuselage (2000).

Background

At present, the wing fuselage of most middle single-wing unmanned aerial vehicles adopts a multi-nail transverse connection mode. Traditional wing fuselage connection operation mode is for bolt and nut cooperation installation one by one, often because of bolt, nut are in great quantity, assembly order and assembly tolerance control scheduling problem, has prolonged unmanned aerial vehicle's technical preparation time greatly. In order to shorten the technical preparation time and improve the ground preparation efficiency of the unmanned aerial vehicle, a device which can meet the use requirement of connection of wings and bodies of the unmanned aerial vehicle and can meet the requirement of quick disassembly and assembly of the wings is required to be designed.

Disclosure of Invention

The invention provides a rapid wing dismounting mechanism of an unmanned aerial vehicle and the unmanned aerial vehicle with the same, and the rapid wing dismounting mechanism can solve the technical problems that in the prior art, when the wing is connected with a fuselage, the dismounting mechanism of the unmanned aerial vehicle is complex in assembly and long in time consumption.

According to an aspect of the invention, there is provided a mechanism for rapidly dismounting a wing of an unmanned aerial vehicle, the mechanism comprising: the base is fixedly arranged on the unmanned aerial vehicle body; the trapezoidal screw rod is rotatably arranged on the base; the lead screw sleeve is in threaded fit connection with the trapezoidal lead screw, and the trapezoidal lead screw can drive the lead screw sleeve to move along a first direction by rotating; one end of the first connecting rod is rotatably arranged on one side of the screw rod sleeve, and one end of the second connecting rod is rotatably arranged on the other side of the screw rod sleeve; the first sliding block assembly and the second sliding block assembly are movably arranged on the base, the first sliding block assembly is rotatably connected with the other end of the first connecting rod, the first connecting rod can drive the first sliding block assembly to move along a second direction, the second sliding block assembly is rotatably connected with the other end of the second connecting rod, the second connecting rod can drive the second sliding block assembly to move along the second direction, and the second direction is perpendicular to the first direction; the first locking rod group is fixedly arranged on the first sliding block component, and the second locking rod group is fixedly arranged on the second sliding block component; the first machine body joint is fixedly arranged at one end of the base, the second machine body joint is fixedly arranged at the other end of the base, the first machine body joint is provided with a first machine body matching hole, and the second machine body joint is provided with a second machine body matching hole; the first wing joint and the second wing joint are fixedly arranged on the wings of the unmanned aerial vehicle at intervals, the first wing joint is provided with a first wing matching hole, and the second wing joint is provided with a second wing matching hole; when the wings of the unmanned aerial vehicle and the body of the unmanned aerial vehicle need to be locked, the trapezoidal lead screw positively rotates around the first direction to drive the first locking rod group to be matched with the first body matching hole and the first wing matching hole respectively and drive the second locking rod group to be matched with the second body matching hole and the second wing matching hole respectively; when needs are with unmanned aerial vehicle wing and unmanned aerial vehicle fuselage unblock, trapezoidal lead screw is around first direction antiport in order to drive first locking lever group and first wing mating holes phase separation and drive second locking lever group and second wing mating holes phase separation.

Further, the base comprises a pedestal assembly, a first guide rail and a second guide rail, the first guide rail is fixedly arranged on one side of the pedestal assembly, the second guide rail is fixedly arranged on the other side of the pedestal assembly, and the first guide rail and the second guide rail are both arranged along a second direction; the first slider assembly has a first guide slot that mates with the first guide rail, and the second slider assembly has a second guide slot that mates with the second guide rail.

Further, the base frame assembly comprises a base frame, a first lug and a second lug, the first lug and the second lug are fixedly arranged on the base frame at intervals, one end of the trapezoidal screw rod is rotatably arranged on the first lug, and the other end of the trapezoidal screw rod is rotatably arranged on the second lug.

Furthermore, the first sliding block assembly comprises a first sliding block body and a first pressing piece, the first sliding block body is provided with a first guide groove and a first locking hole group, the first locking rod group is matched with the first locking hole group, and the first pressing piece is used for fixedly arranging the first locking rod group on the first sliding block body; the second sliding block assembly comprises a second sliding block body and a second pressing piece, the second sliding block body is provided with a second guide groove and a second locking hole group, the second locking rod group is matched with the second locking hole group, and the second pressing piece is used for fixedly arranging the second locking rod group on the second sliding block body.

