CN215554085U

CN215554085U - Airfoil linkage anti-lock structure device about unmanned aerial vehicle

Info

Publication number: CN215554085U
Application number: CN202122160843.6U
Authority: CN
Inventors: 刘晨晖; 金�一; 李新
Original assignee: Jiangxi Tongyi Uav Technology Co ltd
Current assignee: Jiangxi Tongyi Uav Technology Co ltd
Priority date: 2021-09-08
Filing date: 2021-09-08
Publication date: 2022-01-18
Anticipated expiration: 2031-09-08

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, and particularly discloses a left and right wing surface linkage anti-lock structure device of an unmanned aerial vehicle, which comprises a middle plate and fixing plates arranged at the left and right ends of the middle plate, wherein the centers of the left and right sides of the middle plate are respectively provided with a side groove, and the centers of the inner walls of the two side grooves, which are close to each other, are both provided with transversely arranged adjusting grooves, the centers of the inner walls of the two adjusting grooves, which are close to each other, are both connected with connecting rods connected with the wings through electric telescopic rods, and the one end that both sides are close to each other all is connected with the limiting plate around two connecting rods, and buffer spring's design, collocation buffer board and limiting plate use can restrict the removal of connecting rod, thereby prevent that connecting rod and intermediate lamella and fixed plate from taking place the block and influencing the normal adjustment to unmanned aerial vehicle wing gesture, and then avoid causing the influence to unmanned aerial vehicle's normal use.

Description

Airfoil linkage anti-lock structure device about unmanned aerial vehicle

Technical Field

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a linkage anti-lock structure device for left and right wing surfaces of an unmanned aerial vehicle.

Background

An unmanned aircraft, abbreviated as drone and in english as UAV, is an unmanned aircraft that is operated by means of a radio remote control device and a self-contained program control device, or is operated autonomously, either completely or intermittently, by an onboard computer. When using, the wings of the existing unmanned aerial vehicle need to be linked with each other, so that the linkage structure for linking the left wing and the right wing is arranged in the unmanned aerial vehicle, the linkage structure is easy to block due to the influence of various factors when in use, and the adjustment of the wing posture is influenced, so that the influence is caused to the normal use of the unmanned aerial vehicle, and therefore, the unmanned aerial vehicle left and right wing linkage anti-lock structure device is provided.

SUMMERY OF THE UTILITY MODEL

Aiming at the defects of the prior art, the utility model provides the left and right wing surface linkage anti-lock structure device of the unmanned aerial vehicle, which has the advantages of difficult locking and the like, and solves the problem that the existing linkage structure is easy to be locked when in use.

The utility model discloses an unmanned aerial vehicle left and right wing surface linkage anti-lock structure device, which comprises a middle plate and fixing plates arranged at the left and right ends of the middle plate, wherein side grooves are formed in the centers of the left and right sides of the middle plate, adjusting grooves which are transversely arranged are formed in the centers of the inner walls of the two side grooves, which are close to one side, respectively, the centers of the inner walls of the two adjusting grooves, which are close to one side, are connected with connecting rods connected with wings through electric telescopic rods, limiting plates are connected to the ends, close to the front and rear sides, of the two connecting rods, respectively, and buffer plates corresponding to the limiting plates are connected to the front and rear ends, close to one side, of the inner walls of the two fixing plates, respectively, through buffer springs.

Through the design of the technical scheme, buffer spring's design, collocation buffer board and limiting plate use, can restrict the removal of connecting rod, thereby prevent that connecting rod and intermediate lamella and fixed plate from taking place the block and influencing the normal adjustment to unmanned aerial vehicle wing gesture, and then avoid causing the influence to unmanned aerial vehicle's normal use.

As a further improvement of the utility model, a built-in groove is formed in the center of the inner part of the middle plate, the center of the inner part of the built-in groove is connected with a control center through a fixed block, the control center can control the electric telescopic rods and is electrically connected with the two electric telescopic rods respectively, and the control center is in signal connection with a remote controller of the unmanned aerial vehicle.

Through the design of the technical scheme, the control center can control the stretching of the electric telescopic rod, so that the posture of the wings of the unmanned aerial vehicle can be adjusted through the connecting rod, and the normal use of the unmanned aerial vehicle is guaranteed.

As a further improvement of the utility model, the centers of the sides, far away from each other, of the two connecting rods are rotatably connected with connecting plates connected with wings of the unmanned aerial vehicle through rotating blocks, and the upper and lower ends, far away from each other, of the two connecting plates are provided with connecting through holes transversely penetrating through the connecting plates.

