CN217918385U - Covering, wing and unmanned aerial vehicle - Google Patents

Abstract

The application provides a skin, a wing and an unmanned aerial vehicle, wherein the skin is used for the wing of the unmanned aerial vehicle and comprises a first section and a second section which are integrally formed, and a containing cavity is defined by the first section and the second section; the accommodating cavity is used for installing a framework of the wing. The problem of current covering shaping structure can't satisfy the increase of wing demand because the defect of structure itself leads to manufacturing efficiency lower is solved in this application.

Description

Covering, wing and unmanned aerial vehicle

Technical Field

The application relates to the technical field of unmanned aerial vehicles, in particular to skin, wings and an unmanned aerial vehicle.

Background

Civil unmanned aerial vehicles rapidly develop along with the increase of living demands of people. The wing demand of composite fuselages has increased explosively. However, the wings of the existing unmanned aerial vehicle use a molding structure in a mold-clamping mode, and in the molding structure, the manufacturing efficiency of the skin is low, so that the increase of the wing demand is difficult to meet.

SUMMERY OF THE UTILITY MODEL

The application provides a covering, wing and unmanned aerial vehicle aims at solving current covering shaping structure and leads to manufacturing efficiency lower because the defect of structure itself, can't satisfy the problem of the increase of wing demand.

In a first aspect, the present application provides a skin for a wing of an unmanned aerial vehicle, including a first section and a second section that are integrally formed, the first section and the second section defining a receiving cavity; the accommodating cavity is used for installing a framework of the wing.

Optionally, the first and second sections have a common first end and the skin has an opening disposed distally of the first end.

Optionally, the first section further has a second end opposite the first end; the second section further having a third end opposite the first end; the second end portion and the third end portion are arranged at an interval in a height direction to form the opening.

Optionally, the skin has a leading edge and a trailing edge; the first section and the second section extend from the front edge to the rear edge, and gradually get away from each other and gradually get close to each other.

Optionally, the skin is flexible.

In a second aspect, an embodiment of the present application further provides an airfoil, including: a framework; and a skin as previously described; the skeleton is installed in hold the intracavity to with first section and second section all are connected.

Optionally, the framework includes a main beam and a plurality of ribs, and the ribs are arranged on the same side of the main beam at intervals; wherein the spar and the ribs each support the first and second sections.

Optionally, the wing further has a filler structure disposed within the receiving cavity and proximate to the leading edge of the skin.

Optionally, the main beam is a uniform cross-section beam.

In a third aspect, the present application further provides an unmanned aerial vehicle, including: a body; and a wing as described above, the wing being mounted on the fuselage.

The application provides a skin, including integrated into one piece's first section and second section. The first section and the second section define a receiving cavity; the accommodating cavity is used for installing a framework of the wing. Compared with the prior art: the existing skin is divided into an upper skin and a lower skin, and the skin can be formed only by processes such as hot pressing, die assembly and the like during assembly; in the technical scheme, the first section and the second section of the skin are integrally formed, so that complex procedures are not needed, and the manufacturing efficiency is improved.

Drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.

FIG. 1 is a schematic plan view of a skin provided in an embodiment of the present application from a perspective;

FIG. 2 is an enlarged view of a portion of FIG. 1 at A;

FIG. 3 is a schematic perspective view of an embodiment of the present application providing a skin;

FIG. 4 is a schematic perspective view of an airfoil provided in an embodiment of the present application;

fig. 5 is a schematic perspective view of a skeleton provided in an embodiment of the present application.

Detailed Description

The technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application, and it is obvious that the embodiments described are only some embodiments of the present invention, and not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by those skilled in the art without creative efforts belong to the protection scope of the present invention.

In the description of the present invention, it is to be understood that the directions or positional relationships indicated by the terms "length", "width", "height", etc. are based on the directions or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first" and "second" may explicitly or implicitly include one or more of the described features. In the description of the present invention, "a plurality" means two or more unless specifically limited otherwise.

In this application, the word "exemplary" is used to mean "serving as an example, instance, or illustration. Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. The following description is presented to enable any person skilled in the art to make and use the invention. In the following description, details are set forth for the purpose of explanation. It will be apparent to one of ordinary skill in the art that the present invention may be practiced without these specific details. In other instances, well-known structures and processes are not shown in detail to avoid obscuring the description of the invention with unnecessary detail. Thus, the present invention is not intended to be limited to the embodiments shown, but is to be accorded the widest scope consistent with the principles and features disclosed herein.

