CN218142088U

CN218142088U - Connecting assembly, rotation connecting device and unmanned aerial vehicle of unmanned aerial vehicle wing

Info

Publication number: CN218142088U
Application number: CN202221513998.1U
Authority: CN
Inventors: 吴旭民; 朱杰
Original assignee: Guangzhou Xaircraft Technology Co Ltd
Current assignee: Guangzhou Xaircraft Technology Co Ltd
Priority date: 2022-06-16
Filing date: 2022-06-16
Publication date: 2022-12-27
Anticipated expiration: 2032-06-16

Abstract

The application provides coupling assembling, rotation connecting device and unmanned aerial vehicle of unmanned aerial vehicle wing, coupling assembling includes: the guiding sleeve is arranged to be fixed on the body of the unmanned aerial vehicle; the guide rod is inserted into the guide sleeve, can axially move relative to the guide sleeve and can rotate relative to the guide sleeve, and a first end of the guide rod, which extends out of the guide sleeve, is arranged to be rotatably connected with the folding wing; wherein, the uide bushing passes through limit structure cooperation with the guide bar, and limit structure sets up to carry out the axial spacing and carry out circumference spacing to the rotation of guide bar to the axial displacement of guide bar. The technical scheme that this application provided can conveniently and effectively control the angle of the pull-out distance and relative fuselage of folding wing when folding the wing, does benefit to the efficiency when promoting the wing folding to can reduce because exert oneself too hard and rotatory other positions that lead to wing and aircraft damage excessively.

Description

Connecting assembly, rotation connecting device and unmanned aerial vehicle of unmanned aerial vehicle wing

Technical Field

The application relates to the technical field of unmanned aerial vehicles, concretely relates to coupling assembling, rotation connecting device and unmanned aerial vehicle of unmanned aerial vehicle wing.

Background

In the prior art, in the folding process of the folding wing on the unmanned aerial vehicle, the folding wing is usually pulled out for a certain distance in the direction away from the fuselage, then rotates for a certain angle relative to the fuselage, and then is folded towards the rear of the fuselage.

At present, the pulling-out distance and the rotating angle of the folding wing in the direction far away from the fuselage are usually performed by the operation experience or feeling of an operator, and the pulling-out distance and the rotating angle of the folding wing need to be adjusted in the pulling-out and rotating processes, so that the folding efficiency of the folding wing is not high, and the wing and other parts of an airplane are easily damaged if the operator uses too hard force and rotates too much.

Disclosure of Invention

In view of this, this application provides a coupling assembling, rotation connecting device and unmanned aerial vehicle of unmanned aerial vehicle wing to folding wing pulls out and rotates the problem that the operation exists among the prior art in folding process.

The application provides a coupling assembling of unmanned aerial vehicle wing, coupling assembling includes:

the guiding sleeve is arranged on a body of the unmanned aerial vehicle and is used for being fixed on the body;

the guide rod is inserted into the guide sleeve, can move axially relative to the guide sleeve and can rotate relative to the guide sleeve, and a first end of the guide rod, which extends out of the guide sleeve, is arranged to be rotatably connected with a folding wing of the unmanned aerial vehicle;

the guide sleeve is matched with the guide rod through a limiting structure, and the limiting structure is used for axially limiting the axial movement of the guide rod and circumferentially limiting the rotation of the guide rod.

Optionally, the limiting structure comprises a limiting groove formed in the guide sleeve and a limiting column protruding from the outer surface of the guide rod, and the limiting column is configured to move along the limiting groove;

the limiting groove is an L-shaped groove formed by an axial groove extending axially and a circumferential groove extending circumferentially, the axial groove is used for axially limiting the axial movement of the guide rod, the limiting column moves to the position, close to the axial groove, of one end of the circumferential groove and rotates to enter the circumferential groove, and the circumferential groove is used for circumferentially limiting the rotation of the guide rod.

Optionally, the circumferential groove is provided at an end of the axial groove proximate to the first end of the guide rod.

Optionally, a shaft sleeve is sleeved on the guide rod, and the limiting column is arranged on the shaft sleeve.

In another aspect of the present application, there is also provided a rotary connection device, which includes a universal joint and the connection assembly as described above;

the first connecting end of the universal joint is connected with the first end of the guide rod, and the second connecting end of the universal joint is used for being connected with the folding wing.

