CN218477629U

CN218477629U - Arm mechanism and unmanned aerial vehicle

Info

Publication number: CN218477629U
Application number: CN202222777710.8U
Authority: CN
Inventors: 温海军; 赵智博; 彭斌
Original assignee: Guangzhou Xaircraft Technology Co Ltd
Current assignee: Guangzhou Xaircraft Technology Co Ltd
Priority date: 2022-10-20
Filing date: 2022-10-20
Publication date: 2023-02-14
Anticipated expiration: 2032-10-20

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to an arm mechanism and an unmanned aerial vehicle; unmanned aerial vehicle includes the fuselage and connects in the horn mechanism of fuselage, and horn mechanism is including dismantling or rotating first horn and the second horn of connecting, and wherein first horn is connected with unmanned aerial vehicle's power component, and the second horn is connected with the fuselage, and wherein, first horn includes first horn body, and the second horn includes the second horn body, and the intensity of first horn body is greater than the intensity of second horn body. The utility model discloses an unmanned aerial vehicle takes place when the crash accident, can make horn mechanism bend or break at appointed position and let out the power in order to reduce the loss, reduces unmanned aerial vehicle's cost of maintenance.

Description

Arm mechanism and unmanned aerial vehicle

Technical Field

The utility model relates to an unmanned air vehicle technique field particularly, relates to an arm mechanism and unmanned aerial vehicle.

Background

The unmanned aerial vehicle has wide application in the fields of agriculture, aerial photography, fire rescue and the like. Unmanned aerial vehicle generally includes fuselage, horn and power component, and power component passes through the horn and assembles in the fuselage for flight for unmanned aerial vehicle provides lift.

The machine arm comprises an integral fixed type and a sectional type, and the sectional type comprises a folding type and a detachable type; the sectional type horn provided by the related art usually uses the horn pipes with the same size and specification and the same material, for example, the whole horn uses carbon tube material or the whole horn uses aluminum tube material. When the crash accident happens to the unmanned aerial vehicle, the whole arm pipe is made of the same material, so that the impact force borne by each part of the whole arm is equivalent, the unmanned aerial vehicle cannot be bent at the appointed part or broken to release the force so as to reduce the loss when the arm is broken, and the maintenance cost of the unmanned aerial vehicle is high.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide an arm mechanism and unmanned aerial vehicle, when unmanned aerial vehicle took place the crash accident, can make arm mechanism bend or break at appointed position and let out the power in order to reduce the loss, reduce unmanned aerial vehicle's cost of maintenance.

The embodiment of the utility model is realized like this:

in a first aspect, the utility model provides an arm mechanism for unmanned aerial vehicle, include:

one end of the first machine arm is used for being connected with a power assembly of the unmanned aerial vehicle;

one end of the second horn is rotatably or detachably connected with the other end of the first horn, and the other end of the second horn is used for connecting the body of the unmanned aerial vehicle; wherein,

the first arm comprises a first arm body, the second arm comprises a second arm body, and the strength of the first arm body is greater than that of the second arm body.

In an optional embodiment, the first arm further comprises a first connecting part and an assembling part, the first connecting part and the assembling part are respectively connected to two ends of the first arm body in the length extending direction, the assembling part is used for connecting the power assembly, and the first connecting part is connected with the second arm; wherein,

at least one of the first connecting part and the assembling part is integrally formed with the first machine arm body.

In an alternative embodiment, the first connecting portion and the mounting portion are each integrally formed with the first arm body.

In an optional embodiment, the second horn further comprises a second connecting part and a mounting part connected to both ends of the second horn body in the length extending direction; the installation part is used for being connected with the fuselage, and first connecting portion are connected with the second connecting portion.

In an alternative embodiment, the first arm body is a carbon tube; the second horn body is the aluminum pipe.

In an alternative embodiment, at least one of the second connecting portion and the mounting portion is integrally formed with the second horn body.

In an alternative embodiment, both the second connecting portion and the mounting portion are integrally formed with the second horn body.