The existing skin mainly has the following defects: has an upper and a lower skin. Manual skin lay-up is slow and inefficient. The upper and lower skins need to be heated and cured again after being subjected to die assembly, so that the forming time and cost are increased. In conclusion, the existing skin forming manufacturing efficiency is low, and the growing demand of the unmanned aerial vehicle cannot be met.

To this end, the embodiments of the present application provide a skin 10, a wing 1, and a drone (not illustrated). The skin is used for the wing 1 of the drone. Unmanned aerial vehicle includes fuselage and wing 1, and wing 1 installs in the fuselage.

Referring to fig. 1 to 5, a skin 10, a wing 1 and a drone according to an embodiment of the present application are described. Fig. 1 is a schematic plan view of a skin provided in an embodiment of the present application from a viewing angle; FIG. 2 is an enlarged view of a portion of FIG. 1 at A; FIG. 3 is a schematic perspective view of an embodiment of the present application providing a skin; FIG. 4 is a schematic perspective view of an airfoil provided in an embodiment of the present application; fig. 5 is a schematic perspective view of a skeleton provided in an embodiment of the present application.

As shown in fig. 1, the present embodiment provides a skin 10 including a first section 10a and a second section 10b which are integrally formed. The first section 10a and the second section 10b define a housing chamber S; the receiving cavity S is used for mounting the skeleton 20 of the wing 1. Compared with the prior art: firstly, the prior art adopts two dies for respectively manufacturing an upper skin and a lower skin, and in the technical scheme of the application, the first section 10a and the second section 10b of the skin 10 are integrally formed, and only one die is needed; secondly, prior art need take out the back from the mould at upper and lower covering, need just can form through hot pressing, close mould etc. and in the technical scheme of this application, the integrated into one piece structure of covering 10 compares in the time of manufacture and adopts upper and lower covering fashioned structure to shorten greatly, and manufacturing efficiency can improve.

In addition, the integrally formed structure of the skin 10 facilitates maintenance or replacement of the skin 10.

It should be noted that, in the technical solution of the present application, the skin 10 is manufactured in one mold. The shape of the mould depends on the shape and size design of the skin 10, then the raw material of the skin 10 is poured into the mould, the skin 10 is taken out after the procedures of curing, demoulding and the like, and then the surface of the skin 10 is treated to obtain the final integrally formed skin 10. For example, the integral structure of the skin 10 may be formed as follows: the skin 10 is manufactured by using continuous fiber reinforced polycarbonate as a raw material and hot-press molding in an aluminum mold at a temperature of 200 degrees celsius.

Specifically, the raw material of the skin 10 is generally a thermoplastic material or a flexible fiber reinforced material, and the formed skin 10 has flexibility so that the skin 10 can fix the skeleton 20 based on elastic deformation thereof when the skeleton 20 is installed in the receiving cavity S. In the technical solution of the embodiment of the present application, the specifically usable materials of the skin 10 may be: graphite fibers, carbon fibers, glass fibers, carbon black, graphite powder, carbon nanotubes, or the like. In some embodiments, the skin 10 may also be made using ABS, glass reinforced plastic, or nylon.

When the skin is implemented by an implementer, the continuous fiber reinforced thermoplastic material can retain high strength, is beneficial to rapid volume production and is environment-friendly and recyclable, so that the skin 10 is generally made of the continuous fiber reinforced thermoplastic material.

Further, it should be noted that the shape of the accommodating cavity S is designed according to the shape of the framework 20, and the size of the accommodating cavity S is adapted to the size of the framework 20. In a specific implementation process, a implementer mainly sets the shape and the size of the accommodating cavity S according to the shape and the size of the framework 20, and the shape and the size are not limited herein.

As an alternative to the above described embodiment, as shown in FIG. 1, the first and second sections 10a, 10b have a common first end 10-1, and the skin 10 has an opening O disposed away from the first end 10-1. The opening O may be slightly flared during assembly of the skeleton 20 into the receiving cavity S of the skin 10, so as to avoid that the skeleton 20 and the skin 10 generate a large assembly force during assembly, thereby damaging the skeleton 20 or the skin 10.

On the other hand, the skin 10 is provided with the opening O to facilitate quick installation of the wire, and after the installation of the framework 20 and the wire is completed, the opening O is closed by riveting or hinging.

