JP4316057B2 - Composite wing - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a composite material wing capable of remarkably reducing the number of parts and assembling man-hour and reducing cost. SOLUTION: A plurality of composite material intermediate beams 2 in which upper and lower surfaces of flanges 5, 6 form a partial shape of a wing surface are coupled so that surface shapes of the flanges 5, 6 may be smoothly continuous, the intermediate beams 2 molded into U-shapes in cross section by composite materials are arranged in the same direction so that a base end part external surface and an opening end internal surface may come into surface contact with the adjacent intermediate beams 2 and the adjacent intermediate beams each other are coupled by a fastener means 3.

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention relates to a composite wing applied to an aircraft body structure and the like.
[0002]
[Prior art]
Many of the conventional aircraft main wings have a build-up structure made of an aluminum material, but in order to reduce the weight, aircraft main wings using a composite material made of fiber-reinforced resin having a high specific strength have been developed.
The conventional aircraft composite wing is constructed by assembling separately formed lower skin, upper skin, girders and small bones with an assembly jig, and lower skin, upper skin, girders and small bones by fastener means. It is configured by combining the outer plate on one side, the girders, and the small bones into a composite material integrally formed product, and connecting the outer plate on the other surface to the composite material integrated product by fastener means.
[0003]
[Problems to be solved by the invention]
The composite wing of an aircraft that has a lower outer plate, upper outer plate, girders, and small bones as fasteners has a built-up structure, and even though weight reduction is achieved compared to the main wing of aluminum material, the number of parts increases, In addition, since a special assembly jig is required for assembly, the cost increases.
[0004]
Aircraft composite wings with only one side made of composite material are integrated with the conventional structural concept as they are, which complicates the jig and molding process and increases costs.
[0005]
The present invention has been made in view of the above points, and an object of the present invention is to provide a composite blade that can greatly reduce the number of parts and the number of assembling steps and can reduce costs.
[0006]
[Means for Solving the Problems]
The composite material blade of the present invention includes a plurality of intermediate girders of a composite material formed in a U-shaped cross section by a pair of upper and lower flanges and a web integrally connecting the upper and lower flanges, and the plurality of intermediate girders are prepregs. And changing the number of prepregs to be laminated on the inner surface of each open end of the upper and lower flanges, respectively, by changing the number of layers of the upper and lower flanges. The second engagement portions formed thinner than the thickness of the intermediate portion of the upper and lower flanges are respectively provided on the outer surfaces of the base ends of the upper and lower flanges, and the first engagement of one of the intermediate girders adjacent to each other. The joint portion and the second engaging portion of the other intermediate girder are engaged with each other so as to be in surface contact with each other, so that the number of parts and assembly man-hours are greatly reduced and the cost is reduced. The To function.
[0007]
DETAILED DESCRIPTION OF THE INVENTION
Embodiments of the present invention will be described below with reference to the drawings.
FIG. 1 is a perspective view showing an example in which a composite wing according to the present invention is applied to a main wing 1 of an aircraft. The main wing 1 of an aircraft includes an intermediate girder 2a and a plurality of intermediate girders 2 formed into a U-shaped cross section with a composite material. , 2... Are engaged with each other so that the edges in the longitudinal direction are in surface contact, and adjacent intermediate girders are joined by fastener means 3 (FIG. 3).
[0008]
As shown in FIG. 2, each intermediate beam 2, 2 a has a shape that continuously extends from the blade root to the blade tip in a tapered shape corresponding to a shape obtained by dividing the main wing 1 to be molded into a plurality of portions in the longitudinal direction. is there. The intermediate girders 2 and 2a are formed by, for example, a thermosetting composite material lamination method.
