RU2531114C2 - Aircraft wing from polymer composites - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, particularly, to streamlined structures of composites, particularly, aircraft wings. Aircraft wing of polymer composites has lining, spars and stiffness ribs, inner ribs based on glass and coal clothes (coal tapes). Lining comprises top and bottom shells and consists of outer glass and coal cloth-based plies and inner layer of foam filler arranged there between. Wing top and bottom lining shells changing at wing root and end parts into ribs and spars made by infusion of binder with material polymerisation in appropriate dies with interconnection of shells nearby wing leading and trailing edges by glue film applied on both sides of connection surfaces. Wing mid part connection of top and bottom shells is made with the help of twin moulded angle pieces of coal cloth with binder and pre-installed via glue film at inner surfaces of said top and bottom shells connected to ribs by similar flue film. Inner ribs are made by infusion of binder and connected to top and bottom shells and ribs via glue film fed between connection surfaces.

EFFECT: higher surface quality, reliability and strength, decreased weight.

5 cl, 5 dwg

Description

The invention relates to the field of aviation technology and relates to the creation of streamlined structures for aircraft from composite materials, in particular wings and wing devices.

A known aircraft wing structure comprising a power frame filled with a honeycomb core is made of front and rear sides, end fairing, root element and panels of the upper and lower wing surfaces with a thickness decreasing from the root element. The panels of the upper and lower surfaces of the wing are made of a package of fabric layers with overlapping zone of the root element attachment node with the maximum number of layers. The layers determining the thickness variation of the wing surfaces are made in the form of similar triangles with an increase in the size of each subsequent one and the location of its lateral sides parallel to the edges of the wing sides (RU 2333865 C1, B64C 3/26, 11.16.2006).

The disadvantage of this design is that the presence of reinforcing layers located on the outer surfaces of the wing reduces the aerodynamic quality of the wing, which leads to the need for subsequent mechanical processing of its outer surface and, as a consequence, to its microdamage.

Also known is a wing panel of a composite construction containing the upper and lower wing shells made of force layers based on glass, carbon fabric (carbon tape) or prepreg, and the inner layer of foam or honeycomb core and two spars based on glass or carbon fabric (carbon tape). In this case, all structural elements in a dry state are placed between the elements of the wing mandrel, are closed by the upper and lower parts of the matrix, are jointly impregnated with a binder using the RTM method and polymerized at elevated temperatures (US 2010140404 A1, B29C 70/08, 06/10/2010 - prototype) .

The disadvantage of this design is its high cost, since it requires the manufacture of expensive equipment, difficult to operate. In addition, such a wing has a large weight.

The objective of the invention is the creation of an aircraft wing from polymer composite materials, which allows to increase its economic and technical efficiency by reducing the cost of its manufacture and weight, improving the quality of manufacture of the outer surfaces of the wing while ensuring reliability and strength of the wing structure.

The specified technical result is achieved by the fact that the wing of the aircraft made of polymer composite materials has a skin containing the upper and lower shells, consisting of outer layers based on glass, carbon fabric (carbon tape) and an inner layer of foam core between them, located along the wingspan spars and stiffeners - ribs - based on glass, carbon fabric (carbon tape). According to the invention, the upper and lower shells of the wing sheathing, formed together with ribs in the root and end parts of the wing, and the spars are made by infusion of a binder with polymerization of the material in the respective matrices. The cladding shells are connected to each other at the leading and trailing edges of the wing by means of an adhesive film deposited on the mating connecting surfaces. In the middle part of the wing along the profile of the wing, the upper and lower shells are connected using spars through paired molding squares made of carbon fabric with a binder and pre-installed through adhesive film on the inner surfaces of the upper and lower shell shells. The upper and lower shells of the casing are connected with the spars inserted between them by means of an adhesive film, while the internal ribs are made by the infusion of a binder and connected to the upper and lower shells and with the spars through an adhesive film introduced between the connected surfaces. The spars and inner ribs have a three-layer structure, in which between the outer layers of a polymer composite material based on glass, carbon fabric (carbon tape) is located the middle layer of foam aggregate.

