JP2000128092A - Sandwich structure for outer space cruiser - Google Patents

Abstract

PROBLEM TO BE SOLVED: To eliminate the need for an extra adhesive and reducing the mass by sandwiching the end of a side part made of film between a surface member and a core member and securing the side part to a sandwich structure upon adhesion of the surface member and the core member. SOLUTION: A side part 6 made of film is sandwiched between a surface member 4 and a core member 5, and secured to the surface member 4 and the core member 5 with an adhesive 7. Here, there is no need to apply an adhesive to the side part 6 in advance. The adhesive 7 for securing the side part 6 need be applied only to a portion contacting the surface member 4 and the core member 5. Further, as a material of the side part 6, a polyimide film, a metal-evaporated fluorine resin film, or the like are used. As a material of the adhesive 7, an epoxy resin, a cyanate resin, a polyimide resin, or the like are used. This makes it possible to reduce the mass of a sandwich structure and prevent peeling of the side part.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a sandwich structure constituting a so-called space navigation body such as an artificial satellite or a space station. FIG. 3 is a diagram showing an artificial satellite, for example, a solar cell panel 1, a satellite structure 2,
A sandwich structure is used for the antenna reflector 3.

[0002]

2. Description of the Related Art FIG. 4 shows the structure of a conventional sandwich structure having parts (hereinafter, referred to as side parts) attached so as to wrap the side surfaces. Is a side part, and 7 is an adhesive. Side parts 6
The adhesive 8 is applied, and after the skin material 4 and the core material 5 are bonded, the side component 6 is fixed to the skin material 4 by the adhesive force of the adhesive 8. In some cases, the side component 6 is coated with an adhesive instead of an adhesive. There are two main functions of the side surface components. One is to prevent sunlight from entering from the side surface of the sandwich structure in outer space and to suppress a rise in temperature of the sandwich structure. Another one
One is to prevent a part of the core material from jumping out of the sandwich structure and attaching to other parts of the spacecraft when the core material is removed.

FIG. 5 shows the structure of a conventional sandwich structure having side parts different from that of FIG. The side component 6 has a strength that is not easily crushed during the sandwich molding, and the side component 6 is sandwiched between the pair of skin materials 4 at the same time as the skin material 4 and the core material 5 are adhered. It is fixed to 4. Note that a molded product of fiber reinforced plastic is generally used for the side part 6.

[0004]

In the conventional sandwich structure as shown in FIG. 4, there is a problem that the weight increases due to the necessity of applying an adhesive or an adhesive to the side parts. Further, in space, the temperature may be -100 ° C or lower, but when the temperature is -100 ° C or lower, there is a problem that the adhesive strength of the adhesive is reduced and the adhesive is easily peeled.

[0005] In the conventional sandwich structure as shown in FIG. 5, the thickness of the side parts needs to be increased so that the side parts have a strength that is not easily crushed when the skin material and the core material are bonded. There was a problem that the mass increased.

SUMMARY OF THE INVENTION The present invention has been made to solve such a problem, and a side part formed of a film is sandwiched between a skin material of a sandwich structure and a core material to thereby provide a side part having a conventional structure. It is characterized in that the weight is lighter than that of the sandwich structure, and that the side parts do not peel off since no adhesive is required.

[0007]

In the sandwich structure according to the first aspect of the present invention, an end of a side part formed of a film is sandwiched between a skin material and a core material, so that the skin material and the core material are simultaneously bonded and sandwiched. By fixing to the structure, the weight is reduced by eliminating the need for an extra adhesive or adhesive compared to the sandwich structure having the side parts of the conventional structure. This is to prevent peeling.

Further, in the sandwich structure according to the second invention, the side component formed of the film according to the first invention is integrated with an electric insulating material which is a component of a skin material of the sandwich structure of the solar cell panel. This eliminates the need for extra side parts and adhesive in the prior art, thereby reducing the mass.