[0009]
As shown in FIGS. 2 and 3, each intermediate girder 2, 2 a includes a web portion 4 constituting a side plate and a flange portion 5 of a horizontal plate integrally connected to the upper and lower ends of the web portion 4. , 6 in cross section. The intermediate girders 2 and 2a are arranged so that the upper flange portion 5 and the lower side when the base end portion outer surface and the open end inner surface of the U-shaped cross section are joined in surface contact with each other so as to constitute the main wing 1 shown in FIG. The flange portion 6 forms a part of the wing, and the upper surface of the upper flange portion 5 of the intermediate girder 2 and the lower surface of the lower flange portion 6 form a part of the wing surface of the main wing 1.
[0010]
As shown in FIG. 5, the intermediate girder 2 a located on the end side has an engaging portion 5 a on the inner surface of the opening end of the upper flange portion 5 and an engaging portion 6 a on the inner surface of the opening end of the lower flange portion 6. The engaging portions 5a and 6a of the intermediate beam 2a are formed by changing the number of prepregs stacked when the intermediate beam 2a is formed. The wall thicknesses of the upper flange portion 5 of the intermediate beam 2a located on the end side and the open ends 5a, 6a of the lower flange portion 6 are set to be thinner than the thickness of the intermediate portion, for example, about 1/2. . When the two adjacent intermediate girders 2 are engaged so as to be in surface contact with each other, the upper surface of the upper flange portion 5 and the lower surface of the lower flange portion 6 of the two intermediate girders 2a, 2 are smooth. It is for forming.
[0011]
As shown in FIG. 5, reinforcing members 7 and 7 formed separately from a composite material or aluminum or titanium alloy are provided on the inner side of the intermediate girder 2a located on the end side by fastener means 3a. Before being combined. Accordingly, the intermediate beam 2a has a structure that functions as a rear beam of the main wing 1.
[0012]
As shown in FIG. 5, each intermediate girder 2 includes an engagement portion 5 a on the inner surface of the opening end of the upper flange portion 5, an engagement portion 5 b on the outer surface of the base end, and an engagement portion on the inner surface of the opening end of the lower flange portion 6. a 6a and the proximal outer surface that has been closed and an engaging portion 6b. The engaging portions 5a, 5b, 6a, 6b of the intermediate beam 2 are formed by changing the number of prepregs stacked when the intermediate beam 2 is formed. The thickness of the wall thickness and the proximal end of the open mouth end of each intermediate digit of the thickness and the proximal end of the opening end of the upper flange portion 5 of the 2 thick and the lower flange portion 6 is thinner than the thickness of the intermediate portion, For example, the thickness is set to about ½. When the two intermediate girders 2 are engaged so as to come into surface contact, the upper surface of the upper flange portion 5 and the lower surface of the lower flange portion 6 of the two intermediate girders 2a, 2 form a gentle blade surface of the main wing 1. This is to make it happen.
[0013]
Further, inside the intermediate beam 2, a reinforcing member, or a bent tube 8 formed separately or a holder of another device, as shown in FIG. 6, are connected to each other by the fastener means 3b or the secondary bonding means. Combined before doing.
[0014]
There is a method of forming the intermediate girders 2 and 2a by a thermosetting resin impregnation method in addition to the thermosetting composite material laminating method. However, since there is no difference from the conventional method, the description is omitted. .
[0015]
Next, a method for manufacturing the main wing 1 of an aircraft using the intermediate girders 2 and 2a will be described.
First, as shown in FIG. 5, the reinforcing members 7, 7 separately formed on the inner surface of the base end of the intermediate beam 2a located on the end side are joined by the fastener means 3a. In addition, a fixing member for fixing a support member of various apparatuses is attached. Since the reinforcement members 7 and 7 can be joined to the intermediate beam 2a by visual observation, the attachment is easy.