As an alternative to the above embodiment, as shown in FIG. 2, the first section 10a further has a second end 10-2 opposite the first end 10-1; the second section 10b also has a third end 10-3 opposite the first end 10-1; the second end portion 10-2 and the third end portion 10-3 are spaced apart in the height direction to form the opening O. When assembling the skeleton 20 into the receiving cavity S of the skin 10, the second end portion 10-2 and the third end portion 10-3 may each move away from each other based on the first end portion 10-1 as a fulcrum to slightly open the opening O, so that the skeleton 20 can be installed into the receiving cavity S with a small assembling force.

Note that, as shown in fig. 1, 2, and 3, the height direction is perpendicular to the length direction of the skin 10. After the framework 20 is installed in the receiving cavity S of the skin 10, the height direction is perpendicular to the length direction of the girders 20a of the framework 20, and the length direction of the girders 20a is parallel to the length direction of the skin 10.

As an alternative to the above-described embodiment, the skin 10 has a leading edge 10c and a trailing edge 10d, as shown in FIG. 3. The skin 10 functions to form a streamlined outer surface of the wing 1. Thus, the skeleton 20 is required to maintain the outer shape of the skin 10. The skeleton 20 of the wing 1 comprises a spar 20a and ribs 20b. The main spar 20a typically serves as the primary component of the wing 1 that carries the external loads. The rib 20b generally conforms to the shape of the airfoil and is used to support the skin 10 of the aircraft wing 1 and maintain the cross-sectional shape of the wing 1. The dimension of the spar 20a in the height direction is generally greater than the dimension of the rib 20b in the height direction, and the dimension of the rib 20b in the height direction is continuously variable. Thus, in the embodiment of the present application, the first section 10a and the second section 10b both extend from the front edge 10c toward the rear edge 10d, and gradually move away from each other and then gradually move together. Namely: the size of the cavity S of the skin 10 in the height direction, in the direction from the leading edge 10c to the trailing edge 10d (i.e. in the width direction), has a tendency to increase first and then decrease, forming a cavity S that fits the skeleton 20 and forms a streamlined outer surface of the wing 1.

In an embodiment, the first end 10-1 is located at the leading edge 10c; the second end portion 10-2 and the third end portion 10-3 are located at the trailing edge 10d. When installed, the spar 20a is disposed adjacent the leading edge 10c and the rib 20b is disposed adjacent the trailing edge 10d.

As an alternative to the above embodiment, the skin 10 is flexible. The flexible skin 10 has sufficient deformability to meet the deformation requirements of the wing 1, but at the same time the flexible skin 10 also needs to have sufficient rigidity to maintain the wing 1 shape and to withstand certain aerodynamic loads. In the embodiment, the material of the skin 10 is generally selected from a continuous fiber reinforced thermoplastic material so as to satisfy the deformation requirement of the wing 1, and also have sufficient rigidity to maintain the shape of the wing 1 and bear certain aerodynamic loads. Furthermore, the integrated flexible skin 10 facilitates assembly of the skeleton 20.

Based on at least one technical solution in the above embodiments, as shown in fig. 4, the embodiment of the present application further provides a wing 1, including: a skeleton 20 and a skin 10. The skin 10 adopts a part of or all of the technical solutions of the above embodiments, so that the wing 1 has technical advantages of the part of or all of the technical solutions of the above embodiments, which is not described herein again. The skeleton 20 is installed in the accommodating cavity S and connected to both the first section 10a and the second section 10b.

In a specific implementation process, the skeleton 20 is embedded in the accommodating cavity S from the two side ports of the skin 10, and two opposite surfaces of the skeleton 20 abut against the first section 10a and the second section 10b respectively. The skin 10 and the skeleton 20 may be fixed by riveting or gluing.

As an alternative to the above embodiment, as shown in fig. 4, the airfoil 1 further has a filling structure 30, and the filling structure 30 is disposed in the accommodating cavity S and is close to the leading edge 10c of the airfoil 1. Since the first section 10a and the second section 10b are distanced from one another at the front edge 10c of the skin 10, a deformation is easily produced at the front edge 10c, for which purpose a filling structure 30 is provided in the receiving space S close to the front edge 10c of the skin 10. The filling structure 30 has a stiffening effect to ensure that the strength of the skin 10 is sufficient to ensure that the shape and size of the housing cavity S are unchanged. In general, the filler structure 30 may be integrally formed with the skin 10 as the skin 10 is being molded.

It should be noted that the filling structure 30 is an alternative structure of the wing 1. In some embodiments, the wing 1 may be provided without the filler structure 30 when the skin 10 has sufficient strength. For example, when the skin 10 is made of a continuous fiber reinforced thermoplastic skin 10, the filling structure 30 may not be provided in the receiving cavity S.

