CN113443121A - Unmanned aerial vehicle and wing thereof - Google Patents

Abstract

The invention discloses an unmanned aerial vehicle and a wing thereof, wherein the wing comprises a main beam structure and a dimensional structure, the main beam structure comprises a plurality of layers of beam frames which are distributed at intervals along the vertical direction, each beam frame comprises a plurality of longitudinal beams which extend along the length direction of the wing, two adjacent longitudinal beams of the same layer of beam frame are connected through a connecting beam, two adjacent beam frames are connected through a web beam, and at least the beam frame at the uppermost layer and the beam frame at the lowermost layer are connected with the dimensional structure. So set up, the girder structure adopts the space truss structure that a plurality of split type longerons, even roof beam and web member combination formed, and intensity and rigidity are all higher for the wing can keep sufficient rigidity in the course of the work, and compares in prior art, and the quality of above-mentioned girder structure is lighter, more can satisfy light-weighted design requirement.

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

Unmanned aerial vehicle for pursuing long endurance performance, require fuselage structural design to lighten weight as far as possible when satisfying intensity and rigidity demand to improve the effective task load capacity.

The wings of the traditional unmanned aerial vehicle mostly adopt a structure similar to that of the unmanned aerial vehicle, the structure comprises a large-size round or square main beam, and then parts such as skins, wing ribs and the like are installed on the basis of the main beam.

Therefore, how to provide a light unmanned aerial vehicle wing remains a technical problem to be solved urgently by technical personnel in the field.

Disclosure of Invention

The invention aims to provide an unmanned aerial vehicle and a wing thereof, wherein the wing of the unmanned aerial vehicle can meet the design requirement of light weight.

In order to solve the technical problem, the invention provides an unmanned aerial vehicle wing which comprises a main beam structure and a dimensional structure, wherein the main beam structure comprises a plurality of layers of beam frames distributed at intervals along the vertical direction, each beam frame comprises a plurality of longitudinal beams extending along the length direction of the wing, two adjacent longitudinal beams of the same layer of beam frame are connected through connecting beams, two adjacent beam frames are connected through web beams, and at least the uppermost layer of beam frame and the lowermost layer of beam frame are connected with the dimensional structure.

So set up, the girder structure adopts the space truss structure that a plurality of split type longerons, even roof beam and web member combination formed, and intensity and rigidity are all higher for the wing can keep sufficient rigidity in the course of the work, and compares in prior art, and the quality of above-mentioned girder structure is lighter, more can satisfy light-weighted design requirement.

Optionally, the web member is used for connecting the longitudinal beams of two adjacent beam frames.

Optionally, the number of the longitudinal beams of each beam frame is the same, the longitudinal beams of two adjacent layers of beam frames are correspondingly connected one by one, and the surfaces of the center lines of the two longitudinal beams correspondingly connected with each other of the two adjacent layers of beam frames are perpendicular to the chord length direction of the wing.

Optionally, the longitudinal beam and the web beam and the longitudinal beam and the connecting beam of the beam frame on the same layer are connected through joints.

Optionally, the longitudinal beams and/or the webs and/or the web beams and/or the joints are formed by a filament winding process; and/or the joint is connected with other components by gluing.

Optionally, the dimensional structure comprises a dimensional net rack formed by combining a plurality of connecting rods.

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, at least two of the sub-racks which are adjacent to each other in the circumferential direction are directly connected, and/or at least two of the sub-racks which are adjacent to each other in the circumferential direction are connected through the longitudinal beam.

Optionally, a connecting part is arranged at the connecting part of the sub-frame and the longitudinal beam, and the longitudinal beam is connected with the connecting part through gluing.

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 schematic structural view of one embodiment of a beam mount;

FIG. 3 is a schematic illustration of another embodiment of a beam mount;

FIG. 4 is a schematic structural view of yet another embodiment of a beam mount;

FIG. 5 is a view showing a connection structure of a main beam and a web beam;

FIG. 6 is a connection structure view of the main beam, the web beam and the dimensional structure;

FIG. 7 is a schematic view of the structure of the net frame;

FIG. 8 is a schematic diagram of a single cell of a wiki;

FIG. 9 is a split block diagram of one embodiment of a dimensional grid;

FIG. 10 is a schematic view of a sub-rack of FIG. 9;

FIG. 11 is a sectional view of another embodiment of the lattice frame;

FIG. 12 is a schematic view of a sub-rack of FIG. 11;

fig. 13 is a top view of fig. 1.

The reference numerals in fig. 1-13 are illustrated as follows:

1 main beam structure, 11 beam frames, 111 longitudinal beams, 112 connecting beams, 12 web beams and 13 joints;

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

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, fig. 1 is a schematic structural diagram of an embodiment of a wing of an unmanned aerial vehicle according to the present invention.