In an alternative embodiment, the horn mechanism further comprises a locking assembly disposed on one of the second horn and the first horn;

when the second machine arm is rotatably connected with the first machine arm, the locking assembly is used for locking the second machine arm and the first machine arm in a unfolded state or unlocking the second machine arm and the first machine arm from the unfolded state;

when the second arm is detachably connected with the first arm, the locking assembly is used for locking the second arm and the first arm in a mutually connected state.

In an alternative embodiment, the boom mechanism further comprises a shield connected to the first boom for shielding cables of a power assembly mounted to the first boom.

In a second aspect, the present invention provides an unmanned aerial vehicle, comprising a fuselage and a horn mechanism of any of the foregoing embodiments.

The utility model discloses horn mechanism's beneficial effect includes: the embodiment of the utility model provides a horn mechanism is including dismantling or rotating first horn and the second horn of connecting, and wherein first horn is connected with unmanned aerial vehicle's power component, and the second horn is connected with the fuselage, and wherein, first horn includes first horn body, and the second horn includes the second horn body, and the intensity of first horn body is greater than the intensity of second horn body. When the unmanned aerial vehicle provided with the arm mechanism crashes, the second arm with lower strength is easier to bend or break, namely, when the unmanned aerial vehicle crashes, the arm mechanism can be bent or broken at the appointed part to release force, and the purposes of reducing loss and reducing maintenance cost are achieved; moreover, the power assembly is assembled on the first machine arm with higher strength, the second machine arm is provided with fewer integrated components, and if the power assembly is maintained, the maintenance can be completed only by replacing the second machine arm, so that the maintenance cost can be effectively reduced.

The utility model discloses unmanned aerial vehicle's beneficial effect includes: the unmanned aerial vehicle provided by the embodiment of the utility model comprises the arm mechanism, and the arm mechanism can be bent or broken at a designated position to release force when the unmanned aerial vehicle crashes, so that the purposes of reducing loss and maintenance cost are achieved; moreover, the power assembly is assembled on the first machine arm with higher strength, the number of integrated parts on the second machine arm is small, and if the power assembly is maintained, the maintenance can be completed only by replacing the second machine arm, so that the maintenance cost can be effectively reduced.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention, and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.

FIG. 1 is a schematic structural view of a boom mechanism according to an embodiment of the present invention;

fig. 2 is a first exploded view of the boom mechanism according to the embodiment of the present invention;

fig. 3 is a second exploded schematic view of the boom mechanism according to the embodiment of the present invention.

Icon: 100-a horn mechanism; 110-a first horn; 111-a first arm body; 112-a first connection; 113-a mounting portion; 120-a second horn; 121-a second horn body; 122-a second connection; 123-a mounting part; 130-a locking assembly; 140-a protective cover; 150-a rotating shaft; 200-a power assembly; 210-a motor; 220-a propeller; and 230-electric regulation.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, 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, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of embodiments of the present invention, as generally described and illustrated in the figures herein, may be arranged and designed in a wide variety of different configurations.

Thus, the following detailed description of the embodiments of the present invention, presented in the accompanying drawings, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.

It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.

In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", and the like indicate the position or positional relationship based on the position or positional relationship shown in the drawings, or the position or positional relationship which is usually placed when the utility model is used, and are only for convenience of description and simplification of the description, but do not indicate or imply that the device or element to be referred must have a specific position, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like are used merely to distinguish one description from another, and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed" and "connected" are to be interpreted broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood as a specific case by those skilled in the art.

Referring to fig. 1, the present embodiment provides an unmanned aerial vehicle, which may be used in the fields of plant protection, aerial photography, fire rescue, and the like.

The unmanned aerial vehicle comprises a fuselage, an arm mechanism 100 (shown in fig. 1), a power assembly 200 (shown in fig. 1) and a landing gear (not shown), wherein the arm mechanism 100 and the landing gear are both connected with the fuselage; the undercarriage is positioned below the airframe and used for providing support for the airframe so that the unmanned aerial vehicle can take off and land stably; the power assembly 200 is connected to the horn mechanism 100 and is used to provide lift for flight.