As an alternative to the above embodiment, as shown in fig. 5, the framework 20 includes a main beam 20a and a plurality of ribs 20b, and the ribs 20b are spaced apart from each other and disposed on the same side of the main beam 20 a; wherein the spar 20a and ribs 20b each support the first section 10a and second section 10b. Generally, the ribs 20b are of the same shape and size. The ribs 20b are typically formed by die cutting or are cut from a lightweight sheet. A plurality of ribs 20b are each located on the side of the spar 20a facing the trailing edge 10d of the skin 10. The ribs 20b may be glued or riveted to the main beam 20 a.

In a specific implementation process, two opposite surfaces of the main beam 20a are respectively connected with the first section 10a and the second section 10b, and two opposite surfaces of the rib 20b are also respectively connected with the first section 10a and the second section 10b, so as to support the skin 10. Typically, the rib 20b has a streamlined surface and, therefore, the first section 10a has a streamlined inner surface to facilitate a sufficient fit with the rib 20b.

As an alternative to the above embodiment, the main beam 20a is a uniform cross-section beam. The beam with the uniform cross section is as follows: i.e. a beam body with the same cross-sectional dimension at any point along the length of the beam. The main beam 20a has the same shear resistance in a section at any position of the beam length. Typically, the main beam 20a is a hollow structure.

In the embodiment, the main beam 20a generally uses a carbon tube with a uniform cross section as a shear web. The main beam 20a is integrally formed. The main beam 20a is manufactured by adopting an integral rapid forming process, and compared with an assembly beam, the main beam has high manufacturing efficiency and better mechanical property. The main beam 20a may use an epoxy weave pultrusion process or a winding process or a rolling process, or reinforce the carbon tubes using a thermoplastic material.

When the wing 1 provided by the embodiment of the present application is manufactured, the following manufacturing process may be adopted: the main beam 20a and the wing ribs 20b are connected, then the manufactured framework 20 is embedded into the accommodating cavity S, the framework 20 and the skin 10 are fixed, after the internal wire installation of the unmanned aerial vehicle is completed, the second end portion 10-2 and the third end portion 10-3 are riveted or hinged to close the opening O at the position of the rear edge 10d, and the wing 1 is manufactured.

The embodiment of the application further provides an unmanned aerial vehicle, including: fuselage and wing 1, wing 1 installs on the fuselage. Wherein, wing 1 has adopted some technical scheme or all technical scheme in the above-mentioned embodiment, therefore this unmanned aerial vehicle possesses some technical scheme or all technical scheme's in the above-mentioned embodiment technical advantage. The unmanned aerial vehicle also comprises a power device arranged on the wing 1. The power means may be provided as a propeller driven by a motor.

The skin, the wing and the unmanned aerial vehicle provided by the embodiment of the application are described in detail, a specific example is applied to explain the principle and the implementation mode of the utility model, and the description of the embodiment is only used for helping to understand the method and the core idea of the utility model; meanwhile, for those skilled in the art, according to the idea of the present invention, there may be some changes in the specific implementation and application scope, and to sum up, the content of the present specification should not be understood as a limitation to the present invention.

Claims (10)

1. A skin for a wing of a drone, comprising a first section and a second section integrally formed, the first section and the second section defining a housing cavity; the accommodating cavity is used for installing a framework of the wing.

2. The skin of claim 1, wherein the first and second sections have a common first end, and wherein the skin has an opening disposed distal from the first end.

3. The skin of claim 2, wherein the first section further has a second end opposite the first end; the second section further having a third end opposite the first end; the second end portion and the third end portion are arranged at an interval in a height direction to form the opening.

4. The skin of any one of claims 1 to 3, wherein the skin has a leading edge and a trailing edge; the first section and the second section extend from the front edge to the rear edge, and gradually get close to each other after gradually getting away from each other.

5. The skin of any one of claims 1 to 3, wherein the skin is flexible.

6. An airfoil, comprising:

a framework; and

the skin of any one of claims 1 to 5; the skeleton is installed in hold the intracavity to with first section and second section all are connected.

7. The wing as claimed in claim 6, further comprising a filler structure disposed within the pocket and proximate to a leading edge of the skin.

8. The wing of claim 6, wherein the skeleton comprises a main girder and a plurality of ribs spaced apart on the same side of the main girder;

wherein the spar and the ribs each support the first and second sections.

9. The wing of claim 8, wherein the spar is a constant section spar.

10. An unmanned aerial vehicle, comprising:

a body; and

an airfoil as claimed in any of claims 6 to 9, which is mounted on the fuselage.

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