Further, the first locking rod group comprises a plurality of first locking rods arranged at intervals, the first locking hole group is provided with a plurality of first locking holes arranged at intervals, and the plurality of first locking rods are matched with the plurality of first locking holes in a one-to-one correspondence manner; the second locking rod group comprises a plurality of second locking rods arranged at intervals, the second locking hole group is provided with a plurality of second locking holes arranged at intervals, and the plurality of second locking rods are matched with the plurality of second locking holes in a one-to-one correspondence mode.

Further, the free rod end of any locking rod adopts a chamfer design.

Further, the first sliding block body comprises a first sliding block and a third lug, the first sliding block is provided with a first guide groove and a first locking hole group, the third lug is fixedly arranged on the first sliding block, and the other end of the first connecting rod is rotatably connected with the third lug; the second sliding block body comprises a second sliding block and a fourth lug, the second sliding block is provided with a second guide groove and a second locking hole group, the fourth lug is fixedly arranged on the second sliding block, and the other end of the second connecting rod is rotatably connected with the fourth lug.

Further, the lead screw sleeve comprises a sleeve body, a fifth lug and a sixth lug, the sleeve body is connected with the trapezoidal lead screw in a threaded fit mode, the fifth lug is fixedly arranged on one side of the sleeve body, the sixth lug is fixedly arranged on the other side of the sleeve body, one end of the first connecting rod is rotatably connected with the fifth lug, and one end of the second connecting rod is rotatably connected with the sixth lug.

Furthermore, the first machine body joint comprises a first matching plate, a first connecting plate and a second matching plate which are sequentially connected, the first matching plate and the second matching plate are arranged in parallel, and the first matching plate and the second matching plate are provided with first machine body matching holes; the second machine body joint comprises a third matching plate, a second connecting plate and a fourth matching plate which are sequentially connected, the third matching plate and the fourth matching plate are arranged in parallel, and the third matching plate and the fourth matching plate are provided with second machine body matching holes; when the unmanned aerial vehicle wing is in the locking state with the unmanned aerial vehicle fuselage, first wing connects the setting between first cooperation board and second cooperation board, and the setting is connected between third cooperation board and fourth cooperation board to the second wing.

According to another aspect of the invention, an unmanned aerial vehicle is provided, which comprises a body, wings and an unmanned aerial vehicle wing quick assembly and disassembly structure, wherein the unmanned aerial vehicle wing quick assembly and disassembly structure is the unmanned aerial vehicle wing quick assembly and disassembly structure, and the wings are quickly assembled and disassembled with the body through the unmanned aerial vehicle wing quick assembly and disassembly structure.

By applying the technical scheme of the invention, the rapid wing dismounting and mounting mechanism of the unmanned aerial vehicle is provided, the rapid wing dismounting and mounting mechanism of the unmanned aerial vehicle adopts a trapezoidal lead screw structure, and the trapezoidal lead screw acts to respectively drive a lead screw sleeve, a connecting rod, a sliding block assembly and a locking rod group to act so as to realize the separation or connection of the locking rod group and a fuselage joint and a wing joint; meanwhile, the self-locking characteristic of the trapezoidal lead screw is utilized, and the anti-loosening effect can be achieved after the wing joint and the body joint are connected.

Drawings

The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.

Fig. 1 is a schematic diagram illustrating a detached state of a fast wing detachment mechanism of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 2 is a schematic diagram illustrating a fast wing dismounting mechanism of an unmanned aerial vehicle provided according to an embodiment of the present invention in a connected state;

FIG. 3 illustrates a schematic view of a fuselage joint provided in accordance with an exemplary embodiment of the present invention in a detached state from a wing structure;

FIG. 4 illustrates a schematic view of a fuselage joint and wing structure provided in connection according to an embodiment of the present invention.

