CN217575589U - Wingtip structure, wing, aircraft and composite tip structure - Google Patents

Abstract

The utility model discloses a wing tip structure, the wing, aircraft and combined material point structure, this wing tip structure is fibre preimpregnation material shaping structure, wing tip edges and corners including the bed die shaping, the tip of this wing tip edges and corners includes the outer fibrous structure of time by outermost fibrous layer and inlayer fibrous layer cartridge, wherein this time outer fibrous structure is flowing fibre preimpregnation material shaping structure, it utilizes its mobility self-adaptation to realize the good laminating to the tip of wing tip edges and corners in the curing forming process, form the good surface characteristic who corresponds with the shaping bed die, the probability that gap or long-pending glue appear in the tip that has reduced wing tip edges and corners, the structural reliability of product has been improved. The aircraft comprises the wing, the wing comprises the wing tip structure, and the wing has the advantages of few structural surface defects, high reliability and good safety. The composite material has good surface quality, few defects and high product structure reliability.

Description

Wingtip structure, wing, aircraft and composite tip structure

Technical Field

The utility model relates to a material structure technical field specifically, relates to wing tip structure, wing, aircraft and combined material most advanced structure.

Background

Compared with a metal wingtip structure, the composite wingtip structure has the advantages of good structure weight reduction, corrosion resistance, vibration cracking resistance and the like.

As shown in fig. 1, the wing tip structure 100 includes a wing tip corner 110, and due to the characteristic of the laying process of the fiber prepreg, when a female mold is used for molding, as shown in fig. 2, the wing tip structure 100 is molded on the inner wall of the molding female mold 20, a gap or an adhesive deposit defect may be formed at an end 111 of the wing tip corner 110, and after the appearance is repaired, there is a certain risk of local falling off.

SUMMERY OF THE UTILITY MODEL

In view of the above problem, the utility model aims at providing a wing tip structure, wing, aircraft and combined material point end structure to reduce the fashioned fiber material point end of bed die and produce the probability of gap or long-pending gluey defect, improve product surface quality, reduce the local risk of droing of structure.

According to one aspect of the utility model, a wing tip structure is provided,

the wingtip structure is a fiber prepreg forming structure and comprises wingtip edges, the wingtip edges are female die forming structures,

the end part of the wingtip corner comprises a secondary outer layer fiber structure which is wrapped and clamped by an outermost layer fiber layer and an inner layer fiber layer, the outermost layer fiber is arranged corresponding to the inner surface of the fitting forming female die, wherein,

the secondary outer layer fiber structure is a flowing fiber prepreg forming structure and is correspondingly arranged at the top end of the tip edge angle of the wing tip.

Optionally, the outermost fibrous layer is of a lap-laid construction.

Optionally, the wing tip structure is a carbon fiber plain cloth fabric prepreg molding structure.

Optionally, the wing tip structure is a fiberglass unidirectional tape prepreg molded structure.

Optionally, the tip of the tip corner is rounded.

Optionally, the wing tip structure is a unitary cured moulded structure.

According to an aspect of the utility model, provide a wing, include:

according to the utility model provides a wing tip structure.

According to an aspect of the present invention, there is provided an aircraft, comprising:

according to the utility model provides a wing.

According to one aspect of the utility model, a composite material tip structure is provided,

comprises a tip structure formed by a female die, the tip structure comprises a secondary outer layer fiber structure which is sandwiched by an outermost layer fiber layer and an inner layer fiber layer, the outermost layer fiber layer is arranged corresponding to the inner surface of the female die for laminating and forming, wherein,

the secondary outer layer fiber structure is a flowing fiber prepreg forming structure and is correspondingly arranged at the top end of the end part of the tip structure.

Optionally, the outermost fibrous layer is of a lap-laid construction.

The utility model provides a wing tip structure is fibre preimpregnation material shaping structure, including the fashioned wing tip edges and corners of bed die, the tip of this wing tip edges and corners includes the inferior outer fibrous structure of being pressed from both sides by outermost fibrous layer and inlayer fibrous layer package, wherein this time outer fibrous structure is flowing fibre preimpregnation material shaping structure, it utilizes its mobility self-adaptation to realize the good laminating to the tip of wing tip edges and corners in the curing molding process, form the good surface characteristic who corresponds with the shaping bed die, the probability that gap or long-pending glue appear in the tip that has reduced wing tip edges and corners, the structure reliability of product has been improved.

The outermost fiber layer is of a lap joint paving and pasting structure, so that the forming influence of the toughness of fiber materials on the end parts of the wing tip edges can be reduced, the probability of generating gaps of the wing tip edges is further reduced, and the reliability of the product structure is improved.

