CN209988104U

CN209988104U - Wing folding mechanism and unmanned aerial vehicle

Info

Publication number: CN209988104U
Application number: CN201920462610.1U
Authority: CN
Inventors: 刘森林; 孙建萍; 赵冬; 赵翔; 潘其伟; 李钢
Original assignee: Winter Sunshine (tianjin) Intelligent Technology Development Co Ltd
Current assignee: Winter Sunshine (tianjin) Intelligent Technology Development Co Ltd
Priority date: 2019-04-08
Filing date: 2019-04-08
Publication date: 2020-01-24
Anticipated expiration: 2029-04-08

Abstract

The utility model provides a wing folding mechanism and unmanned aerial vehicle, including wing seat, wing frame, fixed plate, quick-operation joint, mounting panel, perforation, mating joint, hinge and locking device, wing seat and wing frame are the inside hollow body, and wing seat first end face is fixed connection with the unmanned aerial vehicle main part, and the cross fixed plate that is equipped with of wing seat second end face, be equipped with the quick-operation joint on the fixed plate, the quick-operation joint is connected with power cord and signal line in the unmanned aerial vehicle main part; the wing frame is connected with the second end face of the wing seat through a hinge and a locking device, the hinge and the locking device are oppositely arranged at the edge of the second end face of the wing seat, a mounting plate is transversely arranged in the wing frame, a through hole is formed in the mounting plate, a power line and a signal line in the wing frame outwards penetrate through the through hole, a matched joint is arranged at the end part of the power line and the signal line, and the matched joint is connected with a quick joint. The utility model discloses structural design is ingenious, and the wing is folding simple, and fixed plate and mounting panel pull out for the pencil and insert and provide convenience, and packing and transportation stability are good.

Description

Wing folding mechanism and unmanned aerial vehicle

Technical Field

The utility model belongs to the technical field of unmanned aerial vehicle equipment, particularly, relate to a wing folding mechanism and unmanned aerial vehicle.

Background

A drone is an unmanned aircraft that is operated with a radio remote control device and self-contained program control, or is operated autonomously, either completely or intermittently, by an onboard computer. Drones tend to be more suitable for tasks that are too "fool, dirty, or dangerous" than are manned aircraft. It is different from common model airplane, and can be used for long-time remote control and flight, so that it can be extensively used in the fields of air transportation, reconnaissance, monitoring and communication, etc.

Unmanned aerial vehicle who uses among the prior art mainly divide into: unmanned fixed wing aircraft, unmanned VTOL aircraft, unmanned airship, unmanned helicopter, unmanned multi-rotor aircraft, unmanned paravane, etc. Because the fixed wing unmanned aerial vehicle has advantages such as wing stable in structure, mechanical strength height, its application effect has obtained the affirmation in market. However, as the fixed-wing unmanned aerial vehicle is applied more and more in various industries, the problem of inconvenient transportation in the aspects of packaging, transportation and the like is caused because the wing unfolding of the fixed-wing unmanned aerial vehicle cannot be effectively folded and disassembled, the wing is easily broken or deformed, and the reuse is influenced, so that the existing unmanned aerial vehicle needs to be improved and the wing is folded. And current fixed wing unmanned aerial vehicle wing end all sets up the screw, need wear to establish the pencil in the wing and realize being connected with the unmanned aerial vehicle main part, how to break off or connect the pencil also is a outstanding problem after the wing is folding.

Therefore, the technical defects in the prior art are technical problems to be solved by those skilled in the art.

SUMMERY OF THE UTILITY MODEL

A primary object of the utility model is to provide a wing folding mechanism and unmanned aerial vehicle aims at solving the technical problem who exists among the prior art.