Wherein the figures include the following reference numerals:

10. a base; 11. a base frame assembly; 111. a base frame; 112. a first lug; 113. a second lug; 12. a first guide rail; 13. a second guide rail; 20. a trapezoidal lead screw; 30. a lead screw sleeve; 31. a sleeve body; 32. a fifth lug; 33. a sixth lug; 40. a first link; 50. a second link; 60. a first slider assembly; 61. a first slider body; 611. a first slider; 612. a third lug; 62. a first tablet; 70. a second slider assembly; 71. a second slider body; 711. a second slider; 712. a fourth lug; 72. a second tabletting; 80. a first set of locking bars; 90. a second set of locking bars; 100. a first body joint; 100a, a first body fitting hole; 110. a second fuselage plug; 110a, a second fuselage fitting hole; 120. a first wing joint; 120a, a first wing mating hole; 130. a second wing joint; 130a, a second wing mating hole; 140. a bearing; 150. a pin; 1000. an unmanned aerial vehicle wing quick dismounting structure; 2000. a body; 3000. an airfoil.

Detailed Description

It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.

The relative arrangement of the components and steps, the numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.

As shown in fig. 1 to 4, according to an embodiment of the present invention, there is provided a fast dismounting and mounting mechanism for wings of an unmanned aerial vehicle, the fast dismounting and mounting mechanism for wings of an unmanned aerial vehicle comprises a base 10, a trapezoidal lead screw 20, a lead screw sleeve 30, a first connecting rod 40, a second connecting rod 50, a first slider assembly 60, a second slider assembly 70, a first locking rod group 80, a second locking rod group 90, a first body joint 100, a second body joint 110, a first wing joint 120 and a second wing joint 130, the base 10 is fixedly disposed on a body of the unmanned aerial vehicle, the trapezoidal lead screw 20 is rotatably disposed on the base 10, the lead screw sleeve 30 is in threaded fit connection with the trapezoidal lead screw 20, the trapezoidal lead screw 20 is rotated to drive the lead screw sleeve 30 to move along a first direction, one end of the first connecting rod 40 is rotatably disposed on one side of the lead screw sleeve 30, one end of the second connecting rod 50 is rotatably disposed on the other side of the lead screw sleeve 30, the first slider assembly 60 and the second slider assembly 70 are movably arranged on the base 10, the first slider assembly 60 is rotatably connected with the other end of the first connecting rod 40, the first connecting rod 40 can drive the first slider assembly 60 to move along a second direction, the second slider assembly 70 is rotatably connected with the other end of the second connecting rod 50, the second connecting rod 50 can drive the second slider assembly 70 to move along the second direction, the second direction is perpendicular to the first direction, the first locking rod group 80 is fixedly arranged on the first slider assembly 60, the second locking rod group 90 is fixedly arranged on the second slider assembly 70, the first fuselage joint 100 is fixedly arranged at one end of the base 10, the second fuselage joint 110 is fixedly arranged at the other end of the base 10, the first fuselage joint 100 is provided with a first fuselage fitting hole 100a, the second fuselage joint 110 is provided with a second fuselage fitting hole 110a, the first fuselage joint and the second wing joint 130 are fixedly arranged on the wings at intervals, the first wing joint 120 has a first wing mating hole 120a and the second wing joint 130 has a second wing mating hole 130 a; when the wings of the unmanned aerial vehicle and the body of the unmanned aerial vehicle need to be locked, the trapezoidal lead screw 20 positively rotates around the first direction to drive the first locking rod group 80 to be matched with the first body matching hole 100a and the first wing matching hole 120a respectively and drive the second locking rod group 90 to be matched with the second body matching hole 110a and the second wing matching hole 130a respectively; when the wings and the fuselage of the unmanned aerial vehicle need to be unlocked, the trapezoidal lead screw 20 reversely rotates around the first direction to drive the first locking rod group 80 to be separated from the first wing matching hole 120a and drive the second locking rod group 90 to be separated from the second wing matching hole 130 a.

By applying the configuration mode, the rapid wing dismounting and mounting mechanism of the unmanned aerial vehicle is provided, the rapid wing dismounting and mounting mechanism of the unmanned aerial vehicle adopts a trapezoidal lead screw structure, and the trapezoidal lead screw acts to respectively drive a lead screw sleeve, a connecting rod, a sliding block assembly and a locking rod group to act so as to realize the separation or connection of the locking rod group with a fuselage joint and a wing joint; meanwhile, the self-locking characteristic of the trapezoidal lead screw is utilized, and the anti-loosening effect can be achieved after the wing joint and the body joint are connected.

