JPH10246391A - Compressive resistant type flexible thermal insulation material - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a compressive resistant type flexible thermal insulation material which has the flexibility, can be made large, and is mounted on an outer surface of a machine body by arranging heat-resistant cloths no both faces of a composite thermal insulation material like a sheet constituted by incorporating a tilelike thermal insulation material into holes of a lattice of a feltlike thermal insulation material formed like a lattice. SOLUTION: A compressive resistant type flexible thermal insulation material is constituted by arranging heat resistant cloths 4, 5 on a top face and a bottom face of a composite thermal insulation material 3 formed by a feltlike thermal insulation material 1 formed like a lattice and a plurality of tilelike thermal insulation materials 2 incorporated into holes of a lattice formed by the thermal insulation material 1. These heat resistant cloths 4, 5 are sewn each other to the feltlike thermal insulation material 1 by using a heat resistant thread 6 and are fixed and are bonded on a surface of a main structure 8 by using adhesive 7. Ceramic fiber is used as the feltlike thermal insulation material 1 from the viewpoint of resistance against heat, and a material obtained by mixing silica fiber and mullite fiber at a weight mixture ratio of 75 to 25, adding boron nitride of 3.6% and silicon carbide whisker of 5% to the mixture, blending them, and baking and solidifying them is used as the tilelike thermal insulation material 2.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a compression-resistant flexible heat insulating material mounted on the outer surface of an airframe such as a spacecraft.

[0002]

2. Description of the Related Art Conventionally, ceramic tiles (applied to the leeward side of the fuselage) and flexible thermal insulators (applied to the leeward side of the fuselage) have been used as heat insulating materials attached to the outer surface of the body of a conventional spacecraft. Was.

First, the ceramic tile will be described in detail with reference to FIG. Ceramic tile 01
Is a solid heat insulating material, which is cut out in accordance with the shape of the machine body and is mounted on the main structure 8 of the machine body via a filler bar 8a or a ship 8b. The vertical and horizontal dimensions of the ceramic tile 01 are set to about 30 in order to follow the deformation of the main structure 8 of the body.
The size is about 0 mm.

[0004] In addition, the ceramic tile 01 needs to be provided with a gap at the boundary between the tiles in order to thermally expand, and further, to prevent a temperature rise due to aerodynamic heating, the height difference between the ceramic tiles is set within an allowable value. There is a need to.

Next, the above-mentioned flexible heat insulating material will be described in detail with reference to FIG. The flexible heat insulating material is a blanket in which a felt-like heat insulating material 02 provided with a tape material 03 on a side thereof is sewn together with heat-resistant cloths 4 and 5 and can be bent by hand according to the shape of the machine. Things. The flexible heat insulating material can follow the deformation of the fuselage, and the vertical and horizontal dimensions can be set arbitrarily.

[0006]

Problems to be solved by ceramic tiles and flexible heat insulating materials which are conventional heat insulating materials will be described below.

(1) Since the ceramic tile cannot be enlarged in length and width, and is cut out in accordance with the shape of the machine, the number of parts increases and the cost increases. In addition, it is necessary to control the gap and the height difference of the mating portion of the tiles, and it takes a lot of time and effort to mount, and the cost is high.

(2) The thickness of the flexible heat insulating material changes with a small load, and it is difficult to apply the heat insulating material to the windward side of the body. Further, the manufacturing accuracy is poor, and irregularities occur on the surface as shown in FIG.

The present invention solves the problems of the above-described heat insulating materials, has flexibility, can be enlarged, can be easily attached to an airframe, and ensures high manufacturing accuracy in the thickness direction. An object is to provide a heat insulating material that is possible and does not deform under a compressive load.

[0010]

According to a first aspect of the present invention, there is provided a compression-resistant flexible heat-insulating material comprising a felt-like heat-insulating material formed in a grid and a grid formed by the felt-like heat-insulating material. A sheet-shaped composite heat insulator formed by a plurality of tile-shaped heat insulators incorporated in the holes, and a heat-resistant material that is arranged on both sides of the composite heat insulator and sewn to the felt heat-insulating material with heat-resistant thread and fixed It is characterized by being formed by a cloth.

