CN220549221U

CN220549221U - Unmanned aerial vehicle and wing thereof

Info

Publication number: CN220549221U
Application number: CN202321102696.XU
Authority: CN
Inventors: 杨立文; 高星亮; 孙勇
Original assignee: Xi'an Jingdong Tianhong Science And Technology Co ltd
Current assignee: Xi'an Jingdong Tianhong Science And Technology Co ltd
Priority date: 2023-05-09
Filing date: 2023-05-09
Publication date: 2024-03-01
Anticipated expiration: 2033-05-09

Abstract

The utility model discloses an unmanned aerial vehicle wing and an unmanned aerial vehicle, wherein the unmanned aerial vehicle wing comprises a wing body and at least one airborne equipment module, the wing body comprises a frame and a skin covered on the outer surface of the frame, and the frame and the skin enclose at least one accommodating cavity. At least one on-board equipment module is arranged in the accommodating cavity. At least part of the frame and the skin serves as an outer shell of the on-board equipment module. According to the unmanned aerial vehicle wing disclosed by the embodiment of the utility model, the wing body not only plays roles of bearing and lifting, but also can be used as a shell of the airborne equipment module, so that the wing body and the airborne equipment module realize shell sharing, the weight of the wing is effectively reduced, and the weight of the unmanned aerial vehicle is further greatly reduced.

Description

Unmanned aerial vehicle and wing thereof

Technical Field

The embodiment of the utility model relates to the technical field of unmanned aerial vehicles, in particular to a wing and an unmanned aerial vehicle comprising the wing.

Background

The drone is an unmanned aircraft that is maneuvered using a radio remote control device and a self-contained programming device, or is operated autonomously, either entirely or intermittently, by an on-board computer. However, the weight of the unmanned aerial vehicle in the prior art needs to be further reduced to meet the requirement of light weight.

Disclosure of Invention

The embodiment of the utility model provides a wing and an unmanned aerial vehicle, which are used for further reducing the weight of the wing.

The unmanned aerial vehicle wing of the embodiment of the utility model comprises:

the wing body comprises a frame and a skin covering the outer surface of the frame, and at least one accommodating cavity is formed by the frame and the skin in an enclosing mode; and

at least one onboard equipment module arranged in the accommodating cavity; wherein at least a portion of the frame and the skin serve as an enclosure for the on-board equipment module.

According to some embodiments of the utility model, a protective layer is further provided between the airborne equipment module and the skin;

the protection layer is towards one side surface of airborne equipment module laminating in airborne equipment module, the protection layer dorsad airborne equipment module's one side surface laminating in the internal surface of covering.

According to some embodiments of the utility model, the protective layer comprises:

the first insulating layer is attached to the surface of one side of the airborne equipment module, which faces the skin; and

and the filling layer is filled between the surface of one side of the first insulating layer, which is opposite to the airborne equipment module, and the inner surface of the skin.

According to some embodiments of the utility model, a second insulating layer is further provided between the on-board equipment module and the frame, the second insulating layer being connected to the first insulating layer.

According to some embodiments of the utility model, the second insulating layer is of unitary construction with the first insulating layer.

According to some embodiments of the utility model, the frame and the skin enclose a plurality of said receiving cavities, the plurality of said receiving cavities being arranged along the length of the wing;

one or more of the plurality of receiving cavities receives the on-board equipment module.

According to some embodiments of the utility model, the frame comprises:

a spar; and

a plurality of ribs connected to the spar and arranged side by side along a length direction of the spar; the skin is connected to the spar and the ribs, and one accommodating cavity is arranged between two adjacent ribs.

According to some embodiments of the utility model, a second insulating layer is provided between the on-board equipment module and the wing rib and between the on-board equipment module and the spar.

According to some embodiments of the utility model, the on-board device module comprises any one of a battery module, a flight control module, or a navigation module.

The unmanned aerial vehicle comprises the unmanned aerial vehicle wing.

One embodiment of the above utility model has at least the following advantages or benefits:

according to the unmanned aerial vehicle wing disclosed by the embodiment of the utility model, the wing body comprises the frame and the skin covered on the outer surface of the frame, at least one accommodating cavity is formed by the frame and the skin, the accommodating cavity is used for accommodating the airborne equipment module, and at least part of the frame and the skin serve as the shell of the airborne equipment module. Therefore, the wing body not only plays roles of bearing and lifting, but also can be used as a shell of the airborne equipment module, so that the wing body and the airborne equipment module can be shared by the shells, the weight of the wing is effectively reduced, and the weight of the unmanned aerial vehicle is greatly reduced.

