JPH1147959A - Manufacture of outside sheet - Google Patents

Abstract

PROBLEM TO BE SOLVED: To facilitate the manufacturing of an outside sheet in a complicated shape by preparing the outside sheet member and its reinforcing member each singly for friction stirring welding. SOLUTION: The material of the stringer 1 and the skin 2 is an aluminum alloy or an aluminum lithium alloy sufficiently. The cross sectional shape of the stringer 1 may be freely selected such as an L-shape and I-shape, with no linearity requirement in the longitudinal direction. The friction stirring welding may be continuous, spot or staggered welding. In the outside sheet of an aircraft, the shape of the stringer 1 is changed so as to reduce the area that comes into contact with the skin 2, for the purpose of reducing the weight as well as the cost of manufacture through a simplified shape. A high tensile aluminum alloy like 2024Al, 7075Al, etc., causes cracks in fusion welding, making a sufficient joint characteristic unavailable and also bringing up a problem of deformation. However, by employing friction stirring welding, the stringer 1 and the skin 2 can be joined with high efficiency and at low cost.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a method for manufacturing an outer panel applied to an aircraft, a rocket, a high-speed vehicle, a high-speed ship, and others.

[0002]

2. Description of the Related Art FIG. 4 is an explanatory view of a conventional outer panel used for an aircraft body or the like. In the figure, the outer panel of the body of an aircraft has a structure in which a skin 02 and a stringer 01 for reinforcing the skin 02 are joined together with rivets 05.

[0003] In addition, although not shown, a conventional outer plate used for a rocket or the like has a structure in which a rib and a skin are integrally formed by shaving a skin and a rib for reinforcing the skin from a thick plate material by machining. ing.

[0004] Further, although not shown, a conventional outer plate used for a vehicle body of a high-speed vehicle or the like has a structure in which extruded mold members are joined together by welding and are integrally assembled.

[0005]

As shown in FIG. 4, in the case of a skin of a conventional aircraft body or the like, a stringer 0 is used.
Since the joint 1 and the skin 02 are joined by the rivets 05, the joint efficiency is poor, and the portion of the stringer 01 overlapping the skin 02 has little significance in terms of strength, and only increases the weight. Further, the cross-sectional shape of the stringer 01 is complicated and the manufacturing cost is high.

Further, in the case of a conventional outer plate such as a rocket, since a thick plate material is machined to cut a skin and ribs for reinforcing the skin by machining, the machining allowance of the plate material is extremely large. High material costs and high machining costs. Also,
In the case where the skin has a curved surface, the plate material is too thick to be bent, so it is bent after shaving. In this case, too, the rigidity differs depending on the presence or absence of the ribs, and it is extremely difficult to bend.

Further, in the case of a conventional outer plate of a vehicle body of a high-speed vehicle, a high-strength aluminum alloy or the like cannot be used because welding is used for joining extruded members. In addition, thickness 1
Extruded profiles of less than mm cannot be manufactured and must be cut after extrusion.

[0008]

SUMMARY OF THE INVENTION An object of the present invention is to provide a method of manufacturing an outer panel, which comprises the steps of separately forming an outer panel member and a reinforcing member for the outer panel member. The plate member and the reinforcing member are connected by friction stir welding.

Further, in the method for manufacturing an outer plate according to the present invention, a reinforcing member of the outer plate member having a joint portion having the same thickness as the outer plate member is provided between a plurality of outer plate members by friction stir welding. To combine.

Further, in the method for manufacturing an outer panel according to the present invention, a plurality of extrusion members in which an outer panel member and a reinforcing member of the outer panel member are integrated are connected to each other by friction stir welding. .

As described above, in the method of manufacturing an outer panel according to the present invention, an outer panel member such as a skin and a reinforcing member of the outer panel member such as a stringer are separately formed and joined by friction stir welding. By separately forming and joining the outer plate member and the reinforcing member of the outer plate member, it is possible to cope with various shapes.

