KR100271064B1 - Method for manufacturing jig for composite aircraft wing and composite aircraft wing - Google Patents

Abstract

PURPOSE: A method for manufacturing a jig for a composite aircraft wing and the composite aircraft wing are provided to form a jig having a precise shape by corresponding to the thickness of a composite material to be layered and to apply sufficient pressure between jigs during vacuum hardening by improving a process. CONSTITUTION: A method for manufacturing a jig for a composite aircraft wing comprises the steps of forming a first upper jig(71) and a first lower jig by laying up respective materials on the upper and lower surfaces of a master model having an outer shape the same as that of an aircraft wing, separating the first upper jig and the first lower jig from the master model and forming a second upper jig(81) and a second lower jig in a specific thickness by laying up respective materials on the inner faces of the first upper jig and the first lower jig, forming plural upright diaphragms(91) in the positions corresponding to the positions of spars, forming plural third upper jigs(101) and third lower jigs having flanges on both ends by laying up materials on the outer faces of the second upper jig, the second lower jig and the upright diaphragms, and forming plural box-shaped jigs by combining the third upper jig with the third lower jigs. The aircraft wind is manufactured by layering a composite material on the outer surfaces of the jigs and hardening the layered composite material by using vacuum.

Description

Fabrication method for composite aircraft wing and method for manufacturing composite aircraft wing using same

The present invention relates to a method for manufacturing a composite aircraft wing tool and a method for manufacturing a wing of a composite aircraft using the tool.

In order to make composite parts (for example, wing blades, auxiliary wings, horizontal tail wings, vertical tail wings, etc.) that are usually used in airplanes, etc., first, a production tool having a shape corresponding to the shape of the target part is made, The resin-impregnated fiber-reinforced composite ply or composite tape is laminated several times until it reaches a predetermined thickness, and then the laminated composite ply is subjected to vacuum curing in an oven of high temperature and high pressure.

The wing 10 of the conventional aircraft, as shown in Figure 1, the upper skin 11 formed in the upper portion in a predetermined curvature shape, the lower skin 12 formed in the lower portion in a predetermined curvature shape, It is provided with a plurality of spar 13 which is installed upright between the upper skin 11 and the lower skin 12.

The conventional assembly type manufacturing method for manufacturing an aircraft wing having such a structure is as follows. First, the tool for forming the upper skin, the tool for forming the lower skin, and the tool for spa forming are produced from the master model having the same shape as the wing skin. Then, the composite material is laminated on the tool and hardened at high temperature, thereby manufacturing the upper skin 21, the lower skin 22, and the spar 23. As shown in FIG. 2, the complete aircraft wing 20 is completed by bolting 24 or using a glue to the spar 23 to the upper and lower skins 21 and 22. .

However, since the use of the assembled structure to manufacture the aircraft wing as described above causes a variety of problems in the process and product quality, a method of manufacturing the aircraft wing using a multi-cell box structure is used.

In the conventional method of manufacturing an aircraft wing using such a multi-cell box structure, as shown in FIG. 3, a plurality of solid mandrel 31 corresponding to the shape of a small portion of the aircraft wing is manufactured, and the plurality of The composite 32 is laminated on the outer surface of the two solid mandrels 31, respectively. And by vacuum-curing in the state that the solid mandrel 31 is in contact with each other, the wing 30 of the complete composite aircraft is completed.

However, in the conventional aircraft wing manufacturing method as described above, since a sufficient pressure is not transmitted between the solid mandrel in the vacuum curing step, it is easy to cause a defect in the structure forming the spa (contact portion 35 between the mandrel 31). A problem occurred.

The present invention was created in order to solve the above problems, a precisely shaped tool in consideration of the thickness of the composite material to be laminated is formed, the composite is improved in the process so that sufficient pressure can be transferred between the tool during vacuum curing An object of the present invention is to provide a method for manufacturing a wing tool for an aircraft wing and a method for manufacturing a wing of a composite aircraft using the same.

1 is a perspective view of a conventional prefabricated composite aircraft wing.

2 is a perspective view of a composite aircraft wing using a conventional cell box structure.

3 is a perspective view of a conventional composite aircraft wing.

4 (a) to 4 (c) are diagrams sequentially illustrating a process of installing the first upper jig and the working support on the outer surface of the master model.

FIG. 5 is a view showing a state where the second upper jig is laid up on the inner surface of the first upper jig of FIG.

6 is a view showing a state in which an upright partition wall is installed in the second upper jig of FIG.

7 (a) is a view showing a state in which the third upper jig is laid up on the outer surface of the second upper jig.

7 (b) is a view showing a state in which the first, second, third lower jig is formed.