Drawings

FIG. 1 shows a schematic view of a wing in accordance with an embodiment of the utility model, with the skin separated from the frame.

Fig. 2 shows a cross-sectional view taken through the wing, taken perpendicular to the length of the wing.

Fig. 3 shows a schematic view of one of the spars.

Fig. 4 shows a schematic view of another spar.

Fig. 5 shows a schematic view of a rib.

Fig. 6 shows a schematic view of a side-by-side arrangement of a plurality of on-board equipment modules.

Figure 7 shows a cross-sectional view of A-A in figure 6.

Figure 8 shows a cross-sectional view of a wing of another embodiment of the utility model, wherein the cross-sectional direction is along a direction perpendicular to the length of the wing.

Wherein reference numerals are as follows:

100. wing body

101. Accommodating chamber

110. Frame

111. Spar beam

112. Wing rib

112a, intermediate rib

112b, side rib

120. Skin cover

121. Inner surface

200. Airborne equipment module

210. Battery cell

220. Insulating board

230. Heating film

240. Outer insulating film

300. Protective layer

310. A first insulating layer

320. Filling layer

400. Second insulating layer

D1, lengthwise direction

D2, width direction

Detailed Description

Example embodiments will now be described more fully with reference to the accompanying drawings. However, the exemplary embodiments can be embodied in many forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the concept of the example embodiments to those skilled in the art. The same reference numerals in the drawings denote the same or similar structures, and thus detailed descriptions thereof will be omitted.

As shown in fig. 1 and 2, the unmanned aerial vehicle wing according to the embodiment of the present utility model includes a wing body 100 and at least one on-board equipment module 200. The wing body 100 includes a frame 110 and a skin 120 covering an outer surface of the frame 110, and the frame 110 and the skin 120 enclose at least one accommodating cavity 101. At least one on-board equipment module 200 is disposed within the receiving cavity 101; wherein at least a portion of the frame 110 and the skin 120 serve as an enclosure for the airborne equipment module 200.

It will be understood that the terms "comprising," "including," and "having," and any variations thereof, are intended to cover non-exclusive inclusions in the embodiments of the utility model. For example, a process, method, system, article, or apparatus that comprises a list of steps or elements is not limited to only those listed steps or elements but may alternatively include other steps or elements not listed or inherent to such process, method, article, or apparatus.

According to the unmanned aerial vehicle wing disclosed by the embodiment of the utility model, the wing body 100 comprises the frame 110 and the skin 120 covered on the outer surface of the frame 110, at least one accommodating cavity 101 is formed by the frame 110 and the skin 120, the accommodating cavity 101 is used for accommodating the airborne equipment module 200, and at least part of the frame 110 and the skin 120 serve as the outer shell of the airborne equipment module 200. In this way, the wing body 100 not only plays roles of bearing and lifting, but also can be used as a shell of the airborne equipment module 200, so that the wing body 100 and the airborne equipment module 200 realize shell sharing, the weight of the wing is effectively reduced, and the weight of the unmanned aerial vehicle is greatly reduced.

As shown in fig. 1, the frame 110 and the skin 120 enclose a plurality of receiving cavities 101, the plurality of receiving cavities 101 being arranged along a length direction D1 of the wing. One or more of the plurality of receiving cavities 101 receives an organic on-board device module 200.

In the embodiment of the present utility model, the frame 110 and the skin 120 enclose four accommodating cavities 101, and each accommodating cavity 101 accommodates the organic airborne equipment module 200 therein.

Of course, in other embodiments, the number of receiving cavities 101 may be one, two, three, or other numbers. Also, when the number of the accommodation chambers 101 is plural, each of the plurality of accommodation chambers 101 may accommodate the on-board apparatus module 200, or a portion of the plurality of accommodation chambers 101 accommodates the organic on-board apparatus module 200 while another portion of the accommodation chambers 101 is empty.

It is understood that the on-board device module 200 may include any one of a battery module, a flight control module, or a navigation module.

In the embodiment of the utility model, the onboard equipment module 200 is a battery module, but not limited thereto.

It should be noted that, the shape of the on-board device module 200 may be a substantially rectangular parallelepiped shape, and the shape of the accommodating cavity 101 is adapted to the shape of the on-board device module 200.