Optionally, the rotating connection device further comprises a rotating part, the second connection end is connected to the rotating part, and the rotating part is used for being connected with the folding wings of the unmanned aerial vehicle.

Optionally, the gimbal is provided as a hollow structure through which wires can pass.

Optionally, an intermediate connection portion is disposed between the first connection end and the second connection end of the universal joint, and the first connection end and the second connection end are respectively hinged to the intermediate connection portion;

wherein a channel for passing through a wire is formed between the first connecting end and/or the second connecting end and the intermediate connecting part.

Optionally, the first connection end comprises two first connection lugs extending towards the intermediate connection portion, and the intermediate connection portion comprises two third connection lugs extending towards the first connection end; each first connecting lug corresponds to one third connecting lug respectively and is rotatably connected through a rotating shaft, and a first channel capable of passing through a wire is formed between connecting structures correspondingly connected with the two first connecting lugs and the third connecting lug respectively;

and/or the second connecting end comprises two second engaging lugs extending towards the intermediate connecting part, and the intermediate connecting part comprises two fourth engaging lugs extending towards the second connecting end; each second engaging lug corresponds to one fourth engaging lug respectively and is connected through the pivot rotation, two second engaging lug with form the second passageway that can pass the wire rod between the connection structure that fourth engaging lug corresponds the connection formation respectively.

The application also provides an unmanned aerial vehicle, which comprises a body, folding wings and the rotary connecting device;

the guide sleeve in the rotary connecting device is fixed on the airframe, and the second connecting end of the universal joint is connected with the folding wing.

The technical scheme that this application provided can conveniently and effectively control the angle of the pull-out distance and relative fuselage of folding wing when folding the wing, does benefit to the efficiency when promoting the wing folding to can reduce because exert oneself too hard and rotatory other positions that lead to wing and aircraft damage excessively. Moreover, the connecting assembly provided by the application is simple in structure and low in cost.

Additional features and advantages of the present application will be described in detail in the detailed description which follows.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the application and, together with the description, serve to explain the application and are not intended to limit the application. In the drawings:

FIG. 1 is a schematic structural view of a connection assembly according to one embodiment of the present application;

FIG. 2 is a schematic view of the connection assembly of FIG. 1 in a disengaged state;

FIG. 3 is a schematic view of a swivel joint assembly according to one embodiment of the present application;

FIG. 4 is an enlarged view taken at A in FIG. 3;

fig. 5 is a schematic structural diagram of a drone according to one embodiment of the present application;

FIG. 6 is an enlarged view of FIG. 5 at B;

FIG. 7 is a schematic view of the structure of FIG. 5 after the fuselage and the folding wings are hidden;

fig. 8 is a top view of fig. 7.

Description of the reference numerals:

1-a rotating connection; 11-a guide bar; 111-a spacing post; 112-shaft sleeve; 12-a rotating part; 13-a universal joint; 131-a first connection end; 1311 a first connection ear; 132-a second connection end; 1321-a second engaging ear; 133-intermediate connection; 1331-a third engaging lug; 1332-a fourth engaging lug; 14-a guide sleeve; 141-axial grooves; 142-a circumferential groove; 2-a first locking assembly; 3-a second locking assembly; 100-a fuselage; 101-a first rib; 102-a second rib; 200-folding wings; 201-third rib plate; 202-fourth rib.

Detailed Description

The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only a part of the embodiments of the present application, and not all of the embodiments. 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 application. In the present application, the embodiments and the features of the embodiments may be combined with each other without conflict.

In the description of the present application, it is to be understood that the terms "central," "longitudinal," "lateral," "upper," "lower," "left," "right," "vertical," "horizontal," "top," "bottom," "axial," "radial," "circumferential," and the like are used in the orientation or positional relationship indicated in the drawings for convenience in describing the present application and for simplicity in description, and are not intended to indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be considered limiting of the present application. The term "inside" and "outside" refer to the inside and the outside of the contour of each member itself.

Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of the feature.