In order to achieve the purpose, the utility model provides a wing folding mechanism, including wing seat, wing frame, fixed plate, quick-operation joint, mounting panel, perforation, mating joint, hinge and locking device, wing seat and wing frame are the inside hollow body, wing seat first end face and unmanned aerial vehicle main part fixed connection, the transversal fixed plate that is equipped with of wing seat second end face, be equipped with the quick-operation joint on the fixed plate, the quick-operation joint is connected with power cord and signal line in the unmanned aerial vehicle main part; the wing frame passes through the hinge with wing seat second terminal surface and is connected with locking device, hinge and locking device locate relatively the edge of wing seat second terminal surface, the transversal mounting panel that is equipped with in the wing frame, the perforation has been seted up on the mounting panel, power cord and signal line in the wing frame are outwards passed the perforation is equipped with the coupling at the tip, the coupling is connected with quick-operation joint.

Furthermore, the mounting plate is arranged on the inner side of the wing frame, and a mounting cavity of the quick connector and the mating connector is reserved between the fixing plate and the mounting plate.

Furthermore, the locking device comprises a locking plate, a screw hole and a first screw, the locking plate is fixed on the outer edge of the wing frame, the first screw is arranged on the locking plate, the screw hole is formed in the outer edge of the wing seat, and the first screw is matched with the screw hole.

Further, the wing frame further comprises a mounting mechanism, and the mounting plate is fixed in the wing frame through the mounting mechanism.

Further, installation mechanism includes installation piece and second screw, mounting panel edge integrated into one piece is equipped with the installation piece, the installation piece is mutually perpendicular with the mounting panel, the installation piece pass through the second screw with wing frame inner wall fixed connection.

The utility model also provides an unmanned aerial vehicle, use as above wing folding mechanism.

By applying the technical scheme of the utility model, the fixation and folding of the wing structure are realized between the wing seat and the wing frame through the hinge and the locking device, thereby facilitating the folding and storage of the wings of the unmanned aerial vehicle; the fixing plate is arranged on the wing seat and the mounting plate is arranged on the wing frame, the quick connector arranged on the fixing plate and the matched connector penetrating through the mounting plate can be plugged in and pulled out, the matched wing seat and the wing frame can be folded and stored conveniently, the quick connector is fixed on the fixing plate and has good stability, the matched connector penetrates through a through hole in the mounting plate, and the matched connector cannot move in the transportation process; and the fixed plate that sets up separates unmanned aerial vehicle main part battery and electron device in the wing frame, has blockked the heat exchange, prevents that the heat from using to cause the influence to electron device in the wing frame. The utility model discloses structural design is ingenious, and the wing is folding simple, and fixed plate and mounting panel pull out for the pencil and insert and provide convenience, and packing and transportation stability are good.

Drawings

The accompanying drawings, which form a part of the present application, are included to provide a further understanding 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 invention and not to limit the invention. In the drawings:

fig. 1 schematically shows a perspective view of an unmanned aerial vehicle to which the wing folding mechanism of the present invention is applied;

fig. 2 schematically shows a folding perspective view of an unmanned aerial vehicle to which the wing folding mechanism of the present invention is applied;

figure 3 schematically illustrates an enlarged view of a portion of figure 2 of the present invention;

wherein the figures include the following reference numerals:

1, a wing seat; 2, a wing frame; 3, fixing a plate; 4, a quick joint; 5, mounting a plate; 6, perforating; 7, a hinge; 8, locking devices; 801 locking plates; 802 screw holes; 803 a first screw; 9, mounting a mechanism; 901, installing a sheet; 902 second screw.

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 present invention will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.

It should be noted that the following detailed description is exemplary and is intended to provide further explanation of the disclosure. Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs.

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.

It should be noted that the terms "first," "second," and the like in the description and claims of this application and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used is interchangeable under appropriate circumstances such that the embodiments of the application described herein are, for example, capable of operation in sequences other than those illustrated or otherwise described herein.

Furthermore, the terms "comprises," "comprising," and any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed, but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.

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 rotated 90 degrees or at other orientations and the spatially relative descriptors used herein interpreted accordingly.

