CN213735512U

CN213735512U - Detachable wing of unmanned aerial vehicle

Info

Publication number: CN213735512U
Application number: CN202022521502.2U
Authority: CN
Inventors: 赵阳
Original assignee: Zhengzhou Mingdao Network Technology Co ltd
Current assignee: Zhengzhou Mingdao Network Technology Co ltd
Priority date: 2020-11-04
Filing date: 2020-11-04
Publication date: 2021-07-20
Anticipated expiration: 2030-11-04

Abstract

The utility model provides a dismantled and assembled wing of unmanned aerial vehicle, including the unmanned aerial vehicle body, set up in four stretching arms of unmanned aerial vehicle body four corners department, set up the driver on stretching arm, set up the wing on the driver, connect through installation mechanism between wing and the driver, installation mechanism is including setting up fixed cover on the driver, set up the mounting groove on fixed cover, slide the top pearl in the mounting groove, the cover is located the fixed slip lantern ring that is used for to a pearl rigidity on the fixed cover of putting, set up in slip lantern ring inner wall and in a pearl complex recess, set up in slip lantern ring below and the cover and locate the elastic component on fixed cover, set up on the wing and be located the installation cover in the fixed cover, set up on the installation with a pearl complex spacing groove. The utility model discloses an installation mechanism can realize the installation or the dismantlement of wing to reduce the occupation space of unmanned aerial vehicle body on the one hand, on the other hand can avoid the unmanned aerial vehicle body to cause the damage to the wing when carrying.

Description

Detachable wing of unmanned aerial vehicle

Technical Field

The utility model relates to an unmanned air vehicle technique field especially relates to a dismantled and assembled wing of unmanned aerial vehicle.

Background

An unmanned aircraft, referred to as "drone", is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device, or is operated autonomously, either completely or intermittently, by an onboard computer. The unmanned aerial vehicle is also divided into military use and civil use, wherein the military unmanned aerial vehicle is more excellent than the civil use in specification and manufacture, and the civil unmanned aerial vehicle is generally used for entertainment, commercial use and the like.

At present, in the actual conditions, in military activities, the user of service generally can use unmanned aerial vehicle to reconnaissance various equipment, but current unmanned aerial vehicle generally is that the shared space of wing is bigger, and consequently the user of service is when carrying unmanned aerial vehicle, and unmanned aerial vehicle can occupy a large amount of spaces, and further removal that will influence the user of service, consequently, the dismantled and assembled wing of an unmanned aerial vehicle comes the solution problem of proposing.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a dismantled and assembled wing of unmanned aerial vehicle aims at solving the problem that the background art provided.

In order to achieve the purpose, the detachable wing of the unmanned aerial vehicle comprises an unmanned aerial vehicle body, four stretching arms arranged at four corners of the unmanned aerial vehicle body, a driver arranged on the stretching arms, and a wing arranged on the driver, connect through installation mechanism between wing and the driver, installation mechanism including set up fixed cover on the driver, set up in fixed mounting groove on the cover, slide in fixed inslot top pearl, cover are located fixed sheathe in be used for to the fixed slip lantern ring of a pearl rigidity, set up in slip lantern ring inner wall just in a pearl complex recess, set up in slip lantern ring below and cover are located fixed cover on the elastic component, set up in on the wing and be located fixed cover installation cover, set up in on the installation with a pearl complex spacing groove, set up in on the driver and the pivot of being connected with the installation cover.

Preferably, a limiting ring for limiting the position of the sliding collar is arranged above the sliding collar.

Preferably, the elastic member is a compression spring.

Preferably, the upper end of the rotating shaft is rectangular, and a rectangular groove matched with the upper end of the rotating shaft is formed in the middle of the mounting sleeve.

Preferably, the first holding tank that is used for placing the arm that stretches is all offered to both sides around the unmanned aerial vehicle body, the one end of first holding tank is provided with the standing groove that is used for depositing the driver.

Preferably, the downside of first holding tank is provided with the circular arc groove that is used for drawing out the arm that stretches out on being located the unmanned aerial vehicle body.

Preferably, the left and right sides of unmanned aerial vehicle body all is provided with the second holding tank that is used for depositing the wing.

The utility model has the advantages that:

1. the utility model discloses, can realize the installation or the dismantlement of wing through installation mechanism to reduce the occupation space of unmanned aerial vehicle body on the one hand, on the other hand can avoid the unmanned aerial vehicle body to cause the damage to the wing when carrying.

2. The utility model discloses, can be convenient for deposit driver and wing through the cooperation of first holding tank and standing groove, reduce the occupation space of unmanned aerial vehicle body, conveniently carry.

Drawings

FIG. 1 is a schematic view of the structure of the present invention;

FIG. 2 is a schematic cross-sectional view of the fixing sleeve structure of the present invention;

FIG. 3 is a schematic top view of the structure of FIG. 1 in accordance with the present invention;

FIG. 4 is a schematic top cross-sectional view of the structure of FIG. 1 in accordance with the present invention;

fig. 5 is a schematic side view of the structure of fig. 1 according to the present invention.

In the figure: 1. an unmanned aerial vehicle body; 2. stretching the arm; 3. a driver; 4. an airfoil; 5. fixing a sleeve; 6. a slip collar; 7. a groove; 8. an elastic member; 9. mounting grooves; 10. a top bead; 11. a rotating shaft; 12. installing a sleeve; 13. a limiting groove; 14. a first accommodating groove; 15. a placement groove; 16. an arc groove; 17. and a second accommodating groove.