Further, by connecting the outer plate member and the reinforcing member by friction stir welding, the materials of the outer plate member and the reinforcing member can be freely selected, and the cutting allowance by machining can be reduced.

[0013]

DESCRIPTION OF THE PREFERRED EMBODIMENTS FIG. 1 is an illustration of an aircraft skin according to a first embodiment of the present invention, and FIG. 2 is an illustration of an aircraft skin according to a second embodiment of the invention. FIG. 3 is an illustration of an aircraft skin according to a third embodiment of the present invention.
In the drawings, the skin of the aircraft according to these embodiments can be used not only for the aircraft but also for the skins of rockets, high-speed vehicles, high-speed ships, and the like. Reference numeral 1 denotes a stringer for reinforcing the skin 2, reference numeral 3 denotes friction stir welding for joining the skin 2 and the stringer 1, and reference numeral 4 denotes an extruded material of the stringer 1 and the skin 2.

In FIG. 1, an outer skin of an aircraft according to the first embodiment is, as shown in FIG. 1, an L-shaped extruded shape member or a sheet material formed on a skin 2 made of a flat or curved plate material. The stringer 1 is formed by friction stir welding as shown in FIG. The outer skin of the aircraft shown in FIG. 1A has a stringer 1 butted against a skin 2 in a T-shape, and the corners of both are friction stir welded in a fillet weld shape. The outer skin of the aircraft shown in FIG. 2 (b) is formed by forming the end of the stringer 1 into a T-shape, and friction stir welding the T-shaped end and three places from the skin 2 side. Is higher in strength than the skin of the aircraft in FIG.

The materials of the stringer 1 and the skin 2 may be different as long as they are aluminum alloy or aluminum lithium alloy. Further, the stringer 1 may be I-shaped instead of L-shaped, and the cross-sectional shape can be freely selected. Further, the stringer 1 does not need to be linear, and it is not necessary to continuously join the stringer 1 and the skin 2 by friction stir welding.

As described above, in the outer panel of the aircraft, the shape of the stringer 1 is changed to a shape having less contact with the skin 2, so that the weight of the portion where the stringer 1 contacts the skin 2 can be reduced. The structure is such that the skin 2 and the stringer 1 are directly connected by friction stir welding so that the manufacturing cost can be reduced by simplifying the shape of the stringer 1. High-strength aluminum alloys such as 2024Al and 7075Al used in aircraft are cracked when joined by fusion welding, failing to obtain sufficient joint properties and causing distortion due to fusion welding. Friction stir welding is adopted. This joining method by friction stir welding can be applied to all aluminum alloy joints, and has advantages such as high joint strength and low distortion. The stringer 1 and the skin 2 can be joined with high efficiency and low cost. It becomes possible to combine.
Further, the cross-sectional shape of the stringer 1 is simplified, and the manufacturing cost is reduced.

In FIG. 2, the skin of the aircraft according to the first embodiment has a stringer 1 and a skin 2 made of separate parts, whereas the skin of the aircraft according to the second embodiment As shown in the figure, a part of the stringer 1 is integrated with the skin 2. Combined with stringer 1 and skin 2
Are performed using friction stir welding. The friction stir welding may be one-pass welding from one side or two-pass welding from both sides. Thus, the same operation and effect as those of the aircraft skin according to the first embodiment can be obtained.

In FIG. 3, as shown in the figure, the outer skin of the aircraft according to the third embodiment is formed by fusion welding of extruded members on the outer skin of a conventional high-speed vehicle body or the like by friction stir welding. And the material of the extruded shape 4 can be freely selected by changing the joining method. For this reason, 7075
High-strength aluminum alloys such as Al can also be used. In addition, friction stir welding has a small deformation of members due to joining, so that a distortion correction step, which was indispensable in the case of fusion welding, is not required, so that manufacturing costs can be reduced. Operations and effects similar to those of the aircraft skin according to the embodiment can be obtained.

