CN216070488U

CN216070488U - Wing folding mechanism of flight device

Info

Publication number: CN216070488U
Application number: CN202122140617.1U
Authority: CN
Inventors: 张晓攀; 杜国柱; 李韶飞; 沈洋
Original assignee: Xian Lingkong Electronic Technology Co Ltd
Current assignee: Xian Lingkong Electronic Technology Co Ltd
Priority date: 2021-09-06
Filing date: 2021-09-06
Publication date: 2022-03-18
Anticipated expiration: 2031-09-06

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, and discloses a wing folding mechanism of a flight device, which comprises an active folding assembly and a folding driving assembly, wherein the active folding assembly comprises a driving shaft and a driving shaft; the active folding assembly comprises a mounting seat and a rotating body which are connected in a rotating manner; the folding driving assembly comprises a driving mechanism and a gear box, the input end of the gear box is in driving connection with the driving mechanism, and the output end of the gear box is used for driving the rotating body of the driving folding assembly to rotate. According to the utility model, the wings of the fixed-wing unmanned aerial vehicle are of a foldable structure through the wing folding mechanism, so that the occupied area of the fixed-wing unmanned aerial vehicle during transportation, carrying and parking is reduced, and the problem that the fixed-wing unmanned aerial vehicle is not easy to store is solved.

Description

Wing folding mechanism of flight device

Technical Field

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a wing folding mechanism of a flight device

Background

The existing unmanned aerial vehicle flying device is basically divided into two types of fixed-wing unmanned aerial vehicles and rotor unmanned aerial vehicles, the two types of unmanned aerial vehicles have different characteristics due to the difference of the structures of the two types of unmanned aerial vehicles, wherein the fixed-wing unmanned aerial vehicles have the advantages of high flying speed, low cost and high carrying capacity, and the rotor unmanned aerial vehicles have the advantages of vertical take-off and landing and hovering. What explains especially, among the current unmanned aerial vehicle flight device, the VTOL fixed wing unmanned aerial vehicle who has combined fixed wing unmanned aerial vehicle and rotor unmanned aerial vehicle advantage has in addition.

The vertical take-off and landing fixed-wing unmanned aerial vehicle is an unmanned aerial vehicle which effectively combines the vertical take-off and landing capability of a multi-rotor unmanned aerial vehicle and the high-efficiency cruising capability of the fixed-wing unmanned aerial vehicle. Because of the unique take-off and landing-cruising performance, the fixed wing unmanned aerial vehicle has great application prospect in the industry fields of military police reconnaissance, border patrol, oil and gas pipeline patrol, power patrol, forest fire control, surveying and mapping and the like. And this unmanned aerial vehicle has solved the difficult problem of fixed wing unmanned aerial vehicle VTOL with simple and reliable mode, has the fixed wing unmanned aerial vehicle duration of sailing concurrently, and characteristics and rotor unmanned aerial vehicle VTOL that speed is high, the distance is far away, and the VTOL mode has strengthened the environmental suitability of this unmanned aerial vehicle platform greatly.

But because fixed wing structure of fixed wing unmanned aerial vehicle flying device makes it have area big when transportation, carry and park, the difficult problem of accomodating.

SUMMERY OF THE UTILITY MODEL

Based on the technical problems, the utility model provides a wing folding mechanism of a flight device, which enables wings of a fixed-wing unmanned aerial vehicle to be of a foldable structure through a folding locking mechanism so as to reduce the occupied area of the fixed-wing unmanned aerial vehicle during transportation, carrying and parking and solve the problem that the fixed-wing unmanned aerial vehicle is not easy to store, and the wing folding mechanism specifically comprises the following technical scheme:

in order to solve the technical problems, the technical scheme adopted by the utility model is as follows:

the wing folding mechanism of the flight device comprises an active folding assembly and a folding driving assembly; the active folding assembly comprises a mounting seat and a rotating body which are connected in a rotating manner; the folding driving assembly comprises a driving mechanism and a gear box, the input end of the gear box is in driving connection with the driving mechanism, and the output end of the gear box is used for driving the rotating body of the driving folding assembly to rotate.

Further, the gear box includes the box, is equipped with reduction gear set in the box.

Furthermore, the box body is formed by assembling a first box body and a second box body.

Furthermore, a gear in the reduction gear set is rotatably erected on the box body, and a bearing is arranged at the rotary connection position of the gear in the reduction gear set and the box body.

Furthermore, the folding device also comprises a driven folding assembly, and the driven folding assembly and the driving folding assembly are consistent in structure; wherein, the driven folding component and the driving folding component are symmetrically arranged at intervals.

Furthermore, the mounting seat is hinged with the rotating body through a rotating pin, the rotating pin is fixedly connected with the rotating body, and the rotating pin is rotationally connected with the mounting seat; wherein, the one end of the rotating pin of initiative folding assembly is fixedly connected with the output of actuating mechanism.