[0016]
Next, as shown in FIG. 5, the intermediate beam 2a and the intermediate beam 2 are arranged in parallel in the same direction so that the base end of the intermediate beam 2 is fitted to the opening end of the intermediate beam 2a. The intermediate beam 2 is pushed into the intermediate beam 2a in the direction indicated by the arrow A so that the base end of the intermediate beam 2 engages with the open end of the intermediate beam 2a, and the engagement portion 5a on the inner surface of the upper end of the upper flange portion 5 of the intermediate beam 2a The engaging portion 6 a on the inner surface of the opening end of the lower flange portion 6, the engaging portion 5 b on the outer surface of the proximal end of the upper flange portion 5 of the intermediate beam 2, and the engaging portion 6 b on the outer surface of the proximal end of the lower flange portion 6 are in surface contact. Engage.
[0017]
The intermediate beam 2a and the intermediate beam 2 are coupled to each other by rivets 10 and 10 by an automatic hammering device 9 shown in FIG. Since the upper and lower flange portions 5 and 6 of the intermediate beam 2a and the upper and lower flange portions 5 and 6 of the intermediate beam 2 are set so as to form a part of the wing, they are coupled to each other so as to constitute the main wing 1 shown in FIG. When this is done, the upper surface of the upper flange portion 5 and the lower surface of the lower flange portion 6 of the intermediate girders 2a, 2 form part of the blade surface of the main wing 1. In this case, the thickness of the engaging portions 5a, 5b, 6a, 6b is thinner than the thickness of the intermediate portion, for example, by making the thickness of the intermediate portion 1/2, the intermediate beam 2a and the intermediate beam engaged with each other. The upper surface of the upper flange portion 2 and the lower surface of the lower flange portion 6 form a blade surface of the main wing 1 that is gently connected.
[0018]
Next, as shown in FIG. 6, the bent tube 8 formed separately is joined to the inner side of the base end of the intermediate beam 2a connected to the intermediate beam 2a located on the end side by the fastener means 3a. A reinforcing member or the like is also attached. Since the connection of the vent tube 8 to the intermediate beam 2 can be performed by visual observation, the attachment is easy.
[0019]
Next, as shown in FIG. 6, the adjacent intermediate beam 2 is arranged in parallel in the same direction so that the proximal end portion is fitted to the opening end of the intermediate beam 2 to which the vent tube 8 is attached. The proximal end portion of the intermediate beam 2 adjacent to the open end of the attached intermediate beam 2 is pushed in, and the engaging portion 5a and the lower flange portion 6 on the inner surface of the upper end of the upper flange portion 5 of the intermediate beam 2 to which the vent tube 8 is attached. The engaging portion 6b on the inner surface of the opening end of the intermediate flange 2 and the engaging portion 5b on the outer surface of the proximal end of the upper flange portion 5 of the intermediate beam 2 and the engaging portion 6b on the outer surface of the proximal end of the lower flange portion 6 are engaged.
[0020]
The intermediate beam 2 adjacent to the intermediate beam 2 to which the vent tube 8 is attached is coupled to the engaging portion by rivets 10 and 10 by an automatic hammering device 9 shown in FIG. Since the upper and lower flange portions 5 and 6 of the intermediate beam 2 and the upper and lower flange portions 5 and 6 of the intermediate beam 2 adjacent to the intermediate beam 2 are set so as to form a part of the wing, the main wing 1 shown in FIG. When coupled to each other, the intermediate beam 2 and the upper surface of the upper flange portion 5 of the intermediate beam 2 and the lower surface of the lower flange portion 6 form part of the blade surface of the main wing 1. In this case, the thickness of the engaging portions 5a, 5b, 6a, 6b is adjusted so that the thickness of the intermediate portion is adjusted, and the upper surface and the lower flange of the intermediate flange 2 and the upper flange portion 5 of the intermediate beam 2 engaged with each other. The wing surface of the main wing 1 is formed so that the lower surface of the portion 6 is smoothly connected.
[0021]
A plurality of intermediate girders 2 are integrally coupled to the intermediate girders 2 thus joined by sequentially repeating the same operation, and finally a U-shape with a flange shortened at the opening of the U-shaped intermediate girders 2. Or the main wing | blade 1 of an aircraft is comprised by joining an I-type girder.