Specifically, when the wings of the unmanned aerial vehicle are required to be locked with the body of the unmanned aerial vehicle, the trapezoidal lead screw rotates around the first direction in a positive direction, the trapezoidal lead screw drives the lead screw sleeve to move downwards along the first direction, the lead screw sleeve simultaneously drives the first connecting rod and the second connecting rod to expand outwards, the first connecting rod acts to drive the first slider assembly and the first locking rod group to move towards the direction close to the first body joint and the first wing joint until the first locking rod group is respectively matched with the first body matching hole and the first wing matching hole, and the second connecting rod acts to drive the second slider assembly and the second locking rod group to move towards the direction close to the second body joint and the second wing matching hole until the second locking rod group is respectively matched with the second body matching hole and the second wing matching hole, so that the locking connection of the wings and the body is realized; when needs are with unmanned aerial vehicle wing and unmanned aerial vehicle fuselage unblock, trapezoidal lead screw is around first direction antiport, trapezoidal lead screw drives the lead screw sleeve and follows first direction upward movement, the lead screw sleeve drives first connecting rod and second connecting rod inward folding simultaneously, first connecting rod action is kept away from the direction motion of first fuselage joint and first wing joint with the orientation of drive first slider subassembly and first locking lever group until first locking lever group and first wing mating holes phase separation, second connecting rod action is kept away from second fuselage joint and second wing joint motion until second locking lever group and second wing mating holes phase separation with the orientation of drive second slider subassembly and second locking lever group, realize the unblock of wing and fuselage from this.

Further, in the present invention, in order to realize the movement of the first slider assembly and the second slider assembly along the second direction, the base 10 may be configured to include a base frame assembly 11, a first rail 12 and a second rail 13, the first rail 12 is fixedly disposed at one side of the base frame assembly 11, the second rail 13 is fixedly disposed at the other side of the base frame assembly 11, and both the first rail 12 and the second rail 13 are disposed along the second direction; the first slider assembly 60 has a first guide slot that mates with the first guide rail 12, and the second slider assembly 70 has a second guide slot that mates with the second guide rail 13. As an embodiment of the present invention, the base frame assembly 11 is integrally formed with the first track 12 and the second track 13, respectively, in a manner that has good integrity but a slightly complicated process. As another embodiment of the present invention, the base frame assembly, the first track 12 and the second track 13 may be separately machined and then connected by assembling, which is simple in machining process, easy to replace after some parts are worn, but relatively poor in integrity.

In addition, in the present invention, in order to simplify the manufacturing process and facilitate the installation of the trapezoidal lead screw on the base frame assembly, the base frame assembly 11 may be configured to include a base frame 111, a first lug 112 and a second lug 113, the first lug 112 and the second lug 113 are fixedly disposed on the base frame 111 at intervals, one end of the trapezoidal lead screw 20 is rotatably disposed on the first lug 112, and the other end of the trapezoidal lead screw 20 is rotatably disposed on the second lug 113.

As an embodiment of the present invention, as shown in fig. 1, the first lug 112 is fixedly mounted on the upper portion of the base frame 111 by a screw, the second lug 113 is fixedly mounted on the lower portion of the base frame 111 by a screw, a bearing 140 is disposed between the first lug 112 and one end of the trapezoidal screw 20, and a bearing 140 is also disposed between the second lug 113 and the other end of the trapezoidal screw 20, so that smooth rotation of the trapezoidal screw 20 on the first lug 112 and the second lug 113 can be achieved.

Further, in the present invention, in order to achieve the fixed mounting of the first and second lock lever groups on the first and second slider assemblies, respectively, the first slider assembly 60 may be configured to include a first slider body 61 and a first pressing piece 62, the first slider body 61 having a first guide groove and a first lock hole group, the first lock lever group 80 being engaged with the first lock hole group, the first pressing piece 62 being used to fixedly dispose the first lock lever group 80 on the first slider body 61; the second slider assembly 70 includes a second slider body 71 and a second pressing piece 72, the second slider body 71 has a second guide groove and a second locking hole group, the second locking lever group 90 is engaged with the second locking hole group, and the second pressing piece 72 is used for fixedly disposing the second locking lever group 90 on the second slider body 71.

