CN212951090U

CN212951090U - Folding structure based on suspended fixed wing unmanned aerial vehicle

Info

Publication number: CN212951090U
Application number: CN202022098507.9U
Authority: CN
Inventors: 闫兆
Original assignee: Beijing Weitong Xinke Measurement And Control Technology Co ltd
Current assignee: Beijing Weitong Xinke Measurement And Control Technology Co ltd
Priority date: 2020-09-23
Filing date: 2020-09-23
Publication date: 2021-04-13
Anticipated expiration: 2030-09-23

Abstract

The utility model discloses a folding structure of unmanned aerial vehicle based on a vertical fixed wing, which comprises a main wing, the edge part of one end of the main wing is rotationally connected with an auxiliary wing, one side of the front surface and one side of the back surface of the main wing are rotationally connected with a rotating column, the middle part of one end of the rotating column is welded with a rotating plate, one end of the rotating plate is welded with an electric telescopic rod, the middle part of one end of the electric telescopic rod is sleeved with the ball, the utility model has scientific and reasonable structure and safe and convenient use, the folding between the main wing and the auxiliary wing is facilitated through the main wing, the auxiliary wing, the rotating column, the rotating plate, the electric telescopic rod, the ball and the positioning column, the folding difficulty between the main wing and the auxiliary wing is reduced, and meanwhile, the main wing and the auxiliary wing after being overturned can be supported, therefore, the phenomenon of shaking between the main wing and the auxiliary wing after the main wing and the auxiliary wing are overturned is prevented, and the connection between the main wing and the auxiliary wing is more stable.

Description

Folding structure based on suspended fixed wing unmanned aerial vehicle

Technical Field

The utility model relates to an unmanned air vehicle technique field specifically is a based on fixed wing unmanned aerial vehicle that hangs down receive and releases beta structure.

Background

Unmanned aerial vehicles, that is, unmanned planes, are mostly controlled by radio intelligent remote control equipment, and along with social development and technological progress, unmanned aerial vehicles are widely used in life of people;

therefore, Chinese patent discloses a folding structure for a laser-suspended fixed wing unmanned aerial vehicle, which is applied No. 201911234666.2, and is characterized in that a plurality of groups of strong springs are arranged between a main wing and an auxiliary wing, a steel wire rope is connected between the main wing and the auxiliary wing, and a winding shaft can be driven by a motor to rotate, so that the steel wire rope is wound, the strong springs are deformed, the auxiliary wing and the main wing are vertically arranged, the whole wing is conveniently folded, the whole area of the unmanned aerial vehicle is reduced, and the folding and storage are convenient;

however, the patent also has the following disadvantages that the auxiliary wing is reset by the strong spring, but after the strong spring is used for a long time, the strong spring is rusted and broken due to corrosion of water stain, so that the normal use of the strong spring is influenced, and the auxiliary wing cannot be reset.

SUMMERY OF THE UTILITY MODEL

The utility model provides a receive and release beta structure based on fixed wing unmanned aerial vehicle that hangs down, the device that can effectively solve and propose in the above-mentioned background art utilizes strong spring to reset to the auxiliary engine wing, but because strong spring is after long-time the use, strong spring leads to rusty cracked phenomenon because of the corruption of water stain to influenced strong spring's normal use, and then leaded to the problem that the auxiliary engine wing can't reset.

In order to achieve the above object, the utility model provides a following technical scheme: a folding structure based on a vertical fixed wing unmanned aerial vehicle comprises a main wing, wherein one end edge part of the main wing is rotatably connected with an auxiliary wing, a rotating column is rotatably connected to the front side and the back side of the main wing, a rotating plate is welded in the middle of one end of the rotating column, an electric telescopic rod is welded at one end of the rotating plate, a ball is sleeved in the middle of one end of the electric telescopic rod, a positioning column is fixedly connected to one side of the outer surface of the ball, and the input end of the electric telescopic rod is electrically connected with the output end of a commercial power;

the welding of auxiliary engine wing bottom middle part equidistance has manual telescopic link, the welding of manual telescopic link bottom middle part has the locating plate, locating plate top and auxiliary engine wing bottom are located the manual telescopic link surface and have cup jointed reset spring, locating plate top middle part is located two the round hole has been seted up between the manual telescopic link, round hole inner wall middle part sliding connection has the stand, stand surface top and bottom all weld the holding ring, stand top middle part bonds there is the shock pad, stand bottom middle part welding has the damper plate.

Preferably, the positioning column is connected with the auxiliary wing in a welding mode, and the electric telescopic rod is connected with the positioning column in a rotating mode through a ball.

Preferably, laminating each other between shock pad top and the auxiliary engine wing, it is spacing through two between stand and the locating plate the holding ring.

Preferably, the upright post is positioned inside the circular hole, and the outer diameter of the upright post is equal to the inner diameter of the circular hole.

The aircraft wing structure is characterized in that one side edge of the top end of the main wing is connected with a limiting plate, the limiting plate is welded with a connecting block in front and at the bottom of the back, the back of the connecting block corresponds to the position of the front edge of the main wing and is provided with a notch, and the middle of one end of the connecting block is connected with a screw through threads.