Further, referring to fig. 1, the power assembly 200 includes a motor 210 and a propeller 220, the motor 210 is assembled to the horn mechanism 100, the propeller 220 is in transmission connection with an output shaft of the motor 210, and the motor 210 is used for driving the propeller 220 to rotate so as to provide a lift force for the unmanned aerial vehicle to fly.

Still further, power assembly 200 still includes electricity accent 230, and electricity accent 230 assembles in horn mechanism 100, and with motor 210 transmission fit for driving motor 210 and screw 220 swing in step.

It should be noted that the structure and the connection mode of the landing gear to the fuselage, and the assembly mode of the motor 210, the propeller 220, and the electric tilt 230 are similar to those of the related art, and are not described herein again.

Referring to fig. 1, fig. 2 and fig. 3, the arm mechanism 100 of the present embodiment includes a first arm 110 and a second arm 120, which are rotatably connected, that is, the arm mechanism 100 is a foldable structure; when the unmanned aerial vehicle is used, the second arm 120 and the first arm 110 need to be unfolded mutually, so that the included angle between the two arms is 180 degrees; when accomodating, carrying unmanned aerial vehicle, then can be with second horn 120 and first horn 110 folding each other, make contained angle between them be the acute angle, the angle can be 30 °, 45 °, 60 etc to reduce the space that unmanned aerial vehicle occupy, the unmanned aerial vehicle's of being more convenient for receiver transport.

Further, the second horn 120 and the first horn 110 are rotatably connected by a rotating shaft 150; in this way, the second arm 120 and the first arm 110 can be flexibly and smoothly rotated as required.

It should be appreciated that in other embodiments, the second boom 120 and the first boom 110 are removably connected; when the unmanned aerial vehicle is used, the second horn 120 and the first horn 110 need to be connected and distributed along a straight line; when accomodating, carrying unmanned aerial vehicle, then can be with second horn 120 and first horn 110 split to unmanned aerial vehicle's accomodating, transport. The detachable connection of the first and

second arms

110 and 120 includes, but is not limited to, a threaded connection, a connection by a fastener such as a bolt, etc.

In still other embodiments, the second horn 120 and the first horn 110 may also be fixedly connected, such as: welding, and the like.

In other embodiments, the horn mechanism 100 may include only the first horn 110, i.e., only one integrally fixed horn.

With continued reference to fig. 1, 2 and 3, the arm mechanism 100 further includes a locking assembly 130, the locking assembly 130 is disposed on the first arm 110; the locking assembly 130 is used to lock or unlock the second and

first arms

120 and 110 in or from the unfolded state. In this way, the locking assembly 130 can be used to lock the relative positions of the second arm 120 and the first arm 110 when the two arms are unfolded to ensure that the unmanned aerial vehicle can fly reliably; or, when needs are accomodate, are carried unmanned aerial vehicle, utilize locking subassembly 130 unblock to expand second horn 120 and first horn 110 under the assembly to make both can fold up through rotating relatively, with the whole volume of reduction unmanned aerial vehicle, be convenient for accomodate, carry.

Of course, in other embodiments, the locking assembly 130 is disposed on the second arm 120.

In other embodiments, the first arm 110 is detachably connected to the second arm 120, and the locking assembly 130 is used to lock the second arm 120 and the first arm 110 in an interconnected state; to ensure that the drone can reliably fly when the second horn 120 and the first horn 110 are connected.

It should be noted that the locking assembly 130 includes, but is not limited to, a hoop assembly, a snap assembly or a threaded assembly, and is not limited to this.

The first horn 110 includes a first horn body 111, a first connecting portion 112 and an assembling portion 113, the first connecting portion 112 and the assembling portion 113 are respectively connected to two ends of the first horn body 111 in the length extending direction, the assembling portion 113 is used for assembling the power assembly 200, the first connecting portion 112 is connected with the body, and specifically, the first connecting portion 112 is connected with the body through the second horn 120; at least one of the first connecting portion 112 and the mounting portion 113 is integrally formed with the first arm body 111.