In addition, in the present invention, in order to improve the firmness of the connection between the wing and the fuselage, the first locking rod group 80 may be configured to include a plurality of first locking rods arranged at intervals, the first locking hole group has a plurality of first locking holes arranged at intervals, and the plurality of first locking rods are matched with the plurality of first locking holes in a one-to-one correspondence manner; the second locking bar group 90 includes a plurality of second locking bars arranged at intervals, the second locking hole group has a plurality of second locking holes arranged at intervals, and the plurality of second locking bars are matched with the plurality of second locking holes in a one-to-one correspondence manner.

As a specific embodiment of the present invention, as shown in fig. 1 and fig. 2, the first locking bar group 80 includes two first locking bars arranged at intervals, the first locking hole group has two first locking holes arranged at intervals, and the two first locking bars are matched with the two first locking holes in a one-to-one correspondence; the second locking bar group 90 includes two second locking bars arranged at intervals, and the second locking hole group has two second locking holes arranged at intervals, and the two second locking bars are matched with the two second locking holes in a one-to-one correspondence manner. In addition, in the invention, in order to facilitate the smooth matching of the locking lever with the fuselage matching hole and the wing matching hole, the free lever end of any locking lever can adopt a chamfer design, and the free lever end of the locking lever refers to the end of the locking lever facing the wing joint.

Further, in the present invention, in order to facilitate the connection of the first slider body and the second slider body with the first link and the second link, respectively, the first slider body 61 may be configured to include a first slider 611 and a third lug 612, the first slider 611 has a first guide groove and a first locking hole group, the third lug 612 is fixedly disposed on the first slider 611, and the other end of the first link 40 is rotatably connected with the third lug 612; the second slider body 71 includes a second slider 711 having a second guide groove and a second locking hole group, and a fourth lug 712 fixedly provided on the second slider 711, and the other end of the second link 50 is rotatably connected to the fourth lug 712. In an embodiment of the present invention, the other end of the first link 40 is rotatably connected to the third lug 612 by the pin 150, and the other end of the second link 50 is rotatably connected to the fourth lug 712 by the pin 150.

In addition, in the present invention, in order to facilitate connection of the screw sleeve to the first link and the second link, respectively, the screw sleeve 30 may be configured to include a sleeve body 31, a fifth lug 32, and a sixth lug 33, the sleeve body 31 is in threaded fit connection with the trapezoidal screw 20, the fifth lug 32 is fixedly disposed at one side of the sleeve body 31, the sixth lug 33 is fixedly disposed at the other side of the sleeve body 31, one end of the first link 40 is rotatably connected to the fifth lug 32, and one end of the second link 50 is rotatably connected to the sixth lug 33.

Further, in the present invention, in order to improve the connection firmness between the wing and the fuselage, the first fuselage joint 100 may be configured to include a first mating plate, a first connecting plate, and a second mating plate that are connected in sequence, where the first mating plate and the second mating plate are arranged in parallel, and both the first mating plate and the second mating plate have a first fuselage mating hole 100 a; the second body joint 110 comprises a third matching plate, a second connecting plate and a fourth matching plate which are connected in sequence, the third matching plate and the fourth matching plate are arranged in parallel, and the third matching plate and the fourth matching plate are provided with second body matching holes 110 a; when the unmanned aerial vehicle wing is in the locking state with the unmanned aerial vehicle fuselage, first wing connects 120 and sets up between first cooperation board and second cooperation board, and second wing connects 130 and sets up between third cooperation board and fourth cooperation board.

According to another aspect of the invention, an unmanned aerial vehicle is provided, the unmanned aerial vehicle comprises a fuselage 2000, wings 3000 and an unmanned aerial vehicle wing quick-assembly and disassembly structure 1000, the unmanned aerial vehicle wing quick-assembly and disassembly structure 1000 is the unmanned aerial vehicle wing quick-assembly and disassembly structure 1000, and the wings 3000 can be quickly assembled and disassembled with the fuselage 2000 through the unmanned aerial vehicle wing quick-assembly and disassembly structure 1000.