As a further improvement of the utility model, four corners on the left side and the right side of the middle plate are respectively provided with a groove, and the mutually adjacent sides of the inner walls of the left group of grooves and the right group of grooves are respectively connected with a clamping rod with an L-shaped front view through a torsion spring rotating shaft.

As a further improvement of the utility model, the ends of the left and right clamping rods far away from each other are clamped with the fixed plates, and the four corners of the two fixed plates far away from each other are respectively provided with connecting bolts connected with the left and right sides of the middle plate.

Through the design of the technical scheme, the clamping rod can enhance the connection between the fixed plate and the middle plate, so that the connecting bolt is prevented from losing efficacy under the vibration of the unmanned aerial vehicle operation and influencing the normal connection of the fixed plate and the middle plate, and the influence on the normal use of the whole device is avoided.

Compared with the prior art, the utility model has the following beneficial effects:

according to the design of the buffer spring, the buffer plate and the limiting plate are matched for use, the movement of the connecting rod can be limited, the connecting rod is prevented from being clamped with the middle plate and the fixing plate, so that the normal adjustment of the wing posture of the unmanned aerial vehicle is influenced, the influence on the normal use of the unmanned aerial vehicle is avoided, the control center can control the stretching of the electric telescopic rod, the wing posture of the unmanned aerial vehicle can be adjusted through the connecting rod, and the normal use of the unmanned aerial vehicle is guaranteed.

Drawings

The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the application and together with the description serve to explain the application and not to limit the application. In the drawings:

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

FIG. 2 is a side sectional view of the intermediate plate according to the present invention;

FIG. 3 is an enlarged view of the structure at A in FIG. 1 according to the present invention.

In the figure: 1. a connecting plate; 2. a buffer spring; 3. an electric telescopic rod; 4. a fixed block; 5. a control hub; 6. a limiting plate; 7. a clamping rod; 8. rotating the block; 9. a connecting rod; 10. a side groove; 11. adjusting the groove; 12. a middle plate; 13. a connecting bolt; 14. and (7) fixing the plate.

Detailed Description

In the following description, for purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of the various embodiments of the utility model. It should be understood, however, that these physical details should not be construed as limiting the utility model. That is, in some embodiments of the utility model, such physical details are not necessary. In addition, some conventional structures and components are shown in simplified schematic form in the drawings.

In addition, the descriptions related to the first, the second, etc. in the present invention are only used for description purposes, do not particularly refer to an order or sequence, and do not limit the present invention, but only distinguish components or operations described in the same technical terms, and are not understood to indicate or imply relative importance or implicitly indicate the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In addition, technical solutions between various embodiments may be combined with each other, but must be realized by a person skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination should not be considered to exist, and is not within the protection scope of the present invention.

Referring to fig. 1, the utility model relates to an unmanned aerial vehicle left and right wing surface linkage anti-lock structure device, which comprises a middle plate 12 and fixing plates 14 arranged at the left and right ends of the middle plate 12, side grooves 10 are formed in the centers of the left and right sides of the middle plate 12, transversely-arranged adjusting grooves 11 are formed in the centers of the inner walls of the two side grooves 10 close to one side, connecting rods 9 connected with wings are connected to the centers of the inner walls of the two adjusting grooves 11 close to one side through electric telescopic rods 3, limiting plates 6 are connected to the ends of the two connecting rods 9 close to the front and back sides, buffer plates corresponding to the limiting plates 6 are connected to the front and back ends of the inner walls of the two fixing plates 14 close to one side through buffer springs 2, the buffer plates are designed by matching with the limiting plates 6, the buffer plates can limit the movement of the connecting rods 9, and the middle plate 12 and the fixing plates 14 are prevented from being clamped, so that the influence on the wing posture of the unmanned aerial vehicle is caused by the clamping of the connecting rods 9 with the middle plate 12 and the fixing plates 14 Normal adjustment, and then avoid causing the influence to unmanned aerial vehicle's normal use, built-in recess has been seted up to the inside central authorities of intermediate lamella 12, the inside central authorities of built-in recess are connected with through fixed block 4 can control electric telescopic handle 3 and respectively with two electric telescopic handle 3 electric connection's control maincenter 5, and control maincenter 5 and unmanned aerial vehicle's remote controller signal connection, control maincenter 5 can control electric telescopic handle 3's flexible, thereby can adjust the gesture of unmanned aerial vehicle wing through connecting rod 9, unmanned aerial vehicle's normal use has been guaranteed, two connecting rod 9 keep away from the central authorities of one side each other and all rotate through turning block 8 and be connected with connecting plate 1 that is connected with the unmanned aerial vehicle wing, and two connecting plate 1 keep away from the upper and lower both ends of one side each other and all set up the connect the via hole that transversely runs through connecting plate 1.