The utility model also provides a wing and aircraft, this aircraft include this wing, and this wing includes this wingtip structure, can improve the reliability of wing and aircraft, improves the navigation security.

Drawings

The above and other objects, features and advantages of the present invention will become more apparent from the following description of the embodiments of the present invention with reference to the accompanying drawings, in which:

FIG. 1 shows a schematic structural view of a wing tip structure according to the prior art;

FIG. 2 shows a schematic view of a sectional structure of a wing tip structure according to the prior art;

fig. 3 shows a schematic end structure view of a wing tip structure according to an embodiment of the invention;

fig. 4 shows a schematic view of a tangential plane structure of a wing tip structure according to an embodiment of the invention.

Detailed Description

Various embodiments of the present invention will be described in more detail below with reference to the accompanying drawings. In the various figures, like elements are identified with the same or similar reference numerals. For purposes of clarity, the various features in the drawings are not drawn to scale.

The following detailed description of the embodiments of the present invention is made with reference to the accompanying drawings and examples.

Fig. 3 shows an end structure schematic diagram of a wing tip structure according to an embodiment of the present invention, and fig. 4 shows a tangent plane structure schematic diagram of a wing tip structure according to an embodiment of the present invention.

As shown in fig. 3 and 4, the wingtip corner 210 of the wingtip structure 200 of the embodiment of the present invention includes an outermost fiber layer 211, a second outer fiber structure 212 and an inner fiber layer 213, and the outermost fiber layer 211 and the inner fiber layer 213 are disposed by sandwiching the second outer fiber structure 212, wherein the second outer fiber structure 212 is a flowing fiber prepreg forming structure and is correspondingly disposed at the tip top end of the wingtip corner 210.

In the molding process of the wing tip structure 200, the fiber prepreg of the outermost fiber layer 211 is laid on the inner wall of the molding female mold 20 (i.e., corresponding to the wing tip corner 210 of the wing tip structure 200), then the flowing fiber prepreg of the secondary outer fiber layer 212 is laid at the top end position corresponding to the wing tip corner 210 of the wing tip structure 200, then the subsequent laying of the fiber prepreg of the inner fiber layer 213 is performed, and after the laying is completed, the whole is heated and cured to obtain the wing tip structure 200 of the integrally cured molded structure as shown in fig. 4.

Wherein, the whole solidification structure is convenient for in the curing process that adds, mobility through time outer fibrous structure 212, outermost fibrous layer 211, time outer fibrous structure 212 and inlayer fibrous layer 213 adaptability match, realize closely laminating to each layer fibrous layer of wingtip edges and corners 210 of wingtip structure 200, and its mobility has ensured the tip of wingtip edges and corners 210 and the matching of the tip in shaping bed die 20, the probability of the production gap or the long-pending gluey defect of the tip of wingtip edges and corners 210 after the solidification moulding has been reduced, reduce the outward appearance amount of repairing, avoid repairing the damage to the fibre, the wingtip structure has been reduced.

Claims (10)

1. A wing tip structure is characterized in that,

the wingtip structure is a fiber prepreg forming structure and comprises wingtip edges, the wingtip edges are female die forming structures,

the end part of the wingtip edge angle comprises a secondary outer layer fiber structure which is wrapped and clamped by an outermost layer fiber layer and an inner layer fiber layer, the outermost layer fiber is arranged corresponding to the inner surface of the attaching forming female die, wherein,

the secondary outer layer fiber structure is a flowing fiber prepreg forming structure and is correspondingly arranged at the top end of the tip edge angle of the wing tip.

2. The wing tip structure of claim 1,

the outermost fiber layer is of a lap joint paving structure.

3. The wing tip structure of claim 1,

the wingtip structure is a carbon fiber plain cloth fabric prepreg forming structure.

4. The wing tip structure of claim 1,

the wing tip structure is a glass fiber unidirectional tape prepreg forming structure.

5. The wing tip structure of claim 1,

the top end of the end part of the wingtip edge is of a round angle structure.

6. The wing tip structure of claim 1,

the wing tip structure is an integral curing molding structure.

7. An airfoil, comprising:

the wing tip structure of any of claims 1 to 6.

8. An aircraft, characterized in that it comprises:

an airfoil as claimed in claim 7.

9. A composite tip structure characterized by,

comprises a tip structure formed by a female die, the tip structure comprises a secondary outer layer fiber structure which is sandwiched by an outermost layer fiber layer and an inner layer fiber layer, the outermost layer fiber layer is arranged corresponding to the inner surface of the female die for laminating and forming, wherein,

the secondary outer layer fiber structure is a flowing fiber prepreg forming structure and is correspondingly arranged at the top end of the end part of the tip structure.

10. The composite tip structure of claim 9,

the outermost fiber layer is of a lap joint paving structure.

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