During assembly, at least one of the first connecting portion 112 and the assembling portion 113 does not need to be additionally connected to the first arm body 111, so that the assembly of the first arm 110 is simplified, and the time consumption of assembly is reduced; in addition, the connection method of the integral molding can improve the connection stability, and the stability of the assembly of the body and the power assembly 200 with the first arm body 111 through the first connection part 112 and the assembly part 113 respectively.

In this embodiment, the first connecting portion 112 and the assembling portion 113 are integrally injection-molded with the first arm body 111; of course, in other embodiments, one of the first connecting portion 112 and the fitting portion 113 is integrally injection molded with the first arm body 111.

Further, the second horn 120 includes a second horn body 121, and a second connecting portion 122 and a mounting portion 123 connected to both ends of the second horn body 121 in a length extending direction; the mounting portion 123 is connected to the body, and the first connecting portion 112 is connected to the second connecting portion 122, so that the first arm 110 is connected to the body through the second arm 120. In this way, the first arm 110 can be reliably connected to the body via the second arm 120 by the connection between the first connection portion 112 and the second connection portion 122 and the connection between the mounting portion 123 and the body.

Still further, both the second connecting portion 122 and the mounting portion 123 are integrally formed with the second horn body 121. Thus, when the unmanned aerial vehicle is assembled, the second connecting portion 122 and the mounting portion 123 do not need to be additionally assembled on the second arm body 121, so that the assembly process can be reduced, time consumption is reduced, the second arm 120 and the first arm 110 are reliably connected through the first connecting portion 112 and the second connecting portion 122, and the motor 210 is reliably connected to the first arm body 111 through the mounting portion 123.

Of course, in other embodiments, one of the second connecting portion 122 and the mounting portion 123 is integrally formed with the second horn body 121.

It should be noted that, in the embodiment, the first connecting portion 112 and the second connecting portion 122 are rotatably connected through the rotating shaft 150, and the locking assembly 130 is disposed on the first connecting portion 112, when the first arm 110 and the second arm 120 are relatively unfolded, the locking mechanism is simultaneously connected with the first connecting portion 112 and the second connecting portion 122, so as to lock the first arm 110 and the second arm 120 in the unfolded state.

It should be noted that the manner of connecting the mounting portion 123 to the body includes, but is not limited to, a bolt connection, a screw connection, etc., and is not limited in detail herein.

The foldable boom mechanism 100 of the present embodiment or the detachable boom mechanism 100 of the other embodiments are all sectional booms, and the sectional booms usually use boom pipes with the same dimension and specification and the same material, for example, the whole boom uses carbon pipe material or the whole boom uses aluminum pipe material. When the crash accident happens to the unmanned aerial vehicle, the whole arm pipe uses the arm pipes with the same size and specification and the same material, so that the impact force borne by each part of the whole arm is equivalent, the arm cannot be bent or broken at the designated part to release force so as to reduce loss when broken, and the maintenance cost of the unmanned aerial vehicle is high.

In order to improve the above problem, the strength of the first arm body 111 is greater than that of the second arm body 121, that is, the first arm 110 may be configured to have a greater impact strength than that of the second arm 120, that is, the first arm 110 may be made of a material having a greater impact strength, and the second arm 120 may be made of a material having a relatively smaller impact strength, or the impact strength of the first arm 110 may be greater than that of the second arm 120 by adjusting the sizes of the arm pipes of the second arm 120 and the first arm 110. According to the distributed design of the horn pipes with different strengths on the same set of horn mechanisms 100, when the unmanned aerial vehicle crashes, the horn mechanisms 100 can be bent or broken at the designated parts to release force, and the purposes of reducing loss and reducing maintenance cost are achieved.

