CN113443120A

CN113443120A - Unmanned aerial vehicle and wing thereof

Info

Publication number: CN113443120A
Application number: CN202010212678.1A
Authority: CN
Inventors: 高彤; 张卫红; 朱继宏; 邓可欣; 宋龙龙
Original assignee: Northwestern Polytechnical University
Current assignee: Northwestern Polytechnical University
Priority date: 2020-03-24
Filing date: 2020-03-24
Publication date: 2021-09-28

Abstract

The invention discloses an unmanned aerial vehicle and a wing thereof, wherein the wing comprises a main beam structure and a dimensional structure, and the dimensional structure comprises a dimensional net rack formed by combining a plurality of connecting rods. The dimension shape rack of space rack form can have higher rigidity and intensity, can satisfy the installation requirement of parts such as covering or payload completely for payload's installation area can not receive bearing capacity's restriction, also can improve unmanned aerial vehicle's continuation of the journey performance to this certain extent.

Description

Unmanned aerial vehicle and wing thereof

Technical Field

The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle and a wing thereof.

Background

The wings of the unmanned aerial vehicle generally comprise a main beam structure and a dimensional structure, wherein the dimensional structure is used for maintaining the aerodynamic shape of the wings, the existing dimensional structure mostly consists of ribs which are bent into a conical shape, the dimensional structure in the form can only meet the basic dimensional function generally, and if parts such as skins or payloads are mounted on the outer surfaces of the wings, the problem of insufficient bearing capacity occurs, so that the size of the payloads to be mounted is limited.

Therefore, how to provide a solution to overcome the above-mentioned drawbacks remains a technical problem to be solved by those skilled in the art.

Disclosure of Invention

The invention aims to provide an unmanned aerial vehicle and a wing thereof, wherein the dimensional structure of the wing of the unmanned aerial vehicle comprises a dimensional net rack, has relatively high bearing performance, and can meet the installation requirements of parts such as skins or effective loads.

In order to solve the technical problem, the invention provides a wing of an unmanned aerial vehicle, which comprises a main beam structure and a dimensional structure, wherein the dimensional structure comprises a dimensional net rack formed by combining a plurality of connecting rods.

The dimension shape rack of space rack form can have higher rigidity and intensity, can satisfy the installation requirement of parts such as covering or payload completely for payload's installation area can not receive bearing capacity's restriction, also can improve unmanned aerial vehicle's continuation of the journey performance to this certain extent.

Optionally, on a cross section perpendicular to the length direction of the wing, the net rack comprises a plurality of sub-racks which are divided along the circumferential direction, and at least two sub-racks which are adjacent to each other in the circumferential direction are directly connected.

Optionally, at least some of the circumferentially adjacent sub frames are connected by the main beam structure.

Optionally, a connection part is arranged at a connection part of the sub-frame and the main beam structure, and the main beam structure is connected with the connection part through gluing.

Optionally, the sub-frame is connected to the main beam structure by a tab and a bolt.

Optionally, the wiki structure further comprises a plurality of wiki ribs.

The invention further provides an unmanned aerial vehicle which comprises a vehicle body and wings, wherein the wings are the wings of the unmanned aerial vehicle.

Since the wings of the above-mentioned unmanned aerial vehicle already have the above technical effects, then, the unmanned aerial vehicle with the wings also has similar technical effects, and therefore, the details are not described herein.

Drawings

Fig. 1 is a schematic structural diagram of an embodiment of a wing of an unmanned aerial vehicle provided in the present invention;

FIG. 2 is a top view of FIG. 1;

FIG. 3 is a schematic structural view of a dimensional net rack;

FIG. 4 is a schematic diagram of a single cell of a wiki;

FIG. 5 is a split block diagram of one embodiment of a dimensional grid;

FIG. 6 is a schematic view of a sub-rack of FIG. 5;

FIG. 7 is a sectional view of another embodiment of the lattice frame;

fig. 8 is a schematic structural diagram of another embodiment of a wing of the drone provided by the present invention;

fig. 9 is a front view of fig. 8.

The reference numerals in fig. 1-9 are illustrated as follows:

1, a main beam structure;

2-dimensional structure, 21-dimensional net rack, 21a connecting rod, 211 split frame, 212 connecting component, 22-dimensional rib and 23 lug;

3 pitching the rudder.