As shown in fig. 1 and 2, the frame 110 includes a spar 111 and a plurality of ribs 112, and the plurality of ribs 112 are connected to the spar 111 and are arranged side by side along a length direction D1 of the spar 111. The skin 120 is connected to the spar 111 and the ribs 112, and a receiving cavity 101 is provided between two adjacent ribs 112.

In the embodiment of the present utility model, the frame 110 includes two spars 111, and the two spars 111 are disposed in parallel and arranged side by side along the width direction D2 of the wing. Each rib 112 is connected at both ends to two spars 111, respectively.

In the present utility model, the specific structure of the spar 111 may have various embodiments. For example, as shown in fig. 3, the spar 111 may be an i-beam. As shown in fig. 4, the spar 111 may be a channel beam.

In the embodiment of the present utility model, as shown in fig. 1, one of the two spars 111 of the present embodiment is an i-beam, and the other is a channel beam, but not limited thereto.

As an example, as shown in fig. 5, the rib 112 includes a middle rib 112a and two side ribs 112b, the two side ribs 112b are respectively connected to opposite sides of the middle rib 112a, and each side rib 112b is perpendicular to the middle rib 112 a. The surfaces of the two side ribs 112b facing away from each other are used for connection with the skin 120.

In the embodiment of the present utility model, the rib 112 is i-shaped. The I-shaped design may improve the strength of the rib 112 and thus the structural strength of the wing body 100.

Of course, in other embodiments, the rib 112 may take other configurations, which will not be described in detail herein.

As shown in fig. 6 and 7, when the on-board device module 200 is a battery module, the on-board device module 200 may include a plurality of battery cells 210, a plurality of insulating plates 220, two heating films 230, and an outer insulating film 240, which are stacked. An insulating plate 220 is disposed between two adjacent cells 210. And the outer side surfaces of the two outermost cells 210 of the plurality of cells 210 are also provided with one insulating plate 220, respectively, in the stacking direction. The two insulating plates 220 are each provided with a heating film 230 on a side facing away from each other. The outer insulating film 240 covers the plurality of battery cells 210, the plurality of insulating plates 220, and the two heating films 230.

As an example, the insulating plate 220 may be made of an epoxy material, the heating film 230 may be a polyimide heating film, and the outer insulating film 240 may be a PVC (Polyvinyl chloride) heat shrink, but is not limited thereto.

As shown in fig. 8, a protective layer 300 is further disposed between the airborne equipment module 200 and the skin 120, a side surface of the protective layer 300 facing the airborne equipment module 200 is attached to the airborne equipment module 200, and a side surface of the protective layer 300 facing away from the airborne equipment module 200 is attached to the inner surface 121 of the skin 120. Wherein the inner surface 121 of the skin 120 refers to a side surface facing the airborne equipment module 200. Since the outer surface of the protection layer 300 facing away from the airborne equipment module 200 is attached to the inner surface 121 of the skin 120, the protection layer 300 fills the gap between the airborne equipment module 200 and the skin 120, so as to avoid the airborne equipment module 200 from shaking relative to the wing body 100 and damaging the airborne equipment module 200.

The protective layer 300 includes a first insulating layer 310 and a filling layer 320. The first insulating layer 310 is attached to a side surface of the airborne equipment module 200 facing the skin 120, and the filling layer 320 is filled between a side surface of the first insulating layer 310 facing away from the airborne equipment module 200 and the inner surface 121 of the skin 120.

In this embodiment, first insulating layer 310 serves as an insulation to isolate airborne equipment module 200 from skin 120. The filler layer 320 fills the gap between the first insulating layer 310 and the inner surface 121 of the skin 120, and serves to prevent the airborne equipment module 200 from shaking.

As an example, the first insulating layer 310 may be made of an insulating material, such as plastic. The filler layer 320 may be made of an aramid paper honeycomb material or a Polymethacrylimide (PMI) foam material. Of course, the materials of the first insulating layer 310 and the filling layer 320 are not limited thereto.

A second insulating layer 400 is further disposed between the airborne equipment module 200 and the frame 110, and the second insulating layer 400 is connected to the first insulating layer 310. Specifically, a second insulating layer 400 is provided between the on-board equipment module 200 and the rib 112 and between the on-board equipment module 200 and the spar 111. The on-board equipment module 200 may be isolated from the frame 110 by the provision of the second insulating layer 400.

The second insulating layer 400 is made of an insulating material, such as plastic, but not limited thereto.

The second insulating layer 400 is integrally formed with the first insulating layer 310. Of course, the second insulating layer 400 and the first insulating layer 310 may be a separate structure.