As shown in fig. 1, the present invention provides a wing of an unmanned aerial vehicle, including a main beam structure 1 and a dimensional structure 2, wherein the main beam structure 1 is used for providing rigidity support, and the dimensional structure 2 can form an external contour of the wing by enclosing the main beam structure 1 as a base, and then cooperate with components such as a skin, so as to form a complete wing.

Different from the prior art, in the embodiment of the present invention, the main beam structure 1 includes a plurality of layers of beam frames 11 distributed at intervals in the up-down direction, each beam frame 11 includes a plurality of longitudinal beams 111 extending in the length direction of the wing, two adjacent longitudinal beams 111 of the same layer of beam frame 11 are connected by a connecting beam 112, two adjacent beam frames 11 are connected by a web beam 12, and at least the uppermost layer of beam frame 11 and the lowermost layer of beam frame 11 are connected to the dimensional structure 2.

So set up, girder structure 1 adopts the space truss structure that a plurality of split type longerons 111, even roof beam 112 and web member 12 combination formed, and intensity and rigidity are all higher for the wing can keep sufficient rigidity in the course of the work, and compares in prior art, and above-mentioned girder structure 1's quality is lighter, more can satisfy light-weighted design requirement.

In the embodiment of the present invention, the number of layers of beam frames 11 is not limited, and is specifically related to parameters such as the size of the wing, and in the scheme of the accompanying drawings, the beam frames 11 may be arranged in two layers, and the beam frames 11 in the upper and lower layers may be connected to the dimensional structure 2; in addition, the embodiments of the present invention are not limited to the structure of the beam frame 11 and the connection structure between the beam frame 11 and the web 12, and those skilled in the art can design the structures of the above-described parts according to actual needs.

In a specific scheme, please refer to fig. 2-6, fig. 2 is a schematic structural diagram of an embodiment of a beam frame, fig. 3 is a schematic structural diagram of another embodiment of the beam frame, fig. 4 is a schematic structural diagram of another embodiment of the beam frame, fig. 5 is a structural diagram of a connection structure of a main beam and a web beam, and fig. 6 is a structural diagram of a connection structure of the main beam, the web beam and a dimensional structure.

The longitudinal beams 111 of the beam frame 11 in the same layer can be arranged side by side, two adjacent longitudinal beams 111 can be connected through the connecting beam 112, and the structural form of the connecting beam 112 can be various and is specifically related to the number of the longitudinal beams 111, the distance between the adjacent longitudinal beams 111 and other parameters.

By way of exemplary illustration, fig. 2 shows a y-shaped coupling beam 112, which can be used for the connection of the 5 stringers 111 shown in the drawings; fig. 3 shows a diagonal tie-beam 112, which can be adapted to the connection of the 3 stringers 111 shown in the drawings; fig. 4 shows a V-shaped coupling beam 112, which is suitable for connecting two longitudinal beams 111 shown in the figure.

The web beam 12 can be used for connecting the longitudinal beams 111 of two adjacent beam frames 11, that is, both ends of the web beam 12 can be connected with the longitudinal beams 111 of different layers of beam frames 11, and it can be known that the longitudinal beam 111 is a main structure of each layer of beam frame 11, and the web beam 12 is directly connected with the longitudinal beam 111, so that the overall rigidity of the whole main beam structure 1 can be improved. Of course, the web 12 may be connected to other parts of the beam 11, such as the connecting beam 112.

The number of the stringers 111 in each layer of beam frames 11 may be the same or different, and may be determined according to actual conditions.

In the embodiment of fig. 6, the number of the longitudinal beams 111 of each beam frame 11 may be the same, the longitudinal beams 111 of two adjacent beam frames 11 may be connected in one-to-one correspondence, and the plane of the central line of the two longitudinal beams 111 connected in correspondence to the two adjacent beam frames 11 may be perpendicular to the chord length direction of the wing (the width direction of the wing, the left-to-right direction in fig. 6), so that the longitudinal beams 111 may be connected in one-to-one correspondence in the up-and-down direction, the mounting surface of each web beam 12 may also be perpendicular to the chord length direction, and the main beam structure 1 has good integrity and high rigidity. In addition, the longitudinal beams 111 in each layer of beam frames 11 may not be vertically aligned, and in this case, the attachment surface of each web beam 12 forms an angle other than 90 degrees with the chord direction.

The longitudinal beam 111 and the web beam 12 and the longitudinal beam 111 and the web beam 112 of the same layer of beam frames 11 can be connected by the joint 13, specifically, the joint 13 can be connected with other components by gluing process, and the longitudinal beam 111 and/or the web beam 112 and/or the web beam 12 and/or the joint 13 can be formed by fiber winding process.