Referring to fig. 1 to 3, the utility model provides a wing folding mechanism, including wing seat 1, wing frame 2, fixed plate 3, quick-operation joint 4, mounting panel 5, perforation 6, mating joint (not seen in the figure), hinge 7 and locking device 8, wing seat 1 and wing frame 2 are inside hollow body, 1 first terminal surface of wing seat and unmanned aerial vehicle main part fixed connection specifically can adopt welding or bolted connection to realize wing seat 1 and unmanned aerial vehicle main part fixed connection, the transversal fixed plate 3 that is equipped with of 1 second terminal surface of wing seat, fixed plate 3 also can adopt welding or bolted connection mode and 1 inner wall fixed connection of wing seat, the preferred welding mode that adopts. The fixing plate 3 is provided with a quick connector 4, the quick connector 4 is connected with a power line and a signal line in the unmanned aerial vehicle body, and therefore electric power and control signals can be provided for a propeller motor and other electronic devices arranged on the re-wing. Wing seat 1 and wing frame 2 have constituted the major structure of unmanned aerial vehicle wing jointly, wing frame 2 passes through hinge 7 and locking device 8 with wing seat 1 second terminal surface and is connected, hinge 7 and locking device 8 are located relatively the edge of wing seat 1 second terminal surface, and is specific, and hinge 7's setting makes wing seat 1 and wing frame 2 when folding, and wing frame 2 uses hinge 7 to rotate folding as the axle, and wing seat 1 and wing frame 2 can not break away from completely, and through the cooperation of locking device 8 and hinge 7, wing seat 1 and wing frame 2 can the stable connection, guarantee the stability in the unmanned aerial vehicle use. The aircraft wing frame 2 is internally provided with a transverse mounting plate 5, the mounting plate 5 is provided with a through hole 6, the mounting plate 5 is also provided with a hollowed hole for reducing weight, a power line and a signal line in the aircraft wing frame 2 outwards penetrate through the through hole 6, and the end part of the power line and the signal line is provided with a matched joint, so that the matched joint cannot retreat into the aircraft wing frame 2 from the through hole 6, and the matched joint belongs to a free moving state and is connected with a quick joint 4. When the wing frame 2 rotates and folds relative to the wing seat 1, the paired joints are pulled out from the quick joint 4, so that a power line and a signal line connected with the paired joints cannot be pulled and disconnected, when the wing frame is required to be used, the paired joints are in butt joint with the quick joint 4, and the paired joints and the quick joint 4 are convenient to pull out and insert.

In order to facilitate the installation operations of the quick connector 4 and the counter connector, a certain operating space needs to be left between the wing frame 2 and the wing seat 1. The mounting panel 5 is located 2 inboards of wing frame, and is concrete, and the mounted position of mounting panel 5 sets up 2-3 centimetres apart from the outer end of wing frame 2, has formed and has left between fixed plate 3 and the mounting panel 5 quick-operation joint 4 and coupling's installation cavity. When the unmanned aerial vehicle wing is in a normal state, the matched joint is connected with the corresponding quick joint 4, namely the matched joint is inserted on the quick joint 4, and the quick joint 4 is fixed on the fixing plate 3, so that the installation cavity provides a placing space for the matched joint; when the wing is folded, the mating connector needs to be pulled out of the quick connector 4, so that the installation cavity provides an operating space for pulling and inserting.

In order to maintain the stability of the wing in normal use and facilitate the detachment and folding of the locking device 8, specifically, the locking device 8 in this embodiment includes a locking plate 801, a screw hole 802 and a first screw 803, the locking plate 801 is fixed on the outer edge of the wing frame 2, specifically, as shown in the figure, the locking plate 801 is disposed outward along the outer edge of the wing frame 2, one portion of the locking plate 801 is fixed to the wing frame 2 by welding, the other portion of the locking plate 801 is provided with the first screw 803, the first screw 803 is screwed by a handle at the upper end, the outer edge of the wing seat 1 is provided with the screw hole 802, and the first screw 803 is matched with the screw hole 802. The use process is as follows:

when the wing frame 2 and the wing seat 1 are in a detached state, the wing frame 2 rotates around the hinge 7, so that the wing frame 2 is in butt joint with the wing seat 1, the end of the locking plate 801 is positioned right above the screw hole 802, and the first screw 803 is screwed into the screw hole 802 manually, so that the stable installation of the wing frame 2 and the wing seat 1 is realized.