By applying the configuration mode, the unmanned aerial vehicle is provided, and the wings of the unmanned aerial vehicle can be quickly assembled and disassembled with the body through the quick assembling and disassembling structure of the wings of the unmanned aerial vehicle; meanwhile, the self-locking characteristic of the trapezoidal lead screw is utilized, and the anti-loosening effect can be achieved after the wing joint and the body joint are connected. Therefore, the rapid wing dismounting structure of the unmanned aerial vehicle is applied to the unmanned aerial vehicle, and the working performance of the unmanned aerial vehicle can be greatly improved.

For further understanding of the present invention, the following describes the fast dismounting structure of wings of an unmanned aerial vehicle provided by the present invention in detail with reference to fig. 1 to 4.

As shown in fig. 1 to 4, according to an embodiment of the present invention, there is provided a rapid wing detachment structure for an unmanned aerial vehicle, which includes a base 10, a trapezoidal lead screw 20, a lead screw sleeve 30, a first connecting rod 40, a second connecting rod 50, a first slider assembly 60, a second slider assembly 70, a first locking rod group 80, a second locking rod group 90, a first body joint 100, a second body joint 110, a first wing joint 120, a second wing joint 130, a bearing 140, and a pin 150, wherein the base 10 includes a base assembly 11, a first rail 12, and a second rail 13, the first rail 12 is fixedly disposed on one side of the base assembly 11, the second rail 13 is fixedly disposed on the other side of the base assembly 11, and both the first rail 12 and the second rail 13 are disposed along a second direction. The base frame assembly 11 comprises a base frame 111, a first lug 112 and a second lug 113, wherein the first lug 112 and the second lug 113 are fixedly arranged on the base frame 111 at intervals, one end of the trapezoidal screw rod 20 is rotatably arranged on the first lug 112 through a bearing 140, and the other end of the trapezoidal screw rod 20 is rotatably arranged on the second lug 113 through the bearing 140. The first body joint 100 is fixed to one end of the base frame 111 by screws, and the second body joint 110 is fixed to the other end of the base frame 111 by screws.

The screw sleeve 30 comprises a sleeve body 31, a fifth lug 32 and a sixth lug 33, the sleeve body 31 is in threaded fit connection with the trapezoidal screw 20, the fifth lug 32 is fixedly arranged on one side of the sleeve body 31, the sixth lug 33 is fixedly arranged on the other side of the sleeve body 31, one end of the first connecting rod 40 is rotatably connected with the fifth lug 32 by a pin 150, and one end of the second connecting rod 50 is rotatably connected with the sixth lug 33 by the pin 150.

The first slider assembly 60 includes a first slider 611, a third lug 612 and a first pressing piece 62, the first slider 611 has a first guide groove and a first locking hole group, the first guide groove is matched with the first guide rail 12, and the length of the first guide rail 12 can be designed according to the stroke requirement of the first slider 611. The first locking rod group 80 is matched with the first locking hole group, the first pressing piece 62 is used for fixedly arranging the first locking rod group 80 on the first sliding block 611, the third lug 612 is fixedly arranged on the first sliding block 611, and the other end of the first connecting rod 40 is rotatably connected with the third lug 612 by the pin 150; the second slider assembly 70 includes a second slider 711, a fourth lug 712 and a second pressing plate 72, the second slider 711 has a second guide groove and a second locking hole group, the second guide groove is matched with the second guide rail 13, and the length of the second guide rail 13 can be designed according to the stroke requirement of the second slider 711. The second locking rod group 90 is engaged with the second locking hole group, the second pressing piece 72 is used for fixedly arranging the second locking rod group 90 on the second slider 711, the fourth lug 712 is fixedly arranged on the second slider 711, and the other end of the second link 50 is rotatably connected with the fourth lug 712 by the pin 150.

The first locking rod group 80 comprises two first locking rods arranged at intervals, the first locking hole group is provided with two first locking holes arranged at intervals, and the two first locking rods are correspondingly matched with the two first locking holes one by one; the second locking bar group 90 includes two second locking bars arranged at intervals, and the second locking hole group has two second locking holes arranged at intervals, and the two second locking bars are matched with the two second locking holes in a one-to-one correspondence manner. In this embodiment, the first locking lever and the second locking lever are both self-made bolts. First locking lever is downthehole through first preforming 62 fixed mounting to first locking, and the second locking lever passes through second preforming 72 fixed mounting to the second locking, and the head of self-control bolt adopts the chamfer design, and preforming and self-control bolt cooperation contact area design clearance, self-control bolt can slide at the downthehole smallly of locking.