The application provides a coupling assembling of unmanned aerial vehicle wing, as shown in fig. 1 and fig. 2, coupling assembling includes:

the guide sleeve 14, the guide sleeve 14 is set up to be used for being fixed on the fuselage of the unmanned aerial vehicle;

the guide rod 11 is inserted into the guide sleeve 14, and can axially move relative to the guide sleeve 14 and can rotate relative to the guide sleeve 14, wherein a first end of the guide rod 11, which extends out of the guide sleeve 14, is arranged to be rotatably connected with a folding wing of the unmanned aerial vehicle;

the guide sleeve 14 is matched with the guide rod 11 through a limiting structure, and the limiting structure is used for axially limiting the axial movement of the guide rod 11 and circumferentially limiting the rotation of the guide rod 11.

It should be noted that the "fuselage" described in this application includes a fuselage body, and may further include a fixed wing portion provided on the fuselage body, and the guide sleeve 14 and the guide rod 11 may be mounted on the fuselage body (in a case where the foldable wing is connected to the fuselage body), or may be mounted on the fixed wing portion (in a case where the foldable wing is connected to the fixed wing portion).

The application provides a coupling assembling is when being applied to unmanned aerial vehicle, installs uide bushing 14 and guide bar 11 in the fuselage, sets up articulated connecting piece between the first end of the folding wing of orientation of guide bar 11 and folding wing, and this articulated connecting piece can be the universal joint, also can be the pivotal axis for folding wing can rotate to realizing folding for guide bar 11.

When folding wing, earlier with folding wing to the direction pulling certain distance of keeping away from the fuselage, guide bar 11 axial displacement to the removal of folding wing is led, when guide bar 11 axial displacement arrives the preset position, limit structure carries out the axial spacing to guide bar 11, then rotates folding wing around the axis of guide bar 11, drives guide bar 11 and rotates, and limit structure carries out circumference spacing to the rotation of guide bar 11, when folding wing rotates to have the angle of predetermineeing with the fuselage, again with folding wing towards the fuselage rear folding. When the folding wings are restored to the unfolding state during flying from the folding state, reverse operation is only needed, and the limiting structures also limit the movement of the guide rods 11 in the axial direction and the circumferential direction.

Therefore, the connecting component provided by the application can conveniently and effectively control the pulling-out distance of the folding wing and the angle of the folding wing relative to the airplane body when the wing is folded, is beneficial to improving the efficiency of the folding wing, and can reduce the damage to the wing and other parts of the airplane caused by overexertion and excessive rotation. Moreover, the connecting assembly provided by the application is simple in structure and low in cost.

In one embodiment, as shown in fig. 1 and 2, the limiting structure includes a limiting groove formed on the guide sleeve 14 and a limiting post 111 convexly formed on an outer surface of the guide rod 11, and the limiting post 111 is configured to move along the limiting groove.

The limiting groove is an L-shaped groove formed by an axial groove 141 extending axially and a circumferential groove 142 extending circumferentially, the axial groove 141 axially limits axial movement of the guide rod 11, and when the limiting column 111 moves to one end of the axial groove 141 close to the circumferential groove 142 and rotates into the circumferential groove 142, the circumferential groove 142 circumferentially limits rotation of the guide rod 11.

In this embodiment, the circumferential groove 142 is provided at an end of the axial groove 141 near the first end of the guide rod.

When the folding wing is folded, the folding wing is pulled in the direction away from the fuselage, in the process that the folding wing and the guide rod 11 move together, the limiting column 111 moves along the axial groove 141 until the limiting column 111 reaches the end of the axial groove 141, then the folding wing and the guide rod 11 rotate together, the limiting column 111 enters the circumferential groove 142 from the axial groove 141 to move, the circumferential groove 142 circumferentially limits the rotation of the limiting column 111, and after the folding wing rotates around the axis of the guide rod 11 by a preset angle, the folding wing rotates to the position close to the rear of the fuselage through the hinge component and is in a folded state.

When the folding wing is converted from the folding state to the unfolding state (i.e. from the folding position close to the fuselage to the outer side to the unfolding state), firstly, the folding wing is rotated outwards to the direction approximately consistent with the guide rod 11 through the universal joint 13, then, the folding wing rotates together with the guide rod 11, the limiting column 111 enters the axial groove 141 along the circumferential groove 142, then, the folding wing is pushed towards the direction of the fuselage, and the folding wing moves towards the fuselage together with the guide rod 11 until the limiting column 111 moves to the end part, far away from the circumferential groove 142, of the axial groove 141.

