CN212890896U

CN212890896U - Wing component with hollow lattice structure

Info

Publication number: CN212890896U
Application number: CN202021793531.8U
Authority: CN
Inventors: 石海; 黄斌; 袁宏伟; 安国进; 马磊; 袁世枢
Original assignee: Guizhou Aerospace Fenghua Precision Equipment Co Ltd
Current assignee: Guizhou Aerospace Fenghua Precision Equipment Co Ltd
Priority date: 2020-08-25
Filing date: 2020-08-25
Publication date: 2021-04-06
Anticipated expiration: 2030-08-25

Abstract

The utility model provides a fretwork lattice structure wing component, including airfoil main part, base, the inside fretwork lattice structure that is of airfoil main part, the base is connected in airfoil main part bottom. The hollow lattice structure enables the internal structure of the wing to be more dense, improves the uniformity of the strength and the mechanical property of the wing, and reduces the weight; the inner part and the outer part can be connected densely, so that the outer surface can be further finished, the smoothness of the surface of the wing is improved, and the aerodynamic performance under high-speed traveling is improved. Further, the hollow dot matrix is three-dimensional net-shaped, the hollow dot matrix and the airfoil main body are of an integrally formed structure, and 2 powder leakage holes are formed in the bottom end of the airfoil main body.

Description

Wing component with hollow lattice structure

Technical Field

The utility model relates to a wing, concretely relates to fretwork lattice structure wing component.

Background

With the development of modern technology, some important components in the fields of automobiles, aerospace and aviation have higher and higher light weight requirements. The light weight is satisfied, and meanwhile, the strength of the product is guaranteed. The traditional method for manufacturing lightweight members is a skin technique, i.e. machining and hollowing out plates or bars, or manufacturing a net frame by welding, and then riveting or welding skins on the outer surface of the net frame. Chinese patent publication No. CN109434380A discloses a method for forming a thickened lightweight missile wing skin, which comprises: the covering comprises an inner plate and an outer plate, the inner plate and the outer plate form a closed cavity through peripheral sealing welding, an upper forming die and a lower forming die are designed, the upper forming die is a plane, the lower forming die is provided with a cavity, the inner plate and the outer plate are arranged at the cavity joint of the lower forming die, the upper forming die and the lower forming die are placed into thermal forming equipment for diffusion welding after die assembly, acid washing is carried out after cooling, oxide skin is removed, and burrs are removed by polishing after cutting. The method improves the structural strength of the skin. However, the processing method is limited by the manufacturing of the skin, the smoothness of the surface of the part is difficult to improve, the aerodynamic requirements of automobiles, missiles and airplanes are difficult to meet in a high-speed traveling state, the oil consumption is influenced if the smoothness is low, and the attitude of the aircraft is influenced if the smoothness is high. And the construction method has complicated procedures and consumes a large amount of manpower and material resources.

SUMMERY OF THE UTILITY MODEL

In order to solve the technical problem, the utility model provides a fretwork lattice structure wing component.

The utility model discloses a following technical scheme can realize.

The utility model provides a fretwork lattice structure wing component, including airfoil main part, base, the inside fretwork lattice structure that is of airfoil main part, the base is connected in airfoil main part bottom.

Further, the hollow lattice is in a three-dimensional net shape.

Furthermore, the three-dimensional mesh comprises a plurality of cubic meshes, and each node of the cubic meshes is connected by a round rod along the edges of the cubes.

Furthermore, the side length of each square grid is 0.8-1 mm.

By adopting the arrangement, the geometrical structure of the hollow dot matrix is simple, the modeling and 3D printing time is saved, and meanwhile, the mass distribution and the mechanical property are uniform.

Further, the hollowed-out dot matrix and the airfoil main body are of an integrally formed structure.

Furthermore, the bottom end of the airfoil main body is provided with a powder leakage hole.

By adopting the arrangement, welding is not needed between the internal hollow lattice structure and the outer wall, and the integrity of the wing and the smoothness of the surface are enhanced.