In this embodiment, the first arm body 111 is a carbon tube, and the impact strength is about 590mpa; the second horn body 121 is an aluminum tube having an impact strength of about 300mpa. When the horn mechanism 100 is impacted by a crash accident, the strength of the second horn body 121 connected with the horn is weaker than that of the first horn 110 relatively far away from the horn, so the second horn body 121 can be bent or broken to play a role in force leakage, and the first horn 110 assembled with the motor 210 is prevented from being damaged to cause larger loss.

Optionally, the horn mechanism 100 further comprises a protective cover 140, the protective cover 140 being connected to an end of the first horn 110; specifically, the shield 140 is connected to the mounting portion 113 for shielding the cable of the motor 210 to improve the problem that the cable is exposed to the outside and easily damaged.

The assembly process of the horn mechanism 100 of the present embodiment includes: the first connecting part 112 and the second connecting part 122 are connected to realize the connection between the first horn 110 and the second horn 120; the mounting part 123 of the second arm 120 is connected to the body, and the arm mechanism 100 can be assembled to the body; the motor 210 of the power module 200 is connected to the mounting portion 113, and the propeller 220 is mounted to the motor 210.

To sum up, the utility model discloses an arm mechanism 100 can be used for unmanned aerial vehicle, when unmanned aerial vehicle takes place the crash accident, can make arm mechanism 100 bend or break at appointed position and let out the power in order to reduce the loss, reduce unmanned aerial vehicle's cost of maintenance.

The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to 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. An arm mechanism for unmanned aerial vehicle, its characterized in that includes:

a first arm (110), one end of the first arm (110) is used for connecting a power assembly (200) of the unmanned aerial vehicle;

one end of the second arm (120) is rotatably or detachably connected with the other end of the first arm (110), and the other end of the second arm (120) is used for connecting the body of the unmanned aerial vehicle; wherein,

the first arm (110) comprises a first arm body (111), the second arm (120) comprises a second arm body (121), and the strength of the first arm body (111) is greater than that of the second arm body (121).

2. The horn mechanism according to claim 1, wherein the first horn (110) further comprises a first connecting portion (112) and a fitting portion (113), and the first connecting portion (112) and the fitting portion (113) are respectively connected to two ends of the first horn body (111) in a length extending direction, the fitting portion (113) is used for connecting the power assembly (200), and the first connecting portion (112) is connected to the second horn (120); wherein,

at least one of the first connecting portion (112) and the fitting portion (113) is integrally formed with the first arm body (111).

3. The horn mechanism according to claim 2, wherein the first connecting portion (112) and the fitting portion (113) are each integrally formed with the first horn body (111).

4. The horn mechanism according to claim 2, wherein the second horn (120) further comprises a second connecting portion (122) and a mounting portion (123) connected to both ends of the second horn body (121) in the length extending direction; the installation part (123) is used for being connected with the fuselage, just first connecting portion (112) with second connecting portion (122) are connected.

5. A robot arm mechanism according to claim 4, characterized in that said first robot arm body (111) is a carbon tube; the second machine arm body (121) is an aluminum pipe.

6. A horn mechanism according to claim 4, characterized in that at least one of the second connecting portion (122) and the mounting portion (123) is integrally formed with the second horn body (121).

7. The horn mechanism of claim 6 wherein the second connecting portion (122) and the mounting portion (123) are both integrally formed with the second horn body (121).

8. The horn mechanism of claim 1, further comprising a locking assembly (130), the locking assembly (130) disposed to one of the second horn (120) and the first horn (110);

the locking assembly (130) is configured to lock or unlock the second horn (120) and the first horn (110) in or from an expanded state when the second horn (120) is rotatably coupled to the first horn (110);

the locking assembly (130) is configured to lock the second boom (120) and the first boom (110) in an interconnected state when the second boom (120) is removably coupled to the first boom (110).

9. A horn mechanism according to any of claims 1-8, characterized in that it further comprises a shield (140), said shield (140) being connected to said first horn (110) for shielding cables of said power assembly (200) fitted to said first horn (110).

10. An unmanned aerial vehicle comprising a fuselage and the horn mechanism of any one of claims 1-9.