A wing trailing edge wedge honeycomb sandwich structure

Abstract

This utility model belongs to the field of aircraft structural design technology, and relates to a wedge-shaped honeycomb sandwich structure for the trailing edge of a wing. It includes a first skin and a second skin arranged opposite each other, which connect to form a "V"-shaped space. Within the "V"-shaped space, a trailing edge strip, a honeycomb core, and a front sparsity are distributed sequentially from bottom to top. The trailing edge strip has a triangular prism structure, and its bottom surface is fixedly connected to the small end face of the honeycomb core, while the large end face of the honeycomb core is fixedly connected to the front sparsity. By filling the triangular space enclosed by the honeycomb core and the first and second skins with the trailing edge strip, the strength of the trailing edge flap structure at the sharp corner is enhanced. Furthermore, due to the use of the trailing edge strip as filler, the machining of the formed honeycomb core is eliminated, effectively avoiding the problem of difficult processing of sharp-cornered honeycomb cores. The third skin is a prepreg continuous fiber cloth; after the entire fabric is laid on the first and second skins, the strength at the sharp corner connection is increased, enabling the trailing edge flap structure to meet more demanding service environments.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft structural design technology, and relates to a wedge-shaped honeycomb sandwich structure for the trailing edge of an airfoil. Background Technology

[0002] The application of advanced composite materials in aircraft structures has a history of over 30 years. Currently, composite materials account for 25% to 40% of the total weight of military aircraft abroad, 10% to 15% of civilian aircraft, and over 60% of helicopters. Among them, composite honeycomb sandwich structures are widely used due to their advantages such as light weight, high specific strength, high specific stiffness, outstanding corrosion resistance and flame retardancy, excellent environmental resistance and insulation, good electromagnetic transmission and high temperature stability.

[0003] As a critical control component on the wing's trailing edge, the trailing edge flap, although not a primary load-bearing component, bears significant aerodynamic and inertial loads during takeoff and landing. Currently, to enhance the structural strength and rigidity of the wing's trailing edge while reducing aircraft weight, a honeycomb sandwich structure composed of a thin skin and a honeycomb core material is commonly used to fabricate the trailing edge flap, designed in a wedge shape to meet aerodynamic requirements. However, at the sharp corners of the wedge-shaped honeycomb sandwich structure, the thickness of the honeycomb core material is close to zero. This reduces the structural strength at the sharp corners and increases the difficulty of machining the honeycomb core material located at the wedge corners, making it prone to breakage during processing. These factors all contribute to the fact that the honeycomb sandwich structure of the aircraft's trailing edge flap cannot effectively and evenly distribute the load it bears, resulting in excessive stress in localized areas of the trailing edge flap. This can easily lead to structural deformation of the trailing edge flap, making it difficult for the trailing edge flap to meet the stringent requirements of high aerodynamic load service environments. Utility Model Content

[0004] The purpose of this invention is to overcome the shortcomings of the prior art and provide a wing trailing edge wedge honeycomb sandwich structure.

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] A wing trailing edge wedge-shaped honeycomb sandwich structure includes a first skin and a second skin arranged opposite to each other. The first skin and the second skin are connected to form a "V"-shaped space. A trailing edge strip, a honeycomb core, and a front spar are distributed sequentially from bottom to top in the "V"-shaped space. The trailing edge strip has a triangular prism structure, and the bottom surface of the trailing edge strip is fixedly connected to the small end face of the honeycomb core, while the large end face of the honeycomb core is fixedly connected to the front spar.

[0007] Specifically, the wing trailing edge wedge-shaped honeycomb sandwich structure further includes a third skin wrapped around the outside of the wedge-shaped honeycomb sandwich structure. Preferably, the third skin is a prepreg continuous fiber cloth.

[0008] Specifically, the third skin is bonded to the outer surfaces of the first skin and the second skin, respectively.

[0009] Specifically, the first skin has a first chamfered edge on one side, and the second skin has a second chamfered edge on one side. The first chamfered edge and the second chamfered edge are fixedly connected so that the first skin and the second skin are joined to form a "V" shaped space. The first chamfered edge and the second chamfered edge are glued together for fixation.

[0010] Specifically, the honeycomb core is a frustum structure. One side of the frustum structure is connected to the inner side of the first skin, the other side is connected to the inner side of the second skin, the top surface is connected to the front beam, and the bottom surface is connected to the tail edge strip. The frustum structure is connected and fixed to the first skin, the second skin, the front beam, and the tail edge strip using adhesive bonding.

[0011] Specifically, the front beam has an overall "U"-shaped structure, which is formed by connecting the first side beam, the bottom beam and the second side beam in sequence, and the two sides of the opening end of the "U"-shaped structure are flush with the adjacent first skin and second skin respectively.