Detailed Description

In order to make the technical solutions of the present invention better understood by those skilled in the art, the present invention will be further described in detail with reference to the accompanying drawings and specific embodiments.

As used herein, the term "plurality" refers to an indefinite number of plural, usually more than two; and when the term "plurality" is used to indicate a quantity of a particular element, it does not indicate a quantitative relationship between such elements.

Referring to fig. 1 to 9, fig. 1 is a schematic structural diagram of an embodiment of a wing of an unmanned aerial vehicle, fig. 2 is a top view of fig. 1, fig. 3 is a schematic structural diagram of a dimensional net rack, fig. 4 is a schematic structural diagram of a single cell of the dimensional net rack, fig. 5 is a structural diagram of a split body of an embodiment of the dimensional net rack, fig. 6 is a structural diagram of a split body of fig. 5, fig. 7 is a structural diagram of a split body of another embodiment of the dimensional net rack, fig. 8 is a structural diagram of another embodiment of the wing of the unmanned aerial vehicle, and fig. 9 is a front view of fig. 8.

The invention provides a wing of an unmanned aerial vehicle, which comprises a main beam structure 1 and a dimensional structure 2, wherein: the main beam structure 1 is used for providing rigidity support, and a specific structure of the main beam structure 1 is not limited in the embodiment of the present invention, and in implementation, a person skilled in the art may design the main beam structure according to actual needs, or may design the main beam structure with reference to the accompanying drawings, in the embodiment of fig. 1, the main beam structure 1 may be a truss beam structure, and in the embodiments of fig. 8 and 9, the main beam structure 1 may be a box beam structure; the dimensional structure 2 can form the external contour of the wing on the basis of the main beam structure 1, and then the complete wing can be formed by matching with parts such as skin and the like.

As described in the background section, the dimensional structure of the existing wing of the unmanned aerial vehicle mostly consists of ribs (the structure of which can be referred to as dimensional ribs 22 in fig. 1) bent into a cone shape, and the dimensional structure in this form can only meet the basic dimensional function generally, and if a skin or a payload or other parts are to be installed on the outer surface of the wing, the problem of insufficient bearing capacity occurs, and the size of the payload to be installed is further limited.

For this reason, as shown in fig. 1 to 4, the dimensional structure 2 in the embodiment of the present invention may include a dimensional grid 21 formed by combining a plurality of connecting rods 21a, and the dimensional grid 21 in the form of a spatial grid may have high rigidity and strength, and may completely meet the installation requirements of components such as a skin or a payload, so that the installation area of the payload is not limited by the bearing capacity, and the cruising performance of the unmanned aerial vehicle may also be improved to a certain extent. The skin mainly comprises a film skin and a metal skin, the thickness of the skin is set according to needs, and the effective load refers to a load mounted on a wing, and can be a solar panel and the like.

Moreover, the weight of the dimensional net rack 21 is light, so that excessive burden is not generated on the weight of the wings, and the design requirement of light weight of the wings of the unmanned aerial vehicle can be met.

In addition, the enclosure net rack 21 in the form of a space net rack is an independent modularized structure, is easy to produce and process, can form more various forms, is provided with different main beam structures 1, and can easily change the external shape of the wings of the unmanned aerial vehicle.

The specific structural form of the dimensional net frame 21 is not limited herein, and those skilled in the art can determine the specific structural form according to actual needs when implementing the method. In an exemplary embodiment, the dimensional grid 21 may be formed by topologically extending a specific unit cell structure along a designated direction, the unit cell structure is not limited, and the unit cell may include two rectangular pyramids arranged opposite to each other and four links 21a distributed circumferentially, as referred to in fig. 4.

With reference to fig. 5 to 9, in a cross section perpendicular to the length direction of the wing, the net frame 21 may include a plurality of sub-frames 211 divided along the circumferential direction, and each sub-frame 211 extends along the length direction of the wing, so that each sub-frame 211 is not a closed structure in the circumferential direction, and the size of each sub-frame 211 may be small, which may facilitate processing, so as to reduce the processing difficulty. The processing technology of each sub-frame 211 can be specifically 3D printing technology.