Referring to fig. 7-12, fig. 7 is a schematic structural view of a net frame, fig. 8 is a schematic structural view of a single cell of the net frame, fig. 9 is a structural view of a split body of an embodiment of the net frame, fig. 10 is a structural view of a split frame of fig. 9, fig. 11 is a structural view of a split body of another embodiment of the net frame, and fig. 12 is a structural view of a split frame of fig. 11.

The dimensional structure 2 is used for cooperating with the main girder structure 1 to construct the outer contour shape of the wing, and the conventional dimensional structure 2 usually only comprises the dimensional ribs 22 shown in fig. 1, and the structural strength of the dimensional structure 2 is low, so that the dimensional structure can only meet the basic dimensional function, and if a skin or a payload and the like are installed on the outer surface of the wing, the bearing capacity is insufficient, so that the size of the payload to be installed is limited. 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.

Therefore, as shown in fig. 7 and with reference to fig. 1, 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 higher 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 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. 8.

With reference to fig. 9-12, 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. The processing technology of each sub-frame 211 can specifically adopt a 3D printing technology.

For each sub-frame 211, two sub-frames 211 that are at least partially circumferentially adjacent to each other may be connected by a longitudinal beam 111, in this case, each longitudinal beam 111 in the aforementioned main beam structure 1 may be located between two adjacent sub-frames 211, and this structural form of the sub-frame 211 may be referred to fig. 9; 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, each longitudinal beam 111 in the main beam structure 1 may be mounted to each sub-frame 211, and this structural form of the sub-frame 211 may be as shown in fig. 11.

The connecting part 212 may be provided at the connecting part between each sub-frame 211 and the longitudinal beam 111, and in combination with fig. 10, the connecting part 212 may be a solid plate-shaped structure, etc. to ensure the reliable connection between the longitudinal beam 111 and the sub-frame 211, unlike the net structure of the net frame 21 itself, and the specific connecting process may be gluing, or as shown in fig. 12, a mechanical connecting part in the form of a tab, a bolt (not shown), etc. may be used to fix between the longitudinal beam 111 and the connecting part 212.

It should be noted that although the embodiment of the present invention provides 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, referring to fig. 13 and fig. 13 being a top view of fig. 1, as shown in fig. 13, the inner portion of the net frame 21 is also provided with net ribs 22 to support the net frame 21, and at the same time, the sectional design of the net frame 21 in the wing length direction can 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.

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.

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 (10)

1. The utility model provides an unmanned aerial vehicle's wing, includes girder structure (1) and dimension shape structure (2), its characterized in that, girder structure (1) includes a plurality of layers roof beam structure (11) along upper and lower direction interval distribution, each roof beam structure (11) all includes the edge a plurality of longerons (111) that the length direction of wing extends, same layer the adjacent two of roof beam structure (11) link to each other through linking roof beam (112) between longeron (111), adjacent two link to each other through web member (12) between roof beam structure (11), at least the superiors roof beam structure (11) and the bottommost roof beam structure (11) with dimension shape structure (2) link to each other.

2. The wing of the drone of claim 1, wherein the web (12) is intended to connect the stringers (111) of two adjacent beams (11).

3. The wing of the unmanned aerial vehicle as claimed in claim 2, wherein the number of the longitudinal beams (111) of each beam frame (11) is the same, the longitudinal beams (111) of two adjacent layers of beam frames (11) are correspondingly connected one by one, and the plane of the center lines of the two longitudinal beams (111) of two adjacent layers of beam frames (11) which are correspondingly connected is perpendicular to the chord length direction of the wing.

4. The wing of the unmanned aerial vehicle of claim 2, characterized in that the longitudinal beam (111) and the web beam (12) and the longitudinal beam (111) and the connecting beam (112) of the beam frame (11) on the same layer are connected through a joint (13).

5. The wing of the drone of claim 4, characterized in that the stringers (111) and/or the tie-beams (112) and/or the web-beams (12) and/or the joints (13) are shaped by a filament winding process; and/or the presence of a gas in the gas,

the joint (13) is connected to the other components by gluing.

6. Wing of a drone according to any one of claims 1 to 5, characterised in that the dimensional structure (2) comprises a dimensional grid (21) formed by a combination of several links (21 a).

7. The wing of the unmanned aerial vehicle of claim 6, characterized in that, in a cross section perpendicular to the length direction of the wing, the dimensional net rack (21) comprises a plurality of sub-racks (211) which are divided along the circumferential direction, two sub-racks (211) which are at least partially adjacent along the circumferential direction are directly connected, and/or two sub-racks (211) which are at least partially adjacent along the circumferential direction are connected through the longitudinal beam (111).

8. The wing of the unmanned aerial vehicle of claim 7, characterized in that the connecting part of the sub-frame (211) and the longitudinal beam (111) is provided with a connecting part (212), and the longitudinal beam (111) is connected with the connecting part (212) through gluing.

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

10. 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 1-9.

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