In the embodiment of the present utility model, if the airborne equipment module 200 is in a cuboid shape, the surfaces of the airborne equipment module 200 facing the two skins 120 respectively are bonded with the protective layers 300, and the other surfaces of the airborne equipment module 200 are bonded with the second insulating layers 400.

In another aspect, the utility model also provides a unmanned aerial vehicle, including a unmanned aerial vehicle wing according to any of the above embodiments. The unmanned aerial vehicle according to the embodiment of the present utility model has all the advantages and beneficial effects of any one of the embodiments described above, and is not described here again.

It will be appreciated that the unmanned aerial vehicle of the embodiments of the present utility model may be a civilian unmanned aerial vehicle, or a military unmanned aerial vehicle.

It will be appreciated that the various embodiments/implementations provided by the utility model may be combined with one another without conflict and are not illustrated here.

In the inventive embodiments, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance; the term "plurality" means two or more, unless expressly defined otherwise. The terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; "coupled" may be directly coupled or indirectly coupled through intermediaries. The specific meaning of the above terms in the embodiments of the utility model will be understood by those skilled in the art according to the specific circumstances.

In the description of the embodiments of the utility model, it should be understood that the directions or positional relationships indicated by the terms "upper", "lower", "left", "right", "front", "rear", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience in describing the embodiments of the utility model and to simplify the description, and do not indicate or imply that the devices or units referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the embodiments of the utility model.

In the description of the present specification, the terms "one embodiment," "some embodiments," "particular embodiments," and the like, mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of an embodiment of the utility model. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

The above is only a preferred embodiment of the utility model and is not intended to limit the embodiment of the utility model, and various modifications and variations can be made to the embodiment of the utility model by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the embodiments of the present utility model should be included in the protection scope of the embodiments of the present utility model.

Claims

1. An unmanned aerial vehicle wing, comprising:

the wing body (100) comprises a frame (110) and a skin (120) covering the outer surface of the frame (110), wherein the frame (110) and the skin (120) enclose at least one accommodating cavity (101); and

at least one on-board equipment module (200) disposed within the housing cavity (101); wherein at least part of the frame (110) and the skin (120) serve as an outer shell of the on-board equipment module (200) so that the wing body (100) and the on-board equipment module (200) realize shell sharing.

2. The unmanned aerial vehicle wing according to claim 1, wherein a protective layer (300) is further provided between the on-board equipment module (200) and the skin (120);

the protection layer (300) is attached to the airborne equipment module (200) towards one side surface of the airborne equipment module (200), and one side surface of the protection layer (300) is attached to the inner surface (121) of the skin (120) away from the airborne equipment module (200).

3. The unmanned aerial vehicle wing according to claim 2, wherein the protective layer (300) comprises:

a first insulating layer (310) attached to a surface of the airborne equipment module (200) facing the skin (120); and

and a filling layer (320) filled between a side surface of the first insulating layer (310) facing away from the airborne equipment module (200) and the inner surface (121) of the skin (120).

4. A wing of an unmanned aerial vehicle according to claim 3, wherein a second insulating layer (400) is further provided between the airborne equipment module (200) and the frame (110), the second insulating layer (400) being connected to the first insulating layer (310).

5. The unmanned aerial vehicle wing according to claim 4, wherein the second insulating layer (400) is of unitary construction with the first insulating layer (310).

6. The unmanned aerial vehicle wing according to any of claims 1 to 5, wherein the frame (110) and the skin (120) enclose a plurality of the accommodation cavities (101), the plurality of accommodation cavities (101) being arranged along the length of the wing;

one or more of the plurality of accommodation cavities (101) accommodates the on-board equipment module (200).

7. The unmanned aerial vehicle wing according to any of claims 1 to 5, wherein the frame (110) comprises:

a spar (111); and

a plurality of ribs (112) connected to the spar (111) and arranged side by side along the length direction of the spar (111); the skin (120) is connected to the spar (111) and to a plurality of ribs (112), and one receiving cavity (101) is arranged between two adjacent ribs (112).

8. The unmanned aerial vehicle wing according to claim 7, wherein a second insulating layer (400) is provided between the on-board equipment module (200) and the rib (112) and between the on-board equipment module (200) and the spar (111).

9. The unmanned aerial vehicle wing according to any of claims 1 to 5, wherein the on-board equipment module (200) comprises any one of a battery module, a flight control module or a navigation module.

10. A unmanned aerial vehicle comprising a unmanned aerial vehicle wing as claimed in any one of claims 1 to 9.