Please refer to fig. 1, fig. 2 and fig. 3, four corners of the left and right sides of the middle plate 12 are all provided with grooves, one side of the left and right inner walls of the two groups of grooves close to each other is connected with a clamping rod 7 with an L-shaped front view through a torsion spring rotating shaft, one end of the left and right clamping rods 7 away from each other is clamped with a fixing plate 14, and four corners of one side of the two fixing plates 14 away from each other are respectively provided with a connecting bolt 13 connected with the left and right sides of the middle plate 12, the clamping rod 7 can enhance the connection between the fixing plate 14 and the middle plate 12, and the connecting bolt 13 is prevented from losing efficacy under the vibration of the unmanned aerial vehicle operation to affect the normal connection of the fixing plate 14 and the middle plate 12, thereby avoiding affecting the normal use of the whole device.

In the use of the utility model: the control center 5 is controlled through a remote controller of the unmanned aerial vehicle, so that the electric telescopic rod 3 can stretch according to instructions, and the connecting rod 9 can drive the connecting plate 1 to stretch under the action of the electric telescopic rod 3, so that the wing posture of the unmanned aerial vehicle can be adjusted, the flight posture of the unmanned aerial vehicle can be adjusted, and the normal use of the unmanned aerial vehicle is ensured;

connecting rod 9 is when removing, and limiting plate 6 can extrude buffer spring 2 and buffer board to the removal to connecting rod 9 limits, reduces connecting rod 9 and intermediate lamella 12 and fixed plate 14 and takes place the dead possibility of card, thereby has guaranteed connecting rod 9's normal use and the validity of unmanned aerial vehicle wing attitude adjustment, and then has guaranteed unmanned aerial vehicle's normal use.

The above description is only an embodiment of the present invention, and is not intended to limit the present invention. Various modifications and alterations to this invention will become apparent to those skilled in the art. Any modification, equivalent replacement, improvement or the like made within the spirit and principle of the present invention should be included in the scope of the claims of the present invention.

Claims

1. The utility model provides an unmanned aerial vehicle left and right sides airfoil linkage anti-lock structure device, includes intermediate lamella (12) and sets up fixed plate (14) at both ends about intermediate lamella (12), its characterized in that: side recess (10) have all been seted up to the central authorities of intermediate plate (12) the left and right sides, and two side recess (10) inner walls are close to the central authorities of one side of each other and all set up horizontal regulation recess (11) that set up, two central authorities that adjust recess (11) inner walls are close to one side of each other all are connected with connecting rod (9) that are connected with the wing through electric telescopic handle (3), and the one end that both sides are close to each other all is connected with limiting plate (6) around two connecting rod (9), two fixed plate (14) inner walls are close to the preceding back both ends of one side of each other and all are connected with the buffer board corresponding with limiting plate (6) through buffer spring (2).

2. The unmanned aerial vehicle left and right airfoil linkage anti-lock braking structure device of claim 1, wherein: the built-in recess has been seted up to the inside central authorities of intermediate lamella (12), and the inside central authorities of built-in recess are connected with through fixed block (4) can control electric telescopic handle (3) and respectively with two electric telescopic handle (3) electric connection's control maincenter (5), and control maincenter (5) and unmanned aerial vehicle's remote controller signal connection.

3. The unmanned aerial vehicle left and right airfoil linkage anti-lock braking structure device of claim 1, wherein: two connecting rods (9) keep away from the central authorities of one side each other and all rotate through turning block (8) and be connected with connecting plate (1) that are connected with the unmanned aerial vehicle wing, and the upper and lower both ends of keeping away from one side each other of two connecting plates (1) all set up the connect the via hole that transversely runs through connecting plate (1).

4. The unmanned aerial vehicle left and right airfoil linkage anti-lock braking structure device of claim 1, wherein: four corners of the left side and the right side of the middle plate (12) are provided with grooves, and the mutually adjacent sides of the inner walls of the left group of grooves and the right group of grooves are connected with clamping rods (7) with L-shaped front views through torsion spring rotating shafts.

5. The unmanned aerial vehicle left and right airfoil linkage anti-lock braking structure device of claim 4, wherein: the ends of the left and right clamping rods (7) which are far away from each other are clamped with the fixing plates (14), and the four corners of one side of each of the two fixing plates (14) which are far away from each other are provided with connecting bolts (13) which are respectively connected with the left side and the right side of the middle plate (12).