In this embodiment, further, a mounting mechanism 9 is further included, and the mounting plate 5 is fixed in the wing frame 2 by the mounting mechanism 9. Specifically, the mounting mechanism 9 includes a mounting piece 901 and a second screw 902, the edge of the mounting plate 5 is integrally formed with the mounting piece 901, the mounting piece 901 is perpendicular to the mounting plate 5, and the mounting piece 901 is fixedly connected to the inner wall of the wing frame 2 through the second screw 902. The edge of the mounting plate 5 is uniformly provided with the mounting pieces 901, so that the mounting requirements can be met.

The utility model discloses use wing folding mechanism as above, provide an unmanned aerial vehicle, as shown in the attached figure 1. Wing folding mechanism one end is connected with the unmanned aerial vehicle main part, and its other end is connected with the horn.

By applying the technical scheme of the utility model, the wing structure is folded between the wing seat and the wing frame through the hinge and the locking device, thereby facilitating the folding and the storage of the wings of the unmanned aerial vehicle; the quick connector is fixed on the fixing plate, so that the quick connector has good stability, the matched connector penetrates through a through hole in the mounting plate, and the matched connector cannot move in the transportation process; and the fixed plate and the mounting panel that set up separate unmanned aerial vehicle main part battery and electron device in the wing frame, have blockked the heat exchange, prevent that the heat from using to cause the influence to electron device in the wing frame. The utility model discloses structural design is ingenious, and the wing is folding simple, and fixed plate and mounting panel pull out for the pencil and insert and provide convenience, and packing and transportation stability are good.

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.

Claims

1. A wing folding mechanism which characterized in that: the unmanned aerial vehicle comprises a wing seat, a wing frame, a fixing plate, a quick connector, a mounting plate, a perforation, a matched joint, a hinge and a locking device, wherein the wing seat and the wing frame are both internally hollow tubes, a first end surface of the wing seat is fixedly connected with an unmanned aerial vehicle main body, the fixing plate is transversely arranged on a second end surface of the wing seat, the quick connector is arranged on the fixing plate, and the quick connector is connected with a power line and a signal line in the unmanned aerial vehicle main body; the wing frame passes through the hinge with wing seat second terminal surface and is connected with locking device, hinge and locking device locate relatively the edge of wing seat second terminal surface, the transversal mounting panel that is equipped with in the wing frame, the perforation has been seted up on the mounting panel, power cord and signal line in the wing frame are outwards passed the perforation is equipped with the coupling at the tip, the coupling is connected with quick-operation joint.

2. The wing-folding mechanism of claim 1, wherein: the mounting panel is located the wing frame is inboard, leave between fixed plate and the mounting panel quick-operation joint and mating connector's installation cavity.

3. The wing-folding mechanism of claim 2, wherein: the locking device comprises a locking plate, a screw hole and a first screw, the locking plate is fixed on the outer edge of the wing frame, the first screw is arranged on the locking plate, the screw hole is formed in the outer edge of the wing seat, and the first screw is matched with the screw hole.

4. The wing-folding mechanism of claim 3, wherein: still include installation mechanism, the mounting panel passes through installation mechanism to be fixed in the wing frame.

5. The wing-folding mechanism of claim 4, wherein: installation mechanism includes installation piece and second screw, mounting panel edge integrated into one piece is equipped with the installation piece, the installation piece is mutually perpendicular with the mounting panel, the installation piece pass through the second screw with wing frame inner wall fixed connection.

6. An unmanned aerial vehicle, its characterized in that: use of a wing-folding mechanism as claimed in any of claims 1 to 5.