Detailed Description

The technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention.

In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.

The utility model discloses a specific embodiment of dismantled and assembled wing of unmanned aerial vehicle, as shown in fig. 1 to 5, including unmanned aerial vehicle body 1, set up in four stretching arm 2 of unmanned aerial vehicle body 1 four corners department, set up in stretching arm 2 on driver 3, set up wing 4 on driver 3, connect through installation mechanism between wing 4 and the driver 3, installation mechanism is including setting up fixed cover 5 on driver 3, set up mounting groove 9 on fixed cover 5, the pearl 10 that slides in mounting groove 9, the slip lantern ring 6 that is used for fixing the pearl 10 position to the pearl 10 on the cover is located to the fixed cover 5, set up in the slip lantern ring 6 inner wall and in pearl 10 complex recess 7, set up in the elastic component 8 that the slip lantern ring 6 below and the cover is located fixed cover 5, set up 12 on wing 4 and be located fixed cover 5, set up on mounting 12 with pearl 10 complex spacing groove 13, Set up pivot 11 on driver 3 and be connected with installation cover 12, installation mechanism can realize the installation or the dismantlement of wing 4 to reduce unmanned aerial vehicle body 1's occupation space on the one hand, on the other hand can avoid unmanned aerial vehicle body 1 to cause the damage to wing 4 when carrying.

In this embodiment, a position limiting ring for limiting the position of the sliding collar 6 is arranged above the sliding collar 6.

In this embodiment, the elastic member 8 is a compression spring.

In this embodiment, the upper end of the rotating shaft 11 is rectangular, and the middle part of the mounting sleeve 12 is provided with a rectangular groove adapted to the upper end of the rotating shaft 11, so that the rotating shaft 11 can drive the wing 4 on the mounting sleeve 12 to rotate.

In this embodiment, first holding tank 14 that is used for placing stretch arm 2 is all offered to both sides around unmanned aerial vehicle body 1, and the one end of first holding tank 14 is provided with standing groove 15 that is used for depositing driver 3, and first holding tank 14 can be convenient for deposit driver 3 and wing 4 with the cooperation of standing groove 15, reduces unmanned aerial vehicle body 1's occupation space, conveniently carries.

In this embodiment, the downside of first holding tank 14 is provided with the circular arc groove 16 that is used for drawing out on unmanned aerial vehicle body 1 and stretches out arm 2.

In this embodiment, the left and right sides of unmanned aerial vehicle body 1 all is provided with the second holding tank 17 that is used for depositing wing 4.

The utility model discloses the theory of operation:

when dismantling, remove the slip lantern ring 6 earlier, the slip lantern ring 6 removes and makes the compression of 8 atresss of elastic component, and recess 7 on the slip lantern ring 6 corresponds with a pearl 10, then extracts wing 4, and wing 4 drives installation cover 12 and removes, and installation cover 12 removes and makes a pearl 10 atress removal and spacing groove 13 separation enter into recess 7 in to dismantle wing 4, reduce the occupation space of unmanned aerial vehicle body 1, portable.

The above, only be the concrete implementation of the preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art is in the technical scope of the present invention, according to the technical solution of the present invention and the utility model, the concept of which is equivalent to replace or change, should be covered within the protection scope of the present invention.

Claims

1. The utility model provides a dismantled and assembled wing of unmanned aerial vehicle, includes unmanned aerial vehicle body (1), set up in four of unmanned aerial vehicle body (1) four corners department stretch out arm (2), set up in stretch out driver (3) on arm (2), set up in wing (4) on driver (3), its characterized in that: the wing (4) and the driver (3) are connected through an installing mechanism, the installing mechanism comprises a fixed sleeve (5) arranged on the driver (3), an installing groove (9) arranged on the fixed sleeve (5), a top bead (10) sliding in the installing groove (9), a sliding sleeve ring (6) sleeved on the fixed sleeve (5) and used for fixing the position of the top bead (10), and a groove (7) arranged on the inner wall of the sliding sleeve ring (6) and matched with the top bead (10), set up in slip lantern ring (6) below and cover elastic component (8) on fixed cover (5), set up in on wing (4) and be located installation cover (12) of fixed cover (5), set up in on installation cover (12) with top pearl (10) complex spacing groove (13), set up in pivot (11) that just are connected with installation cover (12) on driver (3).

2. The detachable unmanned aerial vehicle wing of claim 1, wherein: and a limiting ring used for limiting the position of the sliding sleeve ring (6) is arranged above the sliding sleeve ring (6).

3. The detachable unmanned aerial vehicle wing of claim 1, wherein: the elastic piece (8) is a compression spring.

4. The detachable unmanned aerial vehicle wing of claim 1, wherein: the upper end of the rotating shaft (11) is rectangular, and a rectangular groove matched with the upper end of the rotating shaft (11) is formed in the middle of the mounting sleeve (12).

5. The detachable unmanned aerial vehicle wing of claim 1, wherein: first holding tank (14) that are used for placing stretch arm (2) are all offered to both sides around unmanned aerial vehicle body (1), the one end of first holding tank (14) is provided with standing groove (15) that are used for depositing driver (3).

6. The detachable unmanned aerial vehicle wing of claim 5, wherein: the downside of first holding tank (14) is provided with and is located arc groove (16) that are used for stretching out on unmanned aerial vehicle body (1) and stretch arm (2).

7. The detachable unmanned aerial vehicle wing of claim 1, wherein: the left and right sides of unmanned aerial vehicle body (1) all is provided with second holding tank (17) that are used for depositing wing (4).