In addition, the mating connecting surfaces at the leading and trailing edges of the wing are reinforced with foam inserts introduced under them from the inside of the skin.

The inner ribs consist of three parts each and are formed with the formation of double-sided flanges along the perimeters of these parts, with the help of which parts of the inner ribs are connected with the upper and lower shells of the wing and with the side members.

The connection of the side members with parts of the ribs through their flanges was carried out while maintaining the continuity of paired molding squares connecting the side members with the upper and lower shells of the wing.

The manufacture of shell linings for the wing and its spars in separate matrices by the method of infusion of a binder with polymerization of the material reduces the time and material costs of their manufacture, high quality of the aerodynamic surface of the wing, the stability of its geometric dimensions and increased strength characteristics.

The connection of the shells with each other in the region of the leading and trailing edges of the wing, with the side members through paired molding squares and ribs, as well as the side members with squares and parts of ribs by means of an adhesive film applied to the surfaces to be joined, makes it possible to increase the manufacturability of manufacturing the wing with the least labor and ensuring a strong and reliable connections.

Filling the space between the outer layers of the cladding shells and spars with foam filler allows you to reduce the weight of the structure without compromising its strength characteristics.

The presence of foam inserts at the junctions of the lower and upper surfaces of the wing increases the strength and reliability of the connection and the structure of the wing as a whole.

The implementation of the parts of the ribs in the root and end parts of the wing simultaneously with the molding of the upper and lower parts of the wing by the method of binder infusion increases the reliability of the wing structure.

At the same time, the specified wing strength is ensured by laying in the desired areas of the three-layer structures of the upper, lower wing shells and side members of the previously calculated number of layers. The shape of each layer of glass-, carbon fabric (carbon tape) is also determined by calculation, which leads to optimization of the design, a more uniform distribution of stresses in the power elements of the wing and a decrease in its total weight.

The essence of the invention is illustrated by drawings, which show:

- a General view of the design of the proposed wing of the aircraft from polymer composite materials - figure 1;

- cross section aa (figure 1) - figure 2;

- cross section BB (figure 1) - figure 3;

- view B (figure 3) - figure 4;

- structural elements of the wing - figure 5.

The proposed structure of the wing 1 consists of the lower 2 and upper 3 shells of the skin of a three-layer structure, including the outer layers 4 of glass, carbon fabric (carbon tape) and the inner layer 5 made of foam filler located between them (Fig.2, 4), laid in the appropriate equipment for subsequent impregnation of a binder and polymerization of the material from spars 6 located along the wing span (Fig. 1), consisting of external force layers of glass, carbon fabric (carbon tape) 7 and internal foam core 8 (Fig. 4), t also laid in the appropriate equipment for subsequent impregnation with a binder method of infusion of the binder and polymerization of the material, and from one or more internal ribs 9 located in the middle part of the wing (Figs. 1, 3, 5). The number of power layers of glass, carbon fabric (carbon tape) 10 (Fig. 1) in the upper and lower shells of the wing and side members and the shape of each layer on the wing surfaces are determined by calculation and can vary in different areas of the wing. On the inner surfaces of the upper and lower shells of the wing skin are installed using adhesive film 11 (Fig. 4) paired molding squares 12, 13 of carbon fabric with a binder in the cured state for subsequent fastening of these spars inserted between paired squares (Fig. 4, 5) and connected with an adhesive film. The upper and lower shells are connected to each other at the nose 14 and end 15 of the wing edges by means of an adhesive film that is applied to the mating connecting surfaces reinforced by foam inserts 16 introduced from the inside (Fig. 5), and in the middle part along the length of the wing connected by spars. The ribs at the root 17 and end parts of the wing 18 (figure 1) are made by the method of infusion of the binder simultaneously with the formation of the upper and lower shells of the wing skin. The inner rib is made of layers of glass, carbon fabric and a binder by means of a binder infusion and is connected to the upper and lower shells of the wing and to the side members through an adhesive film inserted between the joined surfaces. It consists of three parts, which have perimeter double-sided flanges 19, ensuring their connection with the upper and lower shell shells, as well as with the side members. The connection of ribs through double-sided flanges with spars is carried out while maintaining the continuity of paired molding squares.