[0011] The compression-resistant flexible heat-insulating material according to the present invention is affixed to the surface of the main structure of a spacecraft or the like with an adhesive, and comprises a felt-like heat-insulating material having flexibility and a thickness direction. A composite heat insulating material formed of a tile-shaped heat insulating material effective for maintaining the shape of the base material is a base material.

Therefore, the compression-resistant flexible heat-insulating material according to the present invention also has flexibility due to the felt-like heat-insulating material, and it is possible to increase the size of the single heat-insulating material.
Installation on the surface of the main structure such as a space shuttle is easy.

[0013] Further, since the shape of the heat insulating cloth can be maintained in the thickness direction by the tile-shaped heat insulating material, it is possible to prevent compression deformation during sewing of the heat-resistant cloth, and it is possible to ensure high manufacturing accuracy and to apply a compressive load. This makes it possible to prevent deformation of the airframe, and to apply it to the windward side of the fuselage.

[0014]

DESCRIPTION OF THE PREFERRED EMBODIMENTS A compression-resistant flexible heat insulating material according to an embodiment of the present invention will be described with reference to FIG. In addition,
This embodiment is arranged on the surface of the main structure 8 of the spacecraft in which the temperature becomes 1000 to 1300 ° C.

The compression-resistant flexible heat-insulating material according to the present embodiment shown in FIG. 1 is incorporated into a felt-like heat insulating material 1 formed in a lattice shape and holes in the lattice formed by the felt-like heat insulating material 1, respectively. Heat-insulating cloths 4 and 5, respectively disposed on the upper and lower surfaces of the composite heat-insulating material 3 formed by the plurality of tile-shaped heat insulating materials 2 and the felt-shaped heat insulating materials 1 and the tile-shaped heat insulating materials 2. 5 is formed by a heat-resistant thread 6 stitched and fixed to the felt-like heat insulating material 1 forming the composite heat insulating material 3, and is adhered to the surface of the main structure 8 by an adhesive 7.

The compression-resistant flexible heat-insulating material according to the present embodiment comprises:
A composite heat insulating material 3 formed by combining a grid-like felt heat insulating material 1 having flexibility and a tile heat insulating material 2 effective for maintaining the shape in the thickness direction is formed as a base material.

Therefore, the compression-resistant flexible heat-insulating material according to the present embodiment also has flexibility, so that it is possible to increase the size of the heat-insulating material alone, and to provide a gap of a predetermined size between the conventional heat-insulating materials. As a result, it is not necessary to perform the bonding work for attaching the tile-shaped heat insulating material 2 to the surface of the main structure 8.
Easy to mount to.

The felt-like heat insulating material 1 of the composite heat insulating material 3
Since the tile-shaped heat insulating material 2 prevents compression deformation at the time of sewing the heat resistant cloths 4 and 5 to each other, the smoothness of the surface is improved, and high production accuracy can be secured. Furthermore, the tile-shaped heat insulating material 2 can eliminate deformation due to a compressive load, and a flexible heat insulating material can be used on the windward side of the fuselage.

Next, the specific contents of each material forming the compression-resistant flexible heat insulating material of the present embodiment will be described in detail. As the material of the felt-like heat insulating material 1, ceramic fibers are used from the viewpoint of heat resistance.

Among these ceramic fibers, there are silica fiber, alumina fiber, zirconia fiber, and silicon carbide fiber, but the low thermal conductivity (0.084 kcal / mh ° C at 538) required for the compression-resistant flexible heat insulating material. ° C., as to achieve the atmosphere) and low density (0.10 g / cm ^3), mullite fibers made of silica and alumina, the heat insulating material obtained by mixing silica fibers and silicon carbide whiskers is most effective. In this case, a mixture of silica fibers and mullite fibers in a weight ratio of 2: 8, to which 5 wt% of silicon carbide whiskers are added, is suitable.