For each sub-frame 211, at least a part of two sub-frames 211 adjacent to each other in the circumferential direction may be connected by the main beam structure 1, and at this time, a part of the main beam structure 1 may be located between two adjacent sub-frames 211, and the sub-frame 211 in this structure form may be as shown in fig. 5; and/or, two sub-frames 211 that are at least partially circumferentially adjacent may be directly connected, and a specific connection manner may be gluing, in this case, the main beam structure 1 may be installed and fixed in each sub-frame 211, and in this structure form of the sub-frames 211, as shown in fig. 7, each sub-frame 211 may be provided with an installation groove for fixing the main beam structure 1.

The connection part of each sub-frame 211 and the main beam structure 1 may be provided with a connection part 212, and with reference to fig. 6, the connection part 212 may be a solid plate-shaped structure or the like, different from the net-shaped structure of the net frame 21 itself, so as to ensure the reliable connection between the main beam structure 1 and the sub-frame 211, and the specific connection process may be gluing. Alternatively, as shown in fig. 8 and 9, the main beam structure 1 and each sub-frame 211 may be fixed by using mechanical connectors in the form of tabs 23 and bolts (not labeled in the figures), and the arrangement position of the tabs 23 is not limited in detail here as long as the technical effect of reliable fixation can be satisfied; in addition, but also can set up the coupling mechanism of quick assembly disassembly such as joint part between girder structure 1 and dimension shape structure 2, like this, can also improve the speed of dismouting under the prerequisite of guaranteeing the two reliability of connecting.

It should be noted that although the embodiment of the present invention relates to a dimensional structure 2 including a dimensional grid 21, this does not mean that the wing of the drone provided by the present invention can only adopt this form of dimensional structure 2, and when the requirement on the carrying performance of the wing itself is not high, the dimensional structure 2 can also adopt a conventional dimensional rib 22; alternatively, the aforementioned dimensional net rack 21 and dimensional ribs 22 may be used together and arranged in segments in the length direction of the wing, for example, the dimensional net rack 21 may be used as the dimensional structure 2 in the portion of the wing close to the fuselage to increase the overall stiffness of the wing, and the dimensional ribs 22 may be distributed at the wing tip of the wing.

In fact, as shown in fig. 2, the dimensional net frame 21 may be provided with dimensional ribs 22 inside to support the dimensional net frame 21, and at the same time, the sectional design of the dimensional net frame 21 in the wing length direction may be facilitated.

Besides the above components, the wings of the unmanned aerial vehicle are generally provided with the pitching rudder 3, and the structure of the pitching rudder 3 and the installation control structure thereof and the like can refer to the prior art, which is not described herein.

The invention further provides an unmanned aerial vehicle which comprises a vehicle body and wings, wherein the wings are the wings of the unmanned aerial vehicle related to the above embodiments.

The foregoing is only a preferred embodiment of the present invention, and it should be noted that it is obvious to those skilled in the art that various modifications and improvements can be made without departing from the principle of the present invention, and these modifications and improvements should also be considered as the protection scope of the present invention.

Claims

1. The utility model provides an unmanned aerial vehicle's wing, includes girder structure (1) and dimension shape structure (2), its characterized in that, dimension shape structure (2) include dimension shape rack (21) that a plurality of connecting rods (21a) combination formed.

2. The wing of the unmanned aerial vehicle of claim 1, characterized in that, in a cross section perpendicular to the length direction of the wing, the net frame (21) comprises a plurality of sub frames (211) which are divided along the circumferential direction, and two sub frames (211) which are at least partially adjacent to each other along the circumferential direction are directly connected.

3. Wing of a drone according to claim 2, characterized in that two sub-frames (211) at least partially circumferentially adjacent are connected by the main beam structure (1).

4. The wing of the unmanned aerial vehicle of claim 3, wherein a connecting part (212) is arranged at the connecting part of the sub-frame (211) and the main beam structure (1), and the main beam structure (1) is connected with the connecting part (212) through gluing.

5. The wing of the drone of claim 3, wherein the sub-frame (211) is connected to the main beam structure (1) by tabs (23) and bolts.

6. Wing of a drone according to any one of claims 1 to 5, characterized in that the dimensional structure (2) further comprises several dimensional ribs (22).

7. An unmanned aerial vehicle comprising a fuselage and a wing, wherein the wing is a wing of the unmanned aerial vehicle of any one of claims 1-6.