[0022]
Although the intermediate girder of the U-shaped cross section has been described above, the intermediate girder is not limited to the U-shaped. For example, an intermediate girder 2b having an I-shaped cross section as shown in FIG. 7 can be used, or both a U-shaped intermediate girder 2 and an I-shaped intermediate girder 2b can be used together as shown in FIG. it can. In this case, an opening cannot be used to connect these intermediate girders. However, if a general blind fastener is used for assembling an aircraft, the intermediate girders can be coupled.
[0023]
In addition, it was explained that after attaching the intermediate girder, a reinforcing member or fixing member attached to the intermediate girder or an attachment such as equipment was attached. If the arrangement of the attachments is taken into consideration so that the workability does not deteriorate, the intermediate girders are joined after fixing the attachments to the intermediate girders in advance. You can also.
In addition to rivets, bolts can be used as fasteners.
[0024]
【The invention's effect】
As described above, the composite blade according to the present invention has a composite intermediate girder having a web that integrally connects the upper and lower flanges forming a part of the upper and lower blade outer plates and the surface shape of the upper and lower flanges. Since it is constructed by connecting multiple units so that they continue smoothly, the number of parts and assembly man-hours that make up the composite wing can be greatly reduced, cost can be reduced, and access to the inside during the assembly process It is easy to attach parts to the inside and can easily perform non-destructive inspection.
In the composite blade according to the present invention, the intermediate girder formed in a U-shaped cross section with the composite material is arranged in the same direction so that the outer surface of the base end and the inner surface of the opening end are in surface contact with the adjacent intermediate girder. Since the intermediate girders are joined together by fastener means, the number of parts and assembly man-hours that make up the composite wing can be greatly reduced, the cost can be reduced, and access to the inside during the assembly process It is easy to attach parts to the inside and can easily perform non-destructive inspection.
[Brief description of the drawings]
FIG. 1 is an exploded perspective view showing an example in which a composite wing according to the present invention is applied to an aircraft main wing.
FIG. 2 is an exploded perspective view of the main wing shown in FIG.
FIG. 3 is a view showing a connecting portion of an intermediate beam of a composite wing according to the present invention.
FIG. 4 shows a coupling device for intermediate girders of a composite wing according to the present invention.
FIG. 5 is a diagram showing a stage before joining of intermediate girders of a composite wing according to the present invention.
FIG. 6 shows the stage after the joining of the intermediate girders of the composite wing according to the invention.
FIG. 7 is a diagram showing coupling of intermediate girders having an I-shaped cross section.
FIG. 8 is a view showing a connection between an intermediate girder of an I-shaped cross section and an intermediate girder of a U-shaped cross section;
[Explanation of symbols]
DESCRIPTION OF SYMBOLS 1 Aircraft main wing 2 Intermediate girder 3 Fastener means 4 Web part 5 Upper flange part 5a, 5b Engagement part 6 Lower flange part 6a, 6b Engagement part

Claims (2)

A plurality of intermediate girders of a composite material formed into a U-shaped cross section with a pair of upper and lower flanges and a web that integrally couples these upper and lower flanges ,
The plurality of intermediate digits are
By changing the number of prepregs stacked, the first engaging portion formed thinner than the thickness of the intermediate portion of the upper and lower flanges is provided on the inner surface of each open end of the upper and lower flanges, and the number of prepregs stacked is changed. A second engaging portion formed thinner than the thickness of the middle portion of the upper and lower flanges on the outer surface of each base end of the upper and lower flanges,
The first engaging part of one intermediate girder adjacent to each other and the second engaging part of the other intermediate girder are engaged with each other so as to be in surface contact with each other, and are integrally coupled <br / > Composite wing characterized by that. The composite blade is main wing of an aircraft, the composite blade according to claim 1, characterized in that the intermediate girder extends in the tip direction from the blade root.

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