Furthermore, the rotating connection position of the rotating pin and the mounting seat is provided with an embedding sleeve.

Further, the driving mechanism adopts a motor or a steering engine.

Furthermore, the mounting seat, the gear box and the driving mechanism are fixedly connected with the first wing, and the rotating body is fixedly connected with the second wing.

Furthermore, a connecting plate is arranged on the rotating body.

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

the wing folding and locking mechanism disclosed by the utility model realizes automatic folding and unfolding of the wings of the fixed-wing unmanned aerial vehicle, and solves the problems that the wings of the fixed-wing unmanned aerial vehicle are large in occupied area and difficult to store during transportation, carrying and parking. The whole wing folding locking mechanism has high automation degree, convenient operation and simple and reliable structure.

Drawings

The present application will be further explained by way of exemplary embodiments, which will be described in detail by way of the accompanying drawings, in which:

fig. 1 is a schematic view of an assembly structure of a wing folding mechanism and a wing of a flight device (a wing unfolding state).

Fig. 2 is a schematic view of a wing folding mechanism and a wing assembly structure of the flying device (wing folded state).

Fig. 3 is a schematic structural diagram of a wing folding mechanism of the flight device.

The folding mechanism comprises a driven folding assembly 1, a second wing 2, a driving folding assembly 3, a folding driving assembly 4, a gear box 41, a first box 411, a second box 412, a reduction gear set 413, a bearing 414, a driving mechanism 42, a first wing 5, a rotating body 6, a connecting plate 61, a mounting seat 7, an embedding sleeve 8 and a rotating pin 9.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions of the embodiments of the present application will be clearly and completely described below with reference to the drawings of the embodiments of the present application. It should be apparent that the described embodiments are only some of the embodiments of the present application, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the described embodiments of the application without any inventive step, are within the scope of protection of the application.

Unless defined otherwise, technical or scientific terms used herein shall have the ordinary meaning as understood by one of ordinary skill in the art to which this application belongs. As used in this application, the terms "first," "second," and the like do not denote any order, quantity, or importance, but rather are used to distinguish one element from another. The word "comprising" or "comprises", and the like, means that the element or item listed before the word covers the element or item listed after the word and its equivalents, but does not exclude other elements or items. The terms "connected" or "coupled" and the like are not restricted to physical or mechanical connections, but may include electrical connections, whether direct or indirect. "upper", "lower", "left", "right", and the like are used merely to indicate relative positional relationships, and when the absolute position of the object being described is changed, the relative positional relationships may also be changed accordingly.

Fig. 1 to 3 are schematic structural views of a folding mechanism of a flight device wing according to some embodiments of the present application, and the folding mechanism of the flight device wing according to the present application will be described below with reference to fig. 1 to 3. It should be noted that fig. 1-3 are merely exemplary and are not intended to limit the specific shape and configuration of the folding mechanism of the aircraft wing.

Referring to fig. 3, in some embodiments, a wing folding mechanism for a flying device includes an active folding assembly 3 and a folding drive assembly 4; the active folding assembly 3 comprises a mounting seat 7 and a rotating body 6 which are connected in a rotating manner; the folding driving assembly 4 comprises a driving mechanism 42 and a gear box 41, an input end of the gear box 41 is in driving connection with the driving mechanism 42, and an output end of the gear box 41 is used for driving the rotating body 6 of the active folding assembly 3 to rotate.

Referring to fig. 1 to 2, for the installation of the wing folding mechanism and the wing, the mounting base 7, the gear box 41 and the driving mechanism 42 are all fixedly connected with the first wing 5, and the rotating body 6 is fixedly connected with the second wing 2.

Preferably, the rotating body 6 is provided with a connecting plate 61. The connecting plate 61 can increase the connecting area of the rotating body 6 and the second wing 2, and enhance the reliability of connection.

Therefore, the working process of the wing folding locking mechanism is explained by combining the wing folding locking mechanism and the installation structure of the wing: the wing folding mechanism is matched with the gear box 41 through a driving mechanism 42, and the driving force of the driving mechanism 42 is used for driving the rotating body 6 to rotate around the hinged joint of the rotating body and the mounting base 7, so that the rotating body 6 is used for driving the second wing 2 to rotate and fold. After the wing is folded, the occupied area of the fixed-wing unmanned aerial vehicle can be effectively reduced, and the fixed-wing unmanned aerial vehicle is convenient to transport, carry and park. When the wing needs to be unfolded, the driving mechanism 42 drives the rotating body 6 to rotate reversely, so that the wing can be unfolded rotationally.

Therefore, the automatic folding or unfolding of the wings can be realized, and the whole wing folding mechanism is high in automation degree and convenient and fast to operate.

Specifically, the driving mechanism 42 is a motor or a steering engine.