[0012] Compared with the prior art, the technical solution provided by this utility model has the following beneficial effects:

[0013] 1) By filling the triangular space formed by the honeycomb core, the first skin, and the second skin, the strength of the wedge-shaped honeycomb sandwich structure in the sharp corner area is enhanced, and its load-bearing capacity is significantly increased. Furthermore, since the tail edge is used for filling, there is no need to perform mechanical processing on the formed honeycomb core, which effectively avoids the problem of difficult processing of sharp-corner honeycomb cores.

[0014] 2) The third skin wrapped around the wedge-shaped honeycomb sandwich structure is a prepreg continuous fiber cloth. After the entire cloth is laid on the first and second skins, the strength of the sharp corner joints can be increased, so that the trailing edge flap structure can meet more stringent service environments. Attached Figure Description

[0015] The accompanying drawings are incorporated in and form part of this specification, and together with the description, serve to explain the principles of this invention.

[0016] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, for those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 This is an exploded schematic diagram of the wedge-shaped honeycomb sandwich structure at the trailing edge of the wing.

[0018] Figure 2 This is a schematic diagram of the cross-section of the wedge-shaped honeycomb sandwich structure at the trailing edge of the wing.

[0019] Explanation of reference numerals in the attached diagram: 1. Honeycomb core; 2. Tail edge strip; 3. Front beam; 4. First skin; 5. Second skin; 6. Third skin. Detailed Implementation

[0020] Exemplary embodiments will now be described in detail, examples of which are illustrated in the accompanying drawings. When the following description relates to the drawings, unless otherwise indicated, the same numerals in different drawings denote the same or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with this invention. Rather, they are merely examples consistent with some aspects of this invention as detailed in the appended claims.

[0021] To enable those skilled in the art to better understand the technical solution of this utility model, the present utility model will be further described in detail below with reference to the accompanying drawings and embodiments. Example

[0022] See Figures 1-2 As shown, this embodiment provides a wing trailing edge wedge-shaped honeycomb sandwich structure, including a honeycomb core 1, a trailing edge strip 2, a front spar 3, a first skin 4, a second skin 5, and a third skin 6; the first skin 4 and the second skin 5 are arranged opposite to each other and are connected to form a "V" shaped space, in which the trailing edge strip 2, the honeycomb core 1, and the front spar 3 are distributed sequentially from bottom to top; the trailing edge strip 2 has a triangular prism structure, and the bottom surface of the trailing edge strip 2 is fixedly connected to the small end face of the honeycomb core 1, and the large end face of the honeycomb core 1 is fixedly connected to the front spar 3.

[0023] Furthermore, the bottom surface of the trailing edge strip 2 is bonded to the small end face of the honeycomb core 1. The trailing edge strip 2 is located within the space enclosed by the first skin 4, the honeycomb core 1, and the second skin 5, and serves to supplement the sharp corners of the honeycomb core 1.

[0024] The wing trailing edge wedge honeycomb sandwich structure also includes a third skin 6 wrapped around the outside of the wedge honeycomb sandwich structure. The third skin 6 is bonded to the outer surfaces of the first skin 4 and the second skin 5 respectively, which can effectively cover the bonding area of ​​the first skin 4 and the second skin 5, thereby increasing the strength of the connection point.

[0025] Preferably, the third skin 6 is a prepreg continuous fiber fabric. It should be noted that prepreg continuous fiber fabric is a high-performance composite material semi-finished product in which resin is pre-impregnated into a continuous fiber woven fabric. It combines the excellent mechanical properties of high-performance fibers with the adhesive and protective effects of the resin matrix, and achieves high quality, consistency, and relatively convenient manufacturing processes (such as lay-up and curing) through "pre-impregnation" and "Phase B" states. It is a key basic material for manufacturing lightweight, high-strength, and high-rigidity structural components in modern aerospace and other fields. Here, "Phase B" control refers to the precise control of temperature and residence time during impregnation to allow the resin to reach a partially cured (Phase B) viscous state.

[0026] Furthermore, a first chamfer edge is provided on one side of the first skin 4, and a second chamfer edge is provided on one side of the second skin 5. The first chamfer edge and the second chamfer edge are fixedly connected (e.g., glued) so that the first skin 4 and the second skin 5 are connected to form a "V" shaped space.

[0027] Furthermore, the honeycomb core 1 is a frustum structure. One side of the frustum structure is connected to the inner side of the first skin 4, the other side is connected to the inner side of the second skin 5, the top surface is connected to the front beam 3, and the bottom surface is connected to the tail edge strip 2. Here, the frustum structure is connected and fixed to the first skin 4, the second skin 5, the front beam 3, and the tail edge strip 2 by adhesive bonding.