It is to be understood that the limiting structure between the guide sleeve 14 and the guide rod 11 is not limited to the above-described form, and for example, a limiting groove may be provided on the outer surface of the guide rod 11, a limiting post which protrudes inward and is movable in the limiting groove may be provided on the inner side of the guide sleeve 14, and in addition, other structures which can axially and circumferentially limit the guide rod 11 may be provided.

In addition, the solution described above is to pull out the folding wing and the guide rod 11 in the direction away from the fuselage, and then rotate the wing and the guide rod by a certain angle. The scheme of this application also does not exclude folding wing and guide bar 11 rotate certain angle earlier after, again along the direction of keeping away from the fuselage pull out, under this condition, can set up the tip of keeping away from the first end of guide bar 11 at axial groove 141 with circumferential groove 142.

In one embodiment, to facilitate the positioning of the position-limiting post 111 on the guide rod 11, a sleeve 112 is sleeved on the guide rod 11, and the position-limiting post 111 is disposed on the sleeve 112. Of course, the limiting column 111 may be directly fixed to the guide rod 11 by welding.

According to another aspect of the present application, there is also provided a rotary joint arrangement 1, as shown in fig. 3 and 4, said rotary joint arrangement 1 comprising a universal joint 13 and a connection assembly as described above.

The first connection end 131 of the universal joint 13 is connected with the first end of the guide rod 11 in the connection component, and the second connection end 132 is used for being connected with the folding wing, and the folding wing can rotate to the folding state through the universal joint 13.

In one embodiment, as shown in fig. 3, the rotating connection device 1 further includes a rotating part 12, the second connection end 132 of the universal joint 13 is connected to the rotating part 12, and the rotating part 12 is used for connecting with a folding wing of the drone.

The universal joint 13 used in the rotary joint 1 may have various structural forms, and the present application is not limited thereto.

Optionally, the universal joint 13 is provided as a hollow structure through which wires can pass, so that the wires of the drone can be conveniently arranged.

Optionally, an intermediate connection portion 133 is disposed between the first connection end 131 and the second connection end 132 of the universal joint 13, and the first connection end 131 and the second connection end 132 are respectively hinged to the intermediate connection portion 133; wherein a channel for passing the wire is formed between the first connection end 131 and the intermediate connection portion 133 and/or between the second connection end 132 and the intermediate connection portion 133.

In one embodiment, the specific structure of the universal joint 13 is as shown in fig. 1 and fig. 2, the first connection end 131 of the universal joint 13 includes two first connection lugs 1311 protruding toward the intermediate connection portion 133, and the intermediate connection portion 133 includes two third connection lugs 1331 protruding toward the first connection end 131; wherein, each first engaging lug 1311 is rotatably connected to one third engaging lug 1331 through a rotating shaft, and a first channel M capable of passing through a wire is formed between the two first engaging lugs 1311.

Alternatively, each first coupling lug 1311 and the corresponding third coupling lug 1331 are rotatably connected through an independent rotating shaft, so that the problem that two first coupling lugs 1311 are connected through a common rotating shaft to interfere with the wire passing through the first passage M can be avoided.

The second connecting end 132 includes two second engaging lugs 1321 protruding toward the intermediate connecting portion 133, and the intermediate connecting portion 133 includes two fourth engaging lugs 1332 protruding toward the second connecting end 132; each second engaging lug 1321 corresponds to one fourth engaging lug 1332 and is rotatably connected through the rotating shaft, and a second channel N through which a wire can pass is formed between the two second engaging lugs 1321.

Optionally, each second engaging lug 1321 and the corresponding fourth engaging lug 1332 are rotatably connected through an independent rotating shaft, so that the problem that two second engaging lugs 1321 are connected through a common rotating shaft to easily cause interference with a wire passing through the second channel N can be avoided.

In this embodiment, the first connection end 131 of the universal joint 13 is provided with a projection (or flange) which projects in the radial direction and has a mounting hole, and the first connection end 131 can be connected to the projection (or flange) which projects in the radial direction on the guide bar 11 by a bolt passing through the projection. Similarly, the second connection end 132 of the universal joint 13 is provided with a protrusion (or flange) protruding in the radial direction and having a mounting hole, and the second connection end 132 is connected to the rotating part 12 or the folding wing by a bolt passing through the protrusion.