8 (a) is a view showing a state before the third upper and lower jig corresponding to each other.

8 (b) is a view showing a state in which a complete jig is made to bond the third upper jig and the third lower jig.

9 is a view showing a state in which a composite material is laminated to the tool in one embodiment of the composite aircraft manufacturing method according to the present invention.

FIG. 10 is a working conceptual view showing a process in which a plurality of dental tools of FIG. 9 are coupled and vacuum hardened.

* Explanation of symbols for main parts of the drawings

60: master model 71: the first upper jig

72: first lower limb 77,78: working support

81: second upper jaw 82: second lower jaw

91,92: Upright bulkhead 101: Third upper fixture

102: third lower section 120: composite tape

200,201,202,203: Tool

Method for manufacturing a composite aircraft wing tool according to the present invention for achieving the above object, the production of the wing of the composite aircraft having a plurality of spars installed upright between the upper, lower skin and the upper, lower skin forming an external shape. A method of manufacturing a multi-box tool for use in a method, comprising: laying up a material on an upper surface and a lower surface of a master model having the same outer shape as the wing, respectively, the first upper jig and the lower skin corresponding to the upper skin A first step of forming a first lower jig corresponding to the first jig, and separating the first upper jig and the first lower jig from the master model and laying the material on the inner surfaces of the first upper jig and the first lower jig, respectively. A second step of forming a second upper jig and a second lower jig having a predetermined thickness, and the studs on the outer surfaces of the second upper jig and the second lower jig. A third step of forming a plurality of upstanding bulkheads at positions corresponding to the plurality of upright bulkheads, and laying up materials on the outer surfaces of the second upper jig, the second lower jig, and the upright bulkhead; A fourth step of forming a third upper jig and a third lower jig respectively, and combining the third upper jig and the third lower jig corresponding to each other to form a plurality of box-shaped jig tools corresponding to the shape of each part of the aircraft wing; It is characterized by the fifth step.

And it is preferable that the thickness of the second upper jig and the second lower jig is the same as the thickness of the composite material of the aircraft wing.

It is preferable that the step of installing a mutual support for supporting the outer surface of the first upper jig and the first lower jig, respectively.

It is preferable to further include installing a partition wall for forming a space for receiving a coupling screw in at least one of the third upper jig and the third lower jig to be coupled to each other.

Wing manufacturing method of a composite aircraft according to the present invention for achieving the above object, the tool manufacturing step of forming a plurality of box-shaped tool corresponding to the shape of each part of the aircraft wing, and a predetermined number on the outer surface of the tool A composite lamination step of laminating a composite material to a thickness, and a vacuum curing preparation step of aligning a plurality of tool tools in which the composite material is stacked in order, and closely contacting each other, and simultaneously vacuum bagging the inside and the outside of the plurality of tool tools, and the laminated composite material. It is characterized by having a vacuum curing step of curing.

And the tool manufacturing step, the material is laid up on the upper surface and the lower surface of the master model having the same outer shape as the aircraft wing, respectively corresponding to the first upper jig corresponding to the upper skin of the aircraft and the lower skin of the aircraft A first step of forming a first lower jig, and separating the first upper jig and the first lower jig from the master model, and laying up materials on inner surfaces of the first upper jig and the first lower jig, respectively; A second step of forming a second upper jig and a second lower jig having a thickness; and a third step of forming a plurality of upstanding bulkheads respectively at positions corresponding to spars of the aircraft on the outer surfaces of the second upper jig and the second lower jig. And lay-up materials on the outer surfaces of the second upper jig and the second lower jig and the upright bulkhead to form a plurality of third upper jig and third lower jig, each of which has flanges at both ends thereof. And a fifth step of combining the third upper jig and the third lower jig corresponding to each other to form a plurality of box-like tools corresponding to the shape of each part of the aircraft wing.

Hereinafter, with reference to the accompanying drawings, it will be described in detail a preferred embodiment of the method for manufacturing a composite aircraft wing tool according to the present invention.

1 shows an aircraft wing (e.g., aircraft fuselage, main wing, or tail) intended to be manufactured by the manufacturing method of this embodiment. As shown, the aircraft wing 10 includes an upper skin 11 and a lower skin 12 having a predetermined curved shape and a plurality of spars 13 installed upright between the two skins.

As a first step of the process, a master model 60 having the same outer shape as the upper and lower skin shapes of the aircraft wing is manufactured. The master model 60 is made according to a master surface modeled by computer at the time of product design. The master model has an upper surface corresponding to the upper skin of the wing and a lower surface corresponding to the lower skin of the wing.

