JP2882099B2 - Composite honeycomb structural material - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a composite honeycomb structural material.

[0002]

2. Description of the Related Art Space structural materials, for example, substrates on which various measuring devices are installed, are required to have heat resistance, light weight, high rigidity, high strength, dimensional stability (high thermal conductivity), etc., and other space equipment. Similar requirements have been made for members such as aircraft and propulsion systems of aircraft, acoustic effect materials, and the like, and a composite honeycomb structural material has been proposed as a material that meets these requirements.

[0003] A conventional composite honeycomb structural member is constructed as shown in FIG. 4 using an aluminum material which is lightweight and has high strength.

That is, as shown in FIG. 4A, an adhesive 2 is provided between two thin aluminum plates 1 at a required interval.
Then, another thin aluminum plate 1 is overlaid and bonded with an adhesive 2 so as to be bonded at an intermediate portion of the position where the thin aluminum plate 1 is bonded by the adhesive 2, and this operation is repeated to repeat the required number of thin aluminum plates 1 Glue.

Subsequently, as shown by an arrow 3, the upper and lower thin aluminum plates 1 are deformed by applying a tensile force so as to separate them from each other, thereby forming a honeycomb core having a honeycomb hole 4 as shown in FIG. 5 is formed.

Subsequently, two aluminum substrates 6 and 6 are prepared so as to sandwich both ends of the hole 4 of the honeycomb core 5 in the axial direction.
As shown in (C), the honeycomb core 5 and the aluminum substrate 6 are integrally bonded with an adhesive 7 to form a composite honeycomb structural member 8.

[0007]

However, in the above-mentioned conventional system, the thin aluminum plates 1 are adhered to each other with an adhesive 2 to form the honeycomb core 5 and the honeycomb core 5 and the aluminum substrate 6 are interposed. Even with such adhesives 2 and 7, the temperature range that can be used is as low as 150 to 250 ° C. even when a polyimide-based adhesive having high heat resistance is used. In some cases, it cannot be used as structural material for equipment.

Further, the adhesives 2 and 7 generally have low thermal conductivity, so that the composite honeycomb structural material 8 is liable to generate thermal strain, and the adhesive surface is peeled off in a short period of time, or the stability of the structure is impaired. There is a possibility.

The present invention has been made in view of the above-mentioned conventional problems, and an object of the present invention is to provide a composite honeycomb structural material capable of greatly expanding the usable temperature range and achieving dimensional stability and high rigidity. Aim.

[0010]

According to the present invention, a thin aluminum plate is formed into a corrugated shape so that irregularities are alternately continuous, and spot welding is performed so as to form a honeycomb with the corrugated aluminum plate. A composite honeycomb comprising a honeycomb core, and a fiber-reinforced metal plate having a bonding material diffusion-bonded to a bonding surface integrally bonded to both end surfaces in the axial direction of the holes of the honeycomb of the honeycomb core by brazing. It depends on the structural material.

[0011]

According to the present invention, a thin aluminum plate is formed into a corrugated plate,
A fiber in which a honeycomb core is formed by spot welding so as to form a honeycomb formed by the corrugated aluminum plate, and a brazing material is diffusion-bonded to an adhesive surface at both axial end surfaces of the honeycomb holes of the honeycomb core. A reinforced metal plate is integrally bonded by brazing to form a composite honeycomb structural material.

[0012]

Embodiments of the present invention will be described below with reference to the drawings.

FIG. 1 shows an embodiment of the composite honeycomb structural member according to the first aspect of the present invention.

As shown in FIG. 1A, a thin aluminum plate 1
Is passed between the forming gears 11 and 12 provided with the concave portions 9 and the convex portions 10 alternately on the outer peripheral surface and provided so as to mesh with each other, so that the concave and convex portions are alternately and continuously formed into a corrugated plate shape. A corrugated aluminum plate 13 is formed.

In this case, the corrugated aluminum plate 13 may be formed by using a press or the like.

The corrugated aluminum plate 13 thus obtained
Are welded by spot welding 14 so as to form a honeycomb having holes 4 as shown in FIG.