[0028] Furthermore, to facilitate subsequent wing assembly, the front beam 3 is generally in the shape of a "U" and is formed by connecting the first side beam, the bottom beam, and the second side beam in sequence. The two sides of the opening end of the "U" shaped structure are flush with the adjacent first skin 4 and second skin 5, respectively. The bottom beam is bonded to the large end face of the honeycomb core 1 to seal the honeycomb core 1. The first side beam is bonded to the first skin 4, and the second side beam is bonded to the second skin 5.

[0029] The specific fabrication process of the aforementioned wing trailing edge wedge-shaped honeycomb sandwich structure is as follows:

[0030] First, the first skin 4, the second skin 5, the tail edge strip 2, and the front beam 3 are prepared using an autoclave curing molding process; then the honeycomb core 1 is machined to make it into a frustum structure.

[0031] Then, the first skin 4 and the second skin 5 are glued together to form a "V" shaped space. The tail edge strip 2, the honeycomb core 1 and the front beam 3 are placed in the "V" shaped space in order from bottom to top and glued together. Then, a hot autoclave is used for the first curing and shaping.

[0032] Finally, the third skin 6 is wrapped around the outer surfaces of the first skin 4 and the second skin 5 in a whole-layer laying manner, and the inner side of the third skin 6 is glued to the outer surfaces of the first skin 4 and the second skin 5 respectively. Then, it is cured and shaped again in a hot autoclave using a molding tool to obtain a wing trailing edge wedge honeycomb sandwich structure suitable for high-speed flight, so as to meet the service environment of high aerodynamic load.

[0033] It should be noted that the autoclave and molding fixture used in this embodiment are existing equipment, and no excessive limitations are imposed here, as long as they can achieve the corresponding functions. It should be noted that since the molding fixture is a tooling system composed of two or more matching molds (forms), it is necessary to precisely close, apply pressure and maintain a specific cavity during the curing process, and perform precise matching and alignment.

[0034] The above description is merely a specific embodiment of this utility model, enabling those skilled in the art to understand or implement it. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of this utility model.

[0035] It should be understood that this utility model is not limited to the content already described above, and various modifications and changes can be made without departing from its scope. The scope of this utility model is limited only by the appended claims.

Claims

1. A wedge-shaped honeycomb sandwich structure for the trailing edge of an airfoil, characterized in that, It includes a first skin (4) and a second skin (5) which are oppositely arranged. The first skin (4) and the second skin (5) are joined together to form a "V"-shaped space. Inside the "V"-shaped space, a trailing edge strip (2), a honeycomb core (1) and a front beam (3) are sequentially distributed from bottom to top. The trailing edge strip (2) has a triangular prism structure, and the bottom surface of the trailing edge strip (2) is fixedly connected to the small end face of the honeycomb core (1). The large end face of the honeycomb core (1) is fixedly connected to the front beam (3).

2. The wing trailing edge wedge-shaped honeycomb sandwich structure according to claim 1, characterized in that, It further includes a third skin (6) wrapped outside the wedge-shaped honeycomb sandwich structure.

3. The wing trailing edge wedge-shaped honeycomb sandwich structure according to claim 2, characterized in that, The third skin (6) is adhesively bonded to the outer surfaces of the first skin (4) and the second skin (5) respectively.

4. The wing trailing edge wedge-shaped honeycomb sandwich structure according to claim 2, characterized in that, The third skin (6) is a prepreg continuous fiber cloth.

5. The wing trailing edge wedge-shaped honeycomb sandwich structure according to claim 1, characterized in that, One side edge of the first skin (4) is provided with a first chamfer edge, and one side edge of the second skin (5) is provided with a second chamfer edge. The first chamfer edge and the second chamfer edge are fixedly connected so that the first skin (4) and the second skin (5) are joined together to form a "V"-shaped space.

6. The wing trailing edge wedge-shaped honeycomb sandwich structure according to claim 5, characterized in that, The first chamfer edge and the second chamfer edge are adhesively bonded and fixed.

7. The wing trailing edge wedge-shaped honeycomb sandwich structure according to claim 1, characterized in that, The honeycomb core (1) has a frustum structure. One side surface of the frustum structure is connected to the inner surface of the first skin (4), another side surface is connected to the inner surface of the second skin (5), the top surface is connected to the front beam (3), and the bottom surface is connected to the trailing edge strip (2).

8. The wing trailing edge wedge-shaped honeycomb sandwich structure according to claim 7, characterized in that, The frustum structure is connected and fixed to the first skin (4), the second skin (5), the front beam (3) and the trailing edge strip (2) by adhesive bonding.

9. The wing trailing edge wedge-shaped honeycomb sandwich structure according to claim 1, characterized in that, The front beam is integrally in a "U"-shaped structure and is formed by sequentially connecting a first side beam, a bottom beam and a second side beam.

10. The wing trailing edge wedge-shaped honeycomb sandwich structure according to claim 9, characterized in that, The two edges at the open end of the "U"-shaped structure are flush with the adjacent first skin and second skin respectively.

Images