Preferably, the connecting block is positioned inside the notch, and the connecting block is fixedly connected with the main wing through a screw.

Compared with the prior art, the beneficial effects of the utility model are that: the utility model has the advantages of being scientific and reasonable in structure, convenience safe in utilization:

1. through the main wing, the auxiliary wing, the rotation post, the rotor plate, electric telescopic handle, ball and reference column, can be convenient for the folding between main wing and the auxiliary wing, reduced the folding degree of difficulty between main wing and the auxiliary wing, support between the main wing that can overturn simultaneously and the auxiliary wing to the phenomenon of rocking takes place between the main wing and the auxiliary wing after preventing to overturn, and then make and be connected more stable between main wing and the auxiliary wing.

2. Through manual telescopic link, reset spring, locating plate, stand, holding ring, shock pad, shock attenuation board and round hole, can be convenient for carry out the shock attenuation to the auxiliary engine wing, impact force when having reduced to connect between auxiliary engine wing and the plane to the auxiliary engine wing has been protected, the life of auxiliary engine wing has been increased.

3. Through limiting plate, notch, connecting block and screw, can be convenient for carry on spacingly to the angle that the auxiliary wing deflected, prevent that the angle of assisting the wing upset from exceeding ninety degrees to make between auxiliary wing and the plane perpendicular, and then be convenient for connect between auxiliary wing and the plane

Drawings

The accompanying drawings 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 is a schematic structural diagram of the present invention;

fig. 2 is a front view of the main wing of the present invention;

fig. 3 is a schematic view of the mounting structure of the positioning ring of the present invention;

FIG. 4 is a schematic view of the area A of FIG. 1 according to the present invention;

reference numbers in the figures: 1. a main wing; 2. an auxiliary wing; 3. rotating the column; 4. a rotating plate; 5. an electric telescopic rod; 6. a ball; 7. a positioning column; 8. a manual telescopic rod; 9. a return spring; 10. Positioning a plate; 11. a column; 12. a positioning ring; 13. a shock pad; 14. a damper plate; 15. A limiting plate; 16. a notch; 17. connecting blocks; 18. a screw; 19. a circular hole.

Detailed Description

The preferred embodiments of the present invention will be described in conjunction with the accompanying drawings, and it will be understood that they are presented herein only to illustrate and explain the present invention, and not to limit the present invention.

Example (b): as shown in fig. 1-4, the utility model provides a technical scheme, a receive and release beta structure based on fixed wing unmanned aerial vehicle hangs down, including main wing 1, main wing 1 one end edge portion rotates and is connected with auxiliary wing 2, main wing 1 front and back one side all rotates and is connected with rotation post 3, rotation post 3 one end middle part welding has rotor plate 4, rotor plate 4 one end welding has electric telescopic handle 5, electric telescopic handle 5 one end middle part has cup jointed ball 6, ball 6 surface one side fixedly connected with reference column 7, welding connection between reference column 7 and the auxiliary wing 2, electric telescopic handle 5 and reference column 7 rotate through ball 6 and connect, can be convenient for the regulation of electric telescopic handle 5 angle, the regulation degree of difficulty of electric telescopic handle 5 angle has been reduced, the input of electric telescopic handle 5 and the output electric connection of commercial power;

the middle part of the bottom end of the auxiliary wing 2 is equidistantly welded with a manual telescopic rod 8, the middle part of the bottom end of the manual telescopic rod 8 is welded with a positioning plate 10, the top end of the positioning plate 10 and the bottom end of the auxiliary wing 2 are positioned on the outer surface of the manual telescopic rod 8 and are sleeved with a reset spring 9, the middle part of the top end of the positioning plate 10 is positioned between the two manual telescopic rods 8 and is provided with a round hole 19, the upright post 11 is positioned inside the round hole 19, the outer diameter of the upright post 11 is equal to the inner diameter of the round hole 19, the upright post 11 can be conveniently limited, the position of the upright post 11 can be prevented from moving, the middle part of the inner wall of the round hole 19 is connected with the upright post 11 in a sliding mode, the top end and the bottom part of the outer surface of the upright post 11 are both welded with, the phenomenon that the position of the upright post 11 moves is prevented, and a damping plate 14 is welded in the middle of the bottom end of the upright post 11.

Limiting plate 15 is connected with on one side limit portion in 1 top of the main wing, limiting plate 15 openly has all welded connecting block 17 with the back bottom, connecting block 17 is located inside notch 16, through 18 fixed connection of screw between connecting block 17 and the main wing 1, the installation of connecting block 17 of can being convenient for, the installation degree of difficulty of connecting block 17 has been reduced, notch 16 has been seted up to connecting block 17 back correspondence main wing 1 openly limit portion position department, there is 18 screws in connecting block 17 one end middle part through threaded connection.