In the case of a skin of a conventional aircraft body as shown in FIG. 4, the stringer and the skin are joined by rivets, so that the joint efficiency is poor. Has little meaning,
It only results in an increase in weight. Further, the cross-sectional shape of the stringer is complicated and the manufacturing cost is high. In the case of conventional rockets and other outer plates, the machining allowance of the plate material is extremely large because the ribs that reinforce the skin are cut together with the skin by machining from the thick plate material. High machining cost. Also, if the skin has a curved surface, the plate material will be bent after shaving because it is too thick and difficult to bend. hard. Also, in the case of a conventional outer plate such as a vehicle body of a high-speed vehicle, a high-strength aluminum alloy or the like cannot be used because welding is used for joining extruded members. Extruded molds having a thickness of 1 mm or less cannot be manufactured, so they need to be cut after extrusion.

On the other hand, in the skin of the aircraft according to each of the above-described embodiments, the stringer 1 and the skin 2 are used to reduce the weight, increase the strength, improve the degree of freedom of the sectional shape, and reduce the manufacturing cost. Are made separately and joined by friction stir welding. By forming and joining the stringer 1 and the skin 2 separately, it is possible to cope with various shapes. Further, by using friction stir welding as a method of joining the stringer 1 and the skin 2, the material of the stringer 1 and the skin 2 can be freely selected. Further, the materials of the stringer 1 and the skin 2 can be changed. In addition, the machining allowance is small, and the machining cost of the material can be reduced. Also,
By connecting the stringer 1 and the rivet in a linear manner, the shape of the stringer 1 is simplified, and the manufacturing cost and weight of the stringer can be reduced.

Further, the weight of the outer skin of the aircraft according to each of the above embodiments can be reduced by about 20% as compared with the conventional outer skin of the aircraft shown in FIG.
Although the material cost and processing cost of the stringer 1 can be reduced by 20% or more, the cost is increased by about 10% by changing from the rivet connection to the friction stir welding, so that the cost is reduced by about 10%. Is possible. Further, the cost can be reduced by 50% or more as compared with the conventional rocket outer plate. In addition, the use of an aluminum alloy having a higher strength than that of a conventional outer panel of a high-speed vehicle can reduce the weight by 20% or more. In addition, the cost can be reduced by eliminating the need for correcting distortion after welding.

[0022]

The method of manufacturing an outer plate according to the present invention is as described above, and it is possible to cope with various shapes by separately forming and joining the outer plate member and the reinforcing member of the outer plate member. Therefore, even an outer plate having a complicated shape can be easily manufactured.

Further, since the material of the outer plate member and the reinforcing member can be freely selected by connecting the outer plate member and the reinforcing member by friction stir welding, for example, a high-strength aluminum alloy is used. This makes it possible to reduce the weight of the outer plate, and eliminates the need to correct distortion after the outer plate member and the reinforcing member are joined. Further, since the machining allowance for machining is reduced, material costs and machining costs can be reduced.

[Brief description of the drawings]

FIG. 1 is an explanatory diagram of a method for manufacturing an aircraft outer panel according to a first embodiment of the present invention.

FIG. 2 is an explanatory diagram of a method for manufacturing an aircraft skin according to a second embodiment of the present invention.

FIG. 3 is an explanatory diagram of a method for manufacturing an aircraft outer panel according to a third embodiment of the present invention.

FIG. 4 is a cross-sectional view of a skin of a conventional aircraft.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Stringer 2 Skin 3 Friction stir welding 4 Extrusion material

Claims (3)

[Claims] An outer plate member and a reinforcing member for the outer plate member are separately formed, and the outer plate member and the reinforcing member are joined by friction stir welding. Production method. 2. The outer plate member according to claim 1, wherein a reinforcing member of the outer plate member having the same thickness as the outer plate member is joined between the plurality of outer plate members by friction stir welding. Production method. 3. A method for manufacturing an outer plate, comprising: a plurality of extruded members in which an outer plate member and a reinforcing member of the outer plate member are integrated with each other by friction stir welding.