As shown in FIG. 4 (a), the first upper jig 71 is formed by laying up a material such as glass on the upper surface 61 of the master model to form a layer having a predetermined thickness. As shown in FIG. 4 (b), the first upper jig 71 is separated from the master model 60, and the outer upper surface 71a of the first upper jig 71 is formed on both surfaces 71a and 71b of the first upper jig 71. A working support 77 for supporting the first upper jig 71 is installed. Installing the working support 77 in this way is to consider the convenience of the operation so that the process described later can be easily made. Then, as shown in FIG. 4 (c), the working support 77 is positioned downward, so that the inner surface 71b of the first upper jig 70 is in contact with the upper surface 61 of the master model. Face up. By this process, the inner surface 71b of the first upper jig to be processed has the same shape as the curved shape of the upper surface 61 of the master model.

Then, as shown in FIG. 5, the second upper jig 81 is formed by laying up a material such as glass on the inner surface 71b of the first upper jig 71 to form a layer having a predetermined thickness. The thickness t of the second upper jig 81 should be uniform with respect to the entire area so that the outer surface 81b of the second upper jig 81 simulates the shape of the upper surface 61 of the master model. And the thickness t of the second upper jig 81 should be equal to the thickness of the composite material requiring lamination.

Then, as shown in FIG. 6, a plurality of joining upright partition walls 91 are provided on the outer surface 81b of the second upper jig 81 at predetermined intervals. By this upstanding partition wall 91, the upper surface 81b of the second upper jig 81 is divided into a plurality of small portions.

Then, as shown in Fig. 7 (a), four pieces of the third upper jig 101 are formed by laying up materials, such as glass, on each of the four divided portions of the second upper jig 81, respectively. . That is, by laying up the material on the upper end of the small portion and the outer surface of the upright partition wall 91 formed at both ends thereof, a plurality of third upper jig 101 having flanges 101a formed at both ends thereof can be formed. The outer surface of the third upper jig 101 is the same as the shape of the upper spa 11 of a small portion of the aircraft wing.

The process of making the plurality of third upper jig 101 as described above may be applied to the lower jig as it is.

That is, as shown in FIG. 7 (b), the material is laid up on the lower surface (not shown) of the master model to make the first lower jig 72 corresponding to the shape of the lower skin 12 of the wing. 1 A working support 78 for supporting the outer surface of the lower jaw 72 is provided. Then, the second lower jig 82 is formed by laying up a material having a predetermined thickness (that is, the thickness of the composite material to be laminated) on the inner surface of the first lower jig 72. In addition, a plurality of upright bulkheads 92 having a shape and a size corresponding to the upright bulkheads 91 of the upper jig are formed on an outer surface of the second lower jig 82, thereby forming a plurality of second lower jig 82. Partition into parts.

Then, a plurality of (four in the drawing) third lower jig 102 is formed by laying up the material on the small portion of the second lower jig 82 and the upright bulkhead 92. Flange 101a is formed in the both ends of these 3rd lower jig 102, respectively. The outer surface shape of the third lower jig 102 is the same as the shape of the lower skin 12 of the small part of the aircraft wing, and the flange 101a corresponds to the spar 13.

Next, the partition 102b is formed in the flange 102a forming portion of the third lower jig 102, and the screw used to join the third upper and lower jig 101,102 (110 in Fig. 8 (b)). The coupling screw receiving portion for accommodating) is formed. Although not shown, such a partition wall 102b is not formed in the third lower jig 102 but is formed in the third upper jig 101 without departing from the scope of the present invention.

Then, the plurality of third upper jig 101 and the third lower jig 102 are separated from the second upper jig 81 and the second lower jig 82, respectively. In Fig. 8 (a), one set of the plurality of third jiges separated in this way is shown. The third upper jig 101 and the third lower jig 102 corresponding to each other separated as described above are arranged so that the flanges 101a and 102a formed at both ends thereof overlap each other, as shown in FIG. 8 (b). By fitting and joining the flange portions 101a and 102a with the screws 110, one complete tool 200 is formed.

Since the joining process is performed for a plurality of sets of the third upper and lower jig respectively, a plurality of jig (200, 201, 202, 203 in FIG. 10) having a shape corresponding to the shape of the small part of the aircraft wing 10 is produced. The curved shape of the plurality of tool tools is the same as the surface shape of the aircraft wing 10, and the size thereof is smaller than the aircraft wing 10 by the thickness of the second jig 81, 82, that is, the thickness of the composite material to be laminated. Combining the tools of such a shape in order produces a complete tool corresponding to the upper surface 11 and the lower surface 12 of the aircraft wing 10, and the flange part of each tool has a plurality of tools of the aircraft wing 10. It corresponds to the spar 13.