The manufacture of an aircraft wing from polymer composite materials and its operation are as follows.

The upper and lower shells of the wing sheathing with foam filler and its spars are made of glass, carbon-carbon (carbon) by laying in the appropriate matrix for subsequent impregnation of the binder with a binder method and polymerization of the material. Using templates on the inner surfaces of the upper and lower shells of the wing sheathing, paired molding squares made of carbon fabric with a binder in the cured state are installed through the adhesive film for subsequent fastening of these spars. By the method of infusion, three parts of the inner rib are made from layers of glass, carbon fabric and a binder, with the formation of bilateral flanges along their perimeters. By means of an adhesive film deposited on the vertical parts of paired squares mounted on the inner surface of the lower shell of the wing skin, spars are attached to it. Through the adhesive film deposited on the flanges of the parts of the inner rib, these parts are also installed on the inner surface of the lower wing skin and are connected to the side members through their flanges. The upper wing skin is connected to the lower skin by means of an adhesive film applied to the mating connecting surfaces in the region of the front (nose) and end edges of the wing, reinforced with foam inserts, and an adhesive film applied to the inner vertical surfaces of the paired molding squares, between which spars are placed through the adhesive film, as well as the upper parts of the flanges of the inner rib.

During the flight of an aircraft, under the influence of air flow on the aerodynamic surfaces of the wing, a deformation field appears in the elements of its structure. At the same time, the calculated number of power layers in the skins and side members, as well as the calculated shape of each layer on the wing surfaces, leads to optimization of the structure according to deformations and their more uniform distribution over the structural elements of the structure, thereby ensuring the specified wing strength with minimum weight. The manufacture of the lower and upper skins in the appropriate equipment leads to an increase in the quality of manufacturing of the outer aerodynamic surfaces of the wing. Due to the presence of foam inserts at the junctions of the lower and upper skins in the area of the front and rear edges of the wing, a reliable and durable connection of the skins and the strength of the wing as a whole is ensured.

The proposed wing of the aircraft made of polymer composite materials allows you to create a wing structure with external surfaces of high quality, reduce the cost of its manufacture and weight while ensuring reliability and strength of the wing structure, which compares favorably with the prototype.

Claims (5)

1. A wing of an aircraft made of polymer composite materials having a casing containing upper and lower shells and consisting of outer layers based on glass, carbon fabric (carbon tape) and an inner layer of foam core between them, spars and stiffeners located along the wing span - inner ribs based on glass-, carbon fabric (carbon tape), characterized in that the upper and lower shells of the wing sheath, passing in the root and end parts of the wing into ribs, and spars are made by infusion with the material knitting with polymerization in the respective matrices, with the shells joined together at the leading and trailing edges of the wing by means of an adhesive film deposited on the mating connecting surfaces, and in the middle along the profile of the wing part, the upper and lower shells are connected using spars through paired molding squares, made of carbon fabric with a binder and pre-installed through an adhesive film on the inner surfaces of the upper and lower shell shells, the connection of which with Jeroen introduced therebetween, as effected by the adhesive film, wherein the inner ribs are made by infusion of the binder and are connected to the upper and lower shells and longerons through interposed between the joined surfaces of the adhesive film. 2. The wing of the aircraft according to claim 1, characterized in that the spars and inner ribs have a three-layer structure, in which between the outer layers of a polymer composite material based on glass, carbon fabric (carbon tape) is located the middle layer of foam aggregate. 3. The wing of the aircraft according to claim 1, characterized in that the mating connecting surfaces at the front and rear edges of the wing are reinforced with foam inserts introduced under them from the inside of the skin. 4. The wing of the aircraft according to claim 1, characterized in that the inner ribs consist of three parts, each of which is formed with the formation of double-sided flanges along the perimeters of these parts, with which parts of the internal ribs are connected with the upper and lower shells of the wing and the side members. 5. The wing of the aircraft according to claim 1, characterized in that the connection of the side members with parts of the inner ribs through their flanges is carried out while maintaining the continuity of paired molding squares connecting the side members with the upper and lower shells of the wing.

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