Further, the diameter of the powder leakage hole is not less than 3 mm. Save the clear powder time of 3D after printing, improve manufacturing efficiency.

Further, the diameter of the powder leakage hole is 3mm, and correspondingly, the thickness of the airfoil main body is within 20 mm. The arrangement provides the optimal diameter of the powder leakage hole of the airfoil within the thickness of 20mm, reduces the workload of repair welding after powder cleaning, and reduces the welding stress and welding unevenness to the minimum.

Furthermore, the number of the powder leakage holes is 2, and the powder leakage holes are arranged at the positions which are not shielded by the base. The powder cleaning efficiency is greatly improved.

Further, the thickness from the edge of the hollowed-out dot matrix to the outer surface of the airfoil main body is 2-4 mm. By adopting the arrangement, the surface strength is ensured to be greater than the inside, and the weight is reduced to the maximum extent while the damage of the outer surface is effectively prevented.

The beneficial effects of the utility model reside in that:

the inner part of the wing is arranged into a hollow lattice structure, so that the inner structure is more dense, the strength and the mechanical property uniformity of the wing are improved, and the weight is reduced; the inner part and the outer part can be connected densely, so that the outer surface can be further subjected to finish machining, the difficulty is not higher than that of the surface finish machining of a solid part, the smoothness of the surface of the wing is improved, and the aerodynamic performance under high-speed traveling is improved.

Drawings

Fig. 1 is a schematic structural diagram of the present invention;

fig. 2 is an internal perspective view of the present invention;

fig. 3 is a side view of the present invention;

fig. 4 is an enlarged view of the hollow lattice nodes of the present invention.

In the figure: 1-an airfoil body; 2-a base; 3-a process block; 4-powder leakage hole; 5-hollowing out the dot matrix; 6-node; 7-round bar.

Detailed Description

The technical solution of the present invention is further described below, but the scope of the claimed invention is not limited to the described.

As shown in fig. 1-2, the structure of the present invention is schematically illustrated:

the utility model provides a fretwork dot matrix 5 structure wing component, including airfoil main part 1,

base

2, 1 inside fretwork dot matrix 5 structures that is of airfoil main part, base 2 is connected in 1 bottom of airfoil main part.

Further, the hollow lattice 5 is a three-dimensional net.

Further, as shown in fig. 4, which is an enlarged view of the nodes 6 of the three-dimensional mesh network, the three-dimensional mesh network includes a plurality of cubic grids, and each node 6 of the cubic grids is connected by a round bar 7 along a prism of a cube.

Furthermore, the side length of each square grid is 0.8-1 mm.

By adopting the arrangement, the geometrical structure of the hollow dot matrix 5 is simple, the modeling and 3D printing time is saved, and meanwhile, the mass distribution and the mechanical property are uniform.

Further, the hollow dot matrix 5 and the airfoil main body 1 are of an integrally formed structure.

Further, the bottom end of the airfoil main body 1 is provided with a powder leakage hole 4.

By adopting the arrangement, welding is not needed between the internal hollow lattice 5 structure and the outer wall, and the integrity and the surface smoothness of the wing are enhanced. According to the requirement of actual working conditions, the powder leakage hole 4 can be sealed by repair welding after powder cleaning.

Further, the diameter of the powder leakage hole 4 is not less than 3 mm. Save the clear powder time of 3D after printing, improve manufacturing efficiency.

Further, the diameter of the powder leakage hole 4 is 3mm, and correspondingly the thickness of the airfoil body 1 is within 20 mm.

When the thickness of the airfoil main body 1 is within 20mm, the diameter of the powder leakage hole 4 is 3mm, the maximum powder cleaning rate is reached, and the powder cleaning rate is not obviously improved by continuously increasing the diameter of the powder leakage hole 4. The arrangement provides the optimal diameter of the airfoil powder leakage hole 4 within 20mm of thickness, reduces the workload of repair welding after powder cleaning, and reduces the welding stress and welding unevenness to the minimum.