[0009]

DESCRIPTION OF THE PREFERRED EMBODIMENTS Embodiment 1 FIG. 1 is a view showing Embodiment 1 of the present invention, and is an enlarged view of a side surface of a sandwich structure used for the solar cell panel 1 in FIG. In the figure, 4 is a skin material, 5 is a core material,
6 is a side part, 7 is an adhesive. The side part 6 formed of a film is sandwiched between the skin material 4 and the core material 5 and is fixed to the skin material 4 and the core material 5 by an adhesive 7.
In the sandwich structure having such a structure, the side parts 6
It is not necessary to apply an adhesive 8 in advance, and the adhesive 7 for fixing the side parts 6 is only required to be in contact with the skin material 4 and the core material 5. Can be lighter. Further, since the adhesive is unnecessary, the side parts can be prevented from peeling off.

[0010] Examples of the material for the side parts include a polyimide film and a fluororesin film on which metal is deposited. Examples of the material of the adhesive include an epoxy resin, a cyanate resin, and a polyimide resin.

Embodiment 2 FIG. 2 shows a second embodiment of the present invention. As a side part in the first invention, it is integrated with an electric insulating material 9 which is a constituent part of a skin material of the sandwich structure. Such a sandwich structure eliminates the need for the side parts and adhesives of the prior art. Further, the side part 6 in the first invention
The adhesive 7 is not required for fixing to the skin material 4, so that the mass is lighter than that of the sandwich structure in the related art.

A solar panel is mounted on the spacecraft to supply electric power, and between the sandwich structure on which the solar cells are mounted and the solar cells is provided for electrical insulation. Generally, a polyimide film is used. Since this polyimide film can be used also as a side part of the sandwich structure, it is possible to integrate the side part with the electric insulating material as in the second embodiment.

[0013]

According to the first aspect of the present invention, it is not necessary to apply a pressure-sensitive adhesive to the side parts in advance, and the adhesive for fixing the side parts is only required to be in contact with the skin material and the core material. The weight can be reduced as compared with a sandwich structure having a conventional structure. Further, since the adhesive is not required, the side parts do not peel off.

According to the second aspect of the present invention, the mass can be reduced as compared with the conventional sandwich structure.
Further, since the side component according to the first aspect of the present invention is integrated with the electric insulating material, an adhesive for fixing the side component according to the first aspect of the present invention to the skin material is unnecessary. The mass can be made lighter than the structure.

[Brief description of the drawings]

FIG. 1 is a diagram showing Embodiment 1 of a sandwich structure according to the present invention.

FIG. 2 is a view showing a sandwich structure according to a second embodiment of the present invention;

FIG. 3 is a diagram showing an artificial satellite.

FIG. 4 is a view showing the structure of a conventional sandwich structure.

FIG. 5 is a view showing the structure of another conventional sandwich structure different from FIG. 4;

[Explanation of symbols]

1 solar panel, 2 satellite structure, 3 antenna reflector, 4 skin material, 5 core material, 6 side parts, 7
Adhesive, 8 adhesive, 9 electrical insulation.

 ──────────────────────────────────────────────────続 き Continued on the front page F term (reference) 4F100 AK49A AK49C AK49G AK53G AT00A AT00B AT00C BA03 BA06 BA10A BA10C CB00 DB01 DB02 DC00B GB90 JG04A JG04C JK06 JL03

Claims (2)

[Claims] 1. A sandwich structure forming part of a space vehicle, comprising a skin material, a core material, and a component that is attached so as to wrap around the side surface, and an adhesive.
A sandwich structure for a space navigation body, wherein a part constituted by a film attached so as to wrap the side surface is integrally fixed to a sandwich panel by sandwiching an end portion between a skin material and a core material. 2. A solar cell panel for a spacecraft, wherein a part formed of a film which is attached so as to wrap the side surface is integrated with an electric insulating material which is a constituent part of the solar cell panel. The sandwich structure for a space navigation vehicle according to claim 1.