Hereinafter, with reference to the accompanying drawings, a preferred embodiment of the wing manufacturing method of the composite aircraft according to the present invention will be described in detail.

The method of manufacturing a wing of the composite airplane according to the present embodiment (for example, main wing, auxiliary wing, horizontal tail wing, vertical tail wing, etc.) is to make a wing shape using a cell box structure. Therefore, the process of manufacturing a box-shaped tool for making each box structure must be preceded. However, such a box-shaped tool manufacturing step is the same as the manufacturing method of the tool shown in Figures 3 to 8 (b), and a detailed description thereof will be omitted.

The curved shape of the plurality of tools (200, 201, 202, 203) generated as described above is the same as the surface shape of the aircraft wing 10, the size is smaller than the thickness of the second jig (81, 82) than the aircraft wing (10) It becomes a hollow shape with an empty inside. And the flange part of each tooth tool corresponds to the some spar 63 of an airplane wing.

When a plurality of tools are formed by the above process, as shown in FIG. 9, the composite tape having the same thickness as the second upper jig 81 and the second lower jig 62 may be formed on the upper and lower outer surfaces of the jig 200. 120) to form a composite layer (300 in FIG. 10). Then, the outer surface of the composite layer 300 is the same shape and size as the aircraft wing 10. This process is performed for all of the plurality of tools 200, 201, 202, 203.

Next, as shown in FIG. 10, the four tool tools 200, 201, 202, and 203 having the composite layer 300 formed on the outer surface thereof are aligned in order and closely adhered to each other according to the shape of the aircraft wing. In addition, a vacuum bagging process of applying a vacuum to the composite material 300 laminated on the outer surface of each of the tool tools 200, 201, 202, and 203 is performed. This vacuum bag process is for removing the gas contained in the resin layer. As shown in this case, by applying a vacuum not only outside the composite 300, but also inside the composite 300, that is, inside the plurality of tool (200a, 201a, 202a, 203a), the tool and the inside and outside of the composite layer 300 Apply pressure to the composite layer. This internal bagging process is possible because the interiors 200a, 201a, 202a, and 203a of the tool are hollow.

The composite layer laminated on the left and right flange portions of the tool tool is brought into contact with the composite material laminated on the flange portion of the adjacent tool tool, and both composite materials are solidified by the curing process. This hardening process is performed by holding the composite material layer laminated | stacked on the several tool tool in the oven set to predetermined | prescribed temperature and pressure, and the said resin layer mutually fuse | melting and hardening. At this time, since there is no pressure difference between the inside and the outside of the hardened composite material, it is possible to prevent the occurrence of cracks or wrinkles in the spar of the aircraft wing formed in the flange portion.

As described above, the method for manufacturing a tool for a composite aircraft wing and the method for manufacturing a wing of a composite aircraft according to the present invention have the following advantages.

First, it is possible to easily implement a tool of the correct shape in consideration of the thickness of the composite material to be laminated.

Second, it can improve the quality of the product, such as to prevent wrinkles in the spar of the composite wing.

Although the present invention has been described with reference to one embodiment shown in the drawings, it is merely exemplary, and can be modified in various forms by those skilled in the art within the technical scope of the present invention.

Claims (4)

A method of manufacturing a multi-box tool for use in the manufacture of a wing of a composite aircraft having a plurality of spars installed upright between an upper and a lower skin and an upper and lower skin forming an outer shape, the master having the same outer shape as the wing. A first step of laying up materials on the upper and lower surfaces of the model, respectively, to form a first upper jig corresponding to the upper skin and a first lower jig corresponding to the lower skin; A second step of separating a first lower jig from the master model and laying up materials on inner surfaces of the first upper jig and the first lower jig, respectively, to form a second upper jig and a second lower jig having a predetermined thickness; And a third step of respectively forming a plurality of upstanding bulkheads at positions corresponding to the spars on the outer surfaces of the second upper jig and the second lower jig, and the second upper jig and 2 a fourth step of laying up the material on the outer surface of the lower jig and the upright bulkhead to form a plurality of third upper jig and third lower jig with flanges at both ends thereof, and the third upper jig corresponding to each other; And a fifth step of combining the third lower jig to form a plurality of box-shaped tools corresponding to the shape of each part of the aircraft wing. The method of claim 1, wherein the thickness of the second upper jig and the second lower jig is the same as the thickness of the composite material of the aircraft wing. The method of claim 1, further comprising the step of installing a mutual support for supporting the outer surface of the first upper jig and the first lower jig, respectively. The composite material according to claim 1, further comprising installing a partition wall to form a space for receiving a coupling screw in at least one of the third upper jig and the third lower jig to be coupled to each other. Method of manufacturing a tool for aircraft wing.

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