The size of the lattice of the felt-like heat insulating material 1 is determined by the compression elastic modulus of the tile-like heat insulating material 2, the allowable compression thickness against the compressive force in the thickness direction, and the required flexibility (bending curvature). The space shuttle "HO"
In consideration of application to PE ", as shown in FIG. 2, the interval between the suturing lines was set to 25 mm, and the tile-shaped heat insulating material 2 having a width of 15 mm was placed in a grid having a width of 25 mm.

The height of the lattice of the felt-like heat insulating material 1 is determined by the thickness required for heat insulation, but the height required for heat insulation of the main structure of "HOPE" is about 40 mm. From about 120 mm.

The heat insulating material 2 has a heat resistance of 1
300 ° C, compression elasticity is 253kgf / cm ^TwoAbove, the compressive strength
4.4kgf / cm^TwoAbove, the density is 0.12 g / cm^ThreeBelow, heat transfer
Conductivity is 0.095w / m · K (at 550 ° C 0.01atm
 )

In order to satisfy this condition, the material is
The same as the felt-like heat insulating material 1 except that the weight mixing ratio of the silica fiber and the mullite fiber is 75:25, which is 3.6
% Of boron nitride and 5% of silicon carbide whiskers are suitably hardened.

The materials of the heat resistant cloths 4 and 5 include silica fiber, alumina fiber, silicon carbide fiber and glass fiber. The heat resistant cloth on the high temperature side (1300 ° C.) mainly includes silica fiber and alumina fiber. A cloth or silicon carbide fiber cloth as a component is effective.

The thickness of the cloths of the heat resistant cloths 4 and 5 varies depending on the fiber specification, but in this embodiment, the interlock fiber specification is assumed, and the thickness is about 1 mm to 3 mm.

The material of the heat-resistant yarn 6 is the same as that of the heat-resistant cloths 4 and 5, and the thickness thereof varies depending on the number of twisted yarns.
The thickness is about 1.5 mm.

[0028]

The compression-resistant flexible heat insulating material of the present invention comprises a felt-like heat insulating material having a grid-like flexibility and a plurality of heat-insulating materials which are incorporated into the respective holes of the grid and can maintain the shape in the thickness direction. A sheet-shaped composite heat insulating material formed by the above-mentioned tile-shaped heat insulating material, and a heat-resistant cloth which is provided on both surfaces of the composite heat-insulating material and sewn to the felt-shaped heat insulating material by the heat-resistant thread and fixed. This makes it possible to increase the size of a single piece of heat insulating material because of its flexibility, so it can be easily attached to the surface of the main structure of a space shuttle, etc., and can maintain its shape in the thickness direction. Therefore, compression deformation at the time of sewing the heat-resistant cloth can be prevented, and high production accuracy can be ensured. In addition, deformation can be prevented by a compression load, and application to the windward side of the machine body is possible.

[Brief description of the drawings]

FIG. 1 is an explanatory view of a compression-resistant flexible heat insulating material according to an embodiment of the present invention.

FIG. 2 is a diagram illustrating the size of a grid of a felt-like heat insulating material according to the embodiment.

FIG. 3 is an explanatory view of a conventional ceramic tile.

FIG. 4 is an explanatory view of a conventional flexible heat insulating material, where (a) is a perspective view,
(B) is an enlarged view of the part A of (a).

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Felt-like heat insulating material 2 Tile-like heat insulating material 3 Composite heat insulating material 4,5 Heat resistant cloth 6 Heat resistant thread 7 Adhesive 8 Main structure

 ──────────────────────────────────────────────────続 き Continued on the front page (72) Fumito Takeda, Inventor Nagoya Aerospace System Works, Mitsubishi Heavy Industries, Ltd. 10 Oecho, Minato-ku, Nagoya

Claims (1)

[Claims] 1. A sheet-like composite heat insulating material formed by a felt-like heat insulating material formed in a lattice shape and a plurality of tile-like heat insulating materials incorporated in respective holes of a lattice formed by the felt-like heat insulating material. And a compression-resistant flexible heat-insulating material which is provided on both sides of the composite heat-insulating material, and is formed by a heat-resistant cloth sewn to the felt-like heat-insulating material and fixed by heat-resistant thread.