Furthermore, the number of the powder leakage holes 4 is 2, and the powder leakage holes are arranged at the positions which are not shielded by the base 2.

Compressed gas is blown in from one powder leakage hole 4 in the later powder cleaning stage, and the two powder leakage holes 4 are alternately performed, so that the powder cleaning efficiency is greatly improved.

Further, the thickness from the edge of the hollow dot matrix 5 to the outer surface of the airfoil main body 1 is 2-4 mm.

By adopting the arrangement, the surface strength is ensured to be greater than the inside, and the weight is reduced to the maximum extent while the damage of the outer surface is effectively prevented.

In order to carry out finish machining on the surface of the airfoil after manufacturing is finished, 2 process blocks 3 are arranged on the base 2 and used for clamping and positioning in the machining process, and the process blocks are removed by linear cutting after machining is finished.

The utility model discloses a selective laser melting 3D prints the manufacturing, and the preferred magnesium alloy that adopts prints for the space flight field, the at utmost has reduced wing weight, compares in solid construction, and the weight reduction reaches more than 70%. When the small-sized wing surface is manufactured, one or more surfaces can be reserved for repair welding after powder cleaning, and only the powder leakage hole 4 can be reserved; when a large wing surface is manufactured, the large wing surface can be respectively assembled and welded after being printed in blocks, because the thickness and the internal hollow lattice structure of each block are the same, the butt joint can be realized, the quality increase caused by the assembly and welding only exists at the joint, and the error is within an acceptable range; large-scale 3D printing equipment can also be adopted, and due to long printing time, nitrogen needs to be continuously introduced to replace protective gas in the printing process, so that the clean environment in the working cavity is kept.

Fig. 3 is a side view of the present invention, which is generally in the shape of a wing member, and is tapered from the bottom to the end, and the bottom end has a base 2 for mounting to the body. Fig. 1 to 4 are only for illustrating the structural features of the present invention, and should not be construed as limiting the specific shape of the present invention; indeed, the utility model discloses be not limited to specific airfoil shape, all parts that have the lightweight requirement such as aircraft airfoil, rudder face, guided missile airfoil, rudder face adopt the utility model discloses a structure all belongs to the utility model discloses a protection scope.

Claims

1. The utility model provides a fretwork lattice structure wing component which characterized in that: the novel airfoil comprises an airfoil main body (1) and a base (2), wherein the airfoil main body (1) is internally provided with a hollowed-out dot matrix (5) structure, and the base (2) is connected to the bottom end of the airfoil main body (1).

2. The openwork lattice structure airfoil member of claim 1, wherein: the hollow lattice (5) is in a three-dimensional net shape.

3. The openwork lattice structure airfoil member of claim 2, wherein: the three-dimensional mesh comprises a plurality of cubic meshes, and each node (6) of each cubic mesh is connected with each other by a round rod (7) along a cubic ridge.

4. The openwork lattice structure airfoil member of claim 3, wherein: the side length of each cubic grid is 0.8-1 mm.

5. The openwork lattice structure airfoil member of claim 1, wherein: the hollowed-out dot matrix (5) and the airfoil main body (1) are of an integrally formed structure.

6. The openwork lattice structure airfoil member of claim 5, wherein: and a powder leakage hole (4) is formed in the bottom end of the airfoil main body (1).

7. The openwork lattice structure airfoil member of claim 6, wherein: the diameter of the powder leakage hole (4) is not less than 3 mm.

8. The openwork lattice structure airfoil member of claim 7, wherein: the diameter of the powder leakage hole (4) is 3mm, and correspondingly, the thickness of the airfoil main body (1) is within 20 mm.

9. The openwork lattice structure airfoil member of claim 6, wherein: the number of the powder leakage holes (4) is 2, and the powder leakage holes are arranged at the positions which are not shielded by the base (2).

10. The openwork lattice structure airfoil member of claim 1, wherein: the thickness from the edge of the hollow dot matrix (5) to the outer surface of the airfoil main body (1) is 2-4 mm.