In this embodiment, when the wings 3000 of the drone and the drone body 2000 need to be locked, the first wing joint 120 fits the lower limit surface of the first fuselage joint 100 and is inserted into the groove of the first fuselage joint 100, the second wing joint 130 fits the lower limit surface of the second fuselage joint 110 and is inserted into the groove of the second fuselage joint 110, the trapezoidal lead screw 20 is rotated by a hex wrench and rotates around the first direction, the trapezoidal lead screw 20 drives the lead screw sleeve 30 to move downward along the first direction, the lead screw sleeve 30 drives the first connecting rod 40 and the second connecting rod 50 to expand outward at the same time, the first connecting rod 40 acts to drive the first slider assembly 60 and the first locking rod group 80 to move along the first guide rail 12 of the base 10 toward the direction close to the first fuselage joint 100 and the first fuselage joint 120 until the first locking rod group 80 matches the first fuselage mating hole and the first fuselage mating hole respectively, the second link 50 acts to drive the second slider assembly 70 and the second locking lever assembly 90 to move along the second guide rail 13 of the base 10 toward the direction close to the second fuselage joint 110 and the second wing joint 130 until the second locking lever assembly 90 respectively engages with the second fuselage mating bore and the second wing mating bore, thereby achieving the locked connection of the wing to the fuselage.

When the unmanned aerial vehicle wing 3000 and the unmanned aerial vehicle fuselage 2000 need to be unlocked, the trapezoidal lead screw 20 is reversely rotated by using a hexagonal wrench to reversely rotate around the first direction, the trapezoidal lead screw 20 drives the lead screw sleeve 30 to move upwards along the first direction, the lead screw sleeve 30 simultaneously drives the first connecting rod 40 and the second connecting rod 50 to fold inwards, the first connecting rod 40 acts to drive the first slider assembly 60 and the first locking rod group 80 to move along the first guide rail 12 of the base 10 towards the direction far away from the first fuselage joint 100 and the first wing joint 120 until the first locking rod group 80 is separated from the first wing matching hole, the second connecting rod 50 acts to drive the second slider assembly 70 and the second locking rod group 90 to move along the second guide rail 13 of the base 10 towards the direction far away from the second fuselage joint 110 and the second wing joint 130 until the second locking rod group 90 is separated from the second wing matching hole, and therefore unlocking of the wing 3000 and the fuselage 2000 is realized.

In conclusion, the invention provides the rapid wing dismounting and mounting mechanism for the unmanned aerial vehicle, which adopts a trapezoidal lead screw structure, and the trapezoidal lead screw acts to respectively drive a lead screw sleeve, a connecting rod, a sliding block assembly and a locking rod group to act so as to realize the separation or connection of the locking rod group and a fuselage joint and a wing joint, so that the mode has the advantages of simple operation, large acting force, easy realization and short consumed time; meanwhile, the self-locking characteristic of the trapezoidal lead screw is utilized, and the anti-loosening effect can be achieved after the wing joint and the body joint are connected. Therefore, compared with the prior art, the rapid wing dismounting and mounting mechanism for the unmanned aerial vehicle, provided by the invention, not only can meet the use requirement of connecting the wing body of the unmanned aerial vehicle, but also can realize rapid wing dismounting and mounting, shorten the technical preparation time and improve the ground preparation efficiency of the unmanned aerial vehicle.

In the description of the present invention, it is to be understood that the orientation or positional relationship indicated by the orientation words such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal" and "top, bottom", etc. are usually based on the orientation or positional relationship shown in the drawings, and are only for convenience of description and simplicity of description, and in the case of not making a reverse description, these orientation words do not indicate and imply that the device or element being referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore, should not be considered as limiting the scope of the present invention; the terms "inner and outer" refer to the inner and outer relative to the profile of the respective component itself.

Spatially relative terms, such as "above … …," "above … …," "above … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial relationship to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above … …" can include both an orientation of "above … …" and "below … …". The device may be otherwise variously oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.

It should be noted that the terms "first", "second", and the like are used to define the components, and are only used for convenience of distinguishing the corresponding components, and the terms have no special meanings unless otherwise stated, and therefore, the scope of the present invention should not be construed as being limited.

The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.