On the other hand, a fiber reinforced metal plate 21 as shown in FIG. 2 for forming a composite honeycomb structural material together with the honeycomb core 15 is formed.

The fiber-reinforced metal plate 21 is formed by arranging reinforcing fibers 22 on the upper surface of an aluminum thin plate (foil), plasma-spraying aluminum from above, and then applying the plasma-sprayed aluminum to the upper surface of the aluminum in the direction of the reinforcing fibers 22. On the other hand, another reinforcing fiber 22 is arranged in the direction of 90 °, plasma spraying of aluminum is performed again, and this operation is repeated to obtain a required thickness.

Further, an aluminum alloy brazing material 23
At a temperature lower than the brazing temperature of the brazing material 23 (20 to 40 μm).

The honeycomb core 15 is sandwiched by the fiber-reinforced metal plate 21 configured as described above so that the brazing material 23 side faces the axial end face of the honeycomb hole of the honeycomb core 15 shown in FIG. 1B. Further, as shown in FIG. 3A, the brazing is performed at a temperature slightly lower than the melting point of the brazing material 23 by the heating furnace 19 while maintaining the pressurized state by the holding device 18.

The thus obtained composite honeycomb structural member indicated by reference numeral 24 in FIG. 3 (B) is reinforced by the fiber reinforced metal plate 21, so that it is lightweight and can achieve high strength.

Further, since the brazing material 23 is uniformly adhered to the fiber reinforced metal plate 21 by diffusion bonding in advance, the honeycomb core 15 and the fiber reinforced metal plate 21 can be formed with a minimum uniform thin brazing material 23. Can be bonded with high strength.

The composite honeycomb structural member of the present invention is not limited to the above-described embodiment, but may be variously modified without departing from the gist of the present invention.

[0024]

As described above, according to the composite honeycomb structural member of the present invention, since the assembly is performed by spot welding and brazing, the composite honeycomb structural member is compared with a conventional assembly using an adhesive. In addition, the temperature range that can be used can be greatly expanded, and the effect of achieving dimensional stability and high rigidity can be achieved.

Further, since the brazing material is diffusion-bonded to the bonding surface of the fiber-reinforced metal plate, the bonding strength can be increased by the least uniform adhesion by the diffusion bonding of the brazing material, and the use of the fiber-reinforced metal plate can be achieved. Light weight and high strength can be achieved.

[Brief description of the drawings]

FIG. 1 shows an example of a case where a honeycomb core is manufactured, and FIG. 1 (A) is a side view showing a state in which a corrugated aluminum plate is formed;
(B) is a perspective view of a formed state of the honeycomb core.

FIG. 2 is an enlarged side view of a fiber reinforced metal plate.

3A and 3B show an example of a case where a composite honeycomb structural material is formed, in which FIG. 3A is a side view showing a state in which the composite honeycomb structural material is formed by brazing, and FIG. It is a perspective view of the composite honeycomb structure material which was made.

4 (A) and 4 (B) are perspective views showing a procedure for forming a honeycomb core, and FIG. 4 (C) is a perspective view showing a procedure for forming a honeycomb composite material according to the related art. FIG. 2 is a perspective view of the composite honeycomb structural member of FIG.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Thin aluminum plate 4 Hole 13 Corrugated aluminum plate 14 Spot welding 15 Honeycomb core 21 Fiber reinforced metal plate 23 Row material 24 Composite honeycomb structure material

──────────────────────────────────────────────────続 き Continued on the front page (51) Int.Cl. ⁶ Identification code FI B32B 3/12 B32B 3/12 Z C23C 4/06 C23C 4/06

Claims (1)

(57) [Claims] 1. A honeycomb core is formed by forming a thin aluminum plate into a corrugated shape so that irregularities are alternately continuous, and performing spot welding so as to form a honeycomb with the corrugated aluminum plate. A composite honeycomb structural material comprising a fiber-reinforced metal plate having a brazing material diffusion-bonded to an adhesive surface and integrally bonded to both end surfaces in the axial direction of the honeycomb holes of the core by brazing.