The utility model discloses a theory of operation and use flow: in the actual use process of the folding structure for folding and unfolding the fixed wing unmanned aerial vehicle based on the vertical lifting, a user puts the connecting block 17 of the limiting plate 15 into the notch 16 of the main wing 1, then rotates the screw 18, fixes the connecting block 17 and the main wing 1 by using the screw 18, fixes the limiting plate 15 when the connecting block 17 and the main wing 1 are fixed, can conveniently limit the deflection angle of the auxiliary wing 2, and prevents the overturning angle of the auxiliary wing 2 from exceeding ninety degrees, so that the auxiliary wing 2 is perpendicular to a plane, and further the auxiliary wing 2 is connected with the plane;

then the electric telescopic rod 5 is connected with a power supply and starts to operate, the electric telescopic rod 5 drives the ball 6 to rotate outside the positioning column 7 during operation, so that the auxiliary wing 2 is driven to rotate around the main wing 1, the phenomenon of blade rotation is synchronously generated at the other end of the electric telescopic rod 5 at the moment, the rotating plate 4 is driven to rotate when the other end of the electric telescopic rod 5 rotates, the rotating column 3 is driven to rotate inside the main wing 1 when the rotating plate 4 rotates, the folding between the main wing 1 and the auxiliary wing 2 can be facilitated, the folding difficulty between the main wing 1 and the auxiliary wing 2 is reduced, meanwhile, the overturned main wing 1 and auxiliary wing 2 can be supported, the phenomenon of shaking between the main wing 1 and the auxiliary wing 2 after the overturning is prevented, and the connection between the main wing 1 and the auxiliary wing 2 is more stable;

then connect between auxiliary wing 2 bottom and the plane, and auxiliary wing 2 bottom and the plane between connect the time drive damper plate 14 and remove, damper plate 14 removes the time drive stand 11 along round hole 19 at locating plate 10 inside removal, thereby make the holding ring 12 and the locating plate 10 laminating of stand 11 bottom, and drive locating plate 10 and remove, drive manual telescopic link 8 shrink when locating plate 10 removes, and drive reset spring 9 shrink when manual telescopic link 8 shrinks, thereby carry out preliminary shock attenuation to auxiliary wing 2, at this moment, the shock pad 13 on second holding ring 12 top laminates with auxiliary wing 2 bottom, and make the shock pad 13 shrink, thereby can be convenient for carry out secondary shock attenuation to auxiliary wing 2, the impact force when having reduced and connecting between auxiliary wing 2 and the plane, thereby auxiliary wing 2 has been protected, auxiliary wing 2's life has been increased.

Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described in the foregoing embodiments, or equivalents may be substituted for elements thereof. 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. The utility model provides a receive and release beta structure based on fixed wing unmanned aerial vehicle hangs down, includes main wing (1), its characterized in that: the aircraft is characterized in that the edge of one end of the main wing (1) is rotatably connected with an auxiliary wing (2), the front side and one side of the back side of the main wing (1) are rotatably connected with a rotating column (3), the middle of one end of the rotating column (3) is welded with a rotating plate (4), one end of the rotating plate (4) is welded with an electric telescopic rod (5), the middle of one end of the electric telescopic rod (5) is sleeved with a ball (6), one side of the outer surface of the ball (6) is fixedly connected with a positioning column (7), and the input end of the electric telescopic rod (5) is electrically connected with the;

assist wing (2) bottom middle part equidistance welding to have manual telescopic link (8), the welding of manual telescopic link (8) bottom middle part has locating plate (10), locating plate (10) top and assistance wing (2) bottom are located manual telescopic link (8) surface and have cup jointed reset spring (9), locating plate (10) top middle part is located two round hole (19) have been seted up between manual telescopic link (8), round hole (19) inner wall middle part sliding connection has stand (11), stand (11) surface top and bottom all weld holding ring (12), stand (11) top middle part bonds has shock pad (13), stand (11) bottom middle part welding has shock attenuation board (14).

2. The unmanned aerial vehicle folding structure based on the vertical fixed wing is characterized in that the positioning column (7) is connected with the auxiliary wing (2) in a welding mode, and the electric telescopic rod (5) is rotatably connected with the positioning column (7) through a ball (6).

3. The folding structure of the unmanned aerial vehicle based on the fixed wing that hangs down receive and releases according to claim 1, characterized in that, laminating each other between shock pad (13) top and the auxiliary wing (2), spacing through two holding rings (12) between stand (11) and locating plate (10).

4. The folding structure for unmanned aerial vehicle based on vertical fixed wing as claimed in claim 1, wherein the upright column (11) is located inside the circular hole (19), and the outer diameter of the upright column (11) is equal to the inner diameter of the circular hole (19).

5. The folding structure that receive and releases based on fixed wing unmanned aerial vehicle hangs down according to claim 1, characterized in that, a limit plate (15) is connected with to a side limit portion in host computer wing (1) top, connecting block (17) have all been welded to limit plate (15) front and back bottom, notch (16) have been seted up to connecting block (17) back corresponding host computer wing (1) front limit portion position department, there is screw (18) at connecting block (17) one end middle part through threaded connection.

6. The folding structure of the unmanned aerial vehicle based on the vertical fixed wing is characterized in that the connecting block (17) is positioned inside the notch (16), and the connecting block (17) is fixedly connected with the main wing (1) through a screw (18).