Referring to fig. 3, in some embodiments, the gearbox 41 includes a housing having a reduction gear set 413 disposed therein.

The reduction gear set 413 is designed to reduce the rotation speed of the output end of the gear box 41 through the cooperation between the gears, so as to increase the torque.

Preferably, the case is formed by assembling a first case 411 and a second case 412. The box body with the assembled structure is convenient to disassemble and assemble, and the gear box 41 is convenient to maintain later.

Specifically, the driving connection mode of the input end of the gear box 41 and the driving mechanism 42 can be determined according to the installation position of the driving mechanism 42. Referring to the drawings, in the mounting structure, since the input end and the output end of the gear box 41 are oppositely arranged, the driving mechanism 42 and the gear box 41 can be in driving connection through a bevel gear set, so that the power of the driving mechanism 42 is transmitted to the gear box 41 after being changed in direction.

Preferably, the gears of the reduction gear set 413 are rotatably mounted on the housing, and a bearing 414 is disposed at a rotational connection position of the gears of the reduction gear set 413 and the housing. To reduce the friction of the gear rotation.

Referring to fig. 1, in some embodiments, the folding device further includes a driven folding assembly 1, wherein the driven folding assembly 1 is consistent with the driving folding assembly 3 in structure; wherein, the driven folding component 1 and the driving folding component 3 are symmetrically arranged at intervals.

In which, only one folding assembly is arranged on some wings with larger width, and the problem of insufficient connection strength or uneven stress at the folding connection of the wings may occur. By additionally arranging the driven folding assembly 1, folding connection points of the wings are increased, folding connection strength of the wings is enhanced, and folding connection safety is improved.

Referring to fig. 3, in some embodiments, the mounting base 7 is hinged to the rotating body 6 through a rotating pin 9, the rotating pin 9 is fixedly connected to the rotating body 6, and the rotating pin 9 is rotatably connected to the mounting base 7; wherein, one end of the rotating pin 9 of the active folding component 3 is fixedly connected with the output end of the driving mechanism 42.

Under the structure, the output end of the gear box 41 can drive the rotating pin 9 to rotate, so that the gear box 41 can drive the rotating body 6 to rotate, and the subsequent folding or unfolding of the wing is completed.

Preferably, the insert sleeve 8 is arranged at the rotary connection position of the rotating pin 9 and the mounting seat 7. The insert sleeve 8 can reduce the friction force between the rotating pin 9 and the mounting seat 7, so that the rotating pin 9 can rotate more smoothly.

The above is an embodiment of the present invention. The embodiments and specific parameters in the embodiments are only used for clearly illustrating the verification process of the utility model and are not used for limiting the patent protection scope of the utility model, which is defined by the claims, and all the equivalent structural changes made by using the contents of the description and the drawings of the utility model should be included in the protection scope of the utility model.

Claims

1. Aircraft wing folding mechanism, its characterized in that includes:

the active folding assembly comprises a mounting seat and a rotating body which are connected in a rotating mode;

the folding driving assembly comprises a driving mechanism and a gear box, the input end of the gear box is in driving connection with the driving mechanism, and the output end of the gear box is used for driving the rotating body of the active folding assembly to rotate.

2. The heeling apparatus wing-folding mechanism of claim 1, wherein:

the gear box comprises a box body, and a reduction gear set is arranged in the box body.

3. The heeling apparatus wing-folding mechanism of claim 2, wherein:

the box body is formed by assembling a first box body and a second box body.

4. The heeling apparatus wing-folding mechanism of claim 2, wherein:

the middle gear of the reduction gear set is rotatably erected on the box body, and a bearing is arranged at the rotary connection position of the middle gear of the reduction gear set and the box body.

5. The heeling apparatus wing-folding mechanism of claim 1, further comprising:

a driven folding assembly in structural correspondence with the driving folding assembly;

wherein the driven folding assembly and the driving folding assembly are symmetrically arranged at intervals.

6. The heeling apparatus wing-folding mechanism of claim 1, wherein:

the mounting seat is hinged with the rotating body through a rotating pin, the rotating pin is fixedly connected with the rotating body, and the rotating pin is rotationally connected with the mounting seat;

one end of a rotating pin of the active folding assembly is fixedly connected with the output end of the driving mechanism.

7. The heeling apparatus wing-folding mechanism of claim 6, wherein:

and the rotary joint of the rotary pin and the mounting seat is provided with an insert sleeve.

8. The heeling apparatus wing-folding mechanism of claim 1, wherein:

the driving mechanism adopts a motor or a steering engine.

9. A flying device wing fold mechanism as claimed in any one of claims 1 to 8, wherein:

the mounting seat, the gear box and the driving mechanism are fixedly connected with the first wing, and the rotating body is fixedly connected with the second wing.

10. The heeling apparatus wing-folding mechanism of claim 9, wherein:

the rotating body is provided with a connecting plate.