According to a further aspect of the present application, there is also provided a drone, as shown in fig. 5-8, comprising a fuselage 100, folding wings 200 and a rotating connection device 1 as described above;

in the rotary connecting device 1, the guide sleeve 14 of the connecting assembly is fixed on the fuselage 100 of the unmanned aerial vehicle, and the second connecting end 132 of the universal joint 13 is connected to the folding wing 200.

In one embodiment, the rotating connection device 1 further includes a rotating portion 12, the rotating portion 12 is connected to the folding wing 200, and the second connection end 132 of the universal joint 13 is connected to the rotating portion 12.

The unmanned aerial vehicle further comprises a locking assembly, and the locking assembly is used for connecting and fixing the folding wings 200 to the fuselage 100 when the folding wings are in an unfolding state during flying.

The locking components, such as the first locking component 2 and the second locking component 3 shown in fig. 7 and 8, are respectively disposed on two opposite sides of the rotating connecting device 1. Each locking assembly includes a first connection portion connected to the fuselage 200, a second connection portion connected to the folding wing 200, and a locking member for locking the first connection portion and the second connection portion together.

The specific structure of the locking assembly is not limited herein as long as the foldable wing 200 can be fixedly connected to the fuselage 100.

In some embodiments, a rib plate is further disposed between the foldable wing 200 and the fuselage 100, the shape of the rib plate is consistent with the cross-sectional shape of the connection between the foldable wing 200 and the fuselage 100, and the rib plate is used for connecting the wing flow lines, and the rotary connection device 1, the first locking assembly 2 and the second locking assembly 3 can be connected to the rib plate.

Specifically, as shown in the embodiment of fig. 5 to 8, a first rib 101 and a second rib 102 are fixed relative to the body 100, and the parts of the rotating connecting device 1, the first locking member 2 and the second locking member 3 fixed relative to the body 100 can be connected with the first rib 101 and the second rib 102. A third rib 201 and a fourth rib 202 are fixed relative to the folding wing 200, and the parts of the rotary connecting device 1, the first locking component 2 and the second locking component 3 fixed relative to the folding wing 200 can be connected with the third rib 201 and the fourth rib 202.

The above description is only exemplary of the present application and should not be taken as limiting the present application, as any modifications, equivalents and the like that are within the spirit and principle of the present application should be included in the scope of the present application.

Claims

1. A coupling assembling of unmanned aerial vehicle wing, its characterized in that, coupling assembling includes:

the guide rod is inserted into the guide sleeve, can axially move relative to the guide sleeve and can rotate relative to the guide sleeve, and a first end of the guide rod, extending out of the guide sleeve, is arranged to be rotatably connected with a folding wing of the unmanned aerial vehicle;

2. The connecting assembly according to claim 1, wherein the limiting structure comprises a limiting groove arranged on the guide sleeve and a limiting post arranged on the outer surface of the guide rod in a protruding manner, and the limiting post is arranged to move along the limiting groove;

3. The connection assembly according to claim 2, wherein the circumferential groove is provided at an end of the axial groove proximate to the first end of the guide rod.

4. The connecting assembly of claim 2, wherein the guide rod is sleeved with a shaft sleeve, and the limiting column is arranged on the shaft sleeve.

5. A swivel connection, characterized in that it comprises a universal joint and a connecting assembly according to any one of claims 1-4;

6. The rotating connection as claimed in claim 5, further comprising a rotating portion to which the second connection end is connected, the rotating portion being configured to connect with the folding wing.

7. The rotating connection device according to claim 5, wherein the universal joint is provided as a hollow structure through which a wire can pass.

8. The rotating connecting device according to claim 5, wherein an intermediate connecting portion is arranged between the first connecting end and the second connecting end of the universal joint, and the first connecting end and the second connecting end are respectively hinged with the intermediate connecting portion;

9. The swivel connection apparatus according to claim 8, wherein the first connection end comprises two first connection lugs projecting towards the intermediate connection portion, the intermediate connection portion comprises two third connection lugs projecting towards the first connection end; each first connecting lug corresponds to one third connecting lug respectively and is rotatably connected through a rotating shaft, and a first channel capable of passing through a wire is formed between connecting structures correspondingly connected with the two first connecting lugs and the third connecting lug respectively;

10. An unmanned aerial vehicle comprising a fuselage, folding wings and a rotating connection according to any one of claims 5 to 9;