JP2001192000A - Heat-resistant felt spacer - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a heat-resistant felt spacer eliminating the step of a heat insulating material connection section adapted to a space shuttle. SOLUTION: The thickness of the heat insulating material is set according to the heating rate distribution of an airframe for an airframe structure section 30, the thickness of the heat insulating material differs by place, and a step is generated at the connection section. Although the connection section of the heat insulating materials 20, 21 has a step, a wedge-like spacer 10 is inserted and stuck between the heat insulating material 21 thinner in thickness and the airframe side structure section 30. The heat insulating materials 20, 21 are made equal in height at the connection section by the spacer 10, the thinner heat insulating material 21 is inclined in a tapered state and gradually made lower, and the abrupt step shown in the past disappears. The breakage caused by overheat and dynamic pressure at the connection section is eliminated, the heat insulating material 21 is not required to be raised to the level of the heat insulating material 20 to eliminate the step, and a weight increase is prevented.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a heat-resistant felt spacer, which is used for adjusting the thickness of a heat insulating material for a spacecraft and is intended to eliminate a step at a connecting portion of the heat insulating material.

[0002]

2. Description of the Related Art In a spacecraft, high heat is generated on the surface of an airframe due to friction with the atmosphere. In order to prevent the high heat from entering the interior of the airframe, a heat insulating material is mounted on the surface of the airframe. The heat insulating material is set and manufactured to a required thickness in accordance with the heating rate distribution of each location of the body, and there are places where heat insulating materials having different thicknesses are attached adjacently depending on the location.

FIGS. 6A and 6B are cross-sectional views showing a heat insulating material applied to a spacecraft. FIG. 6A shows a step portion of a connecting portion of heat insulating materials having different thicknesses, FIG. 6B shows a thermal effect of the step portion, (C) shows a state where the step is eliminated. In (a),
A heat insulating material 20 and a heat insulating material 21 are adhered to the structural side portion 30 on the body side in accordance with the heating rate distribution of the body. Since the thicknesses of the heat insulating materials 20 and 21 are different, there is a step t at the connecting portion between the two. However, the reason for keeping the step as it is is that the point where the thickness is not necessary to reduce the weight of the body as much as possible is reduced. In order to reduce the weight by making it as thin as possible, a step occurs.

In FIG. 6 (b), when the spacecraft re-enters the atmosphere at the portion adjacent to the heat insulating materials 20 and 21 as described above, the heating rate partially increases due to this step, and the heat resistant temperature of the heat insulating material is increased. , Causing a decrease in strength and melting of the material. Further, the dynamic pressure P is applied to the step, and deformation occurs at the joint of the step, the heating rate increases at the portion B, and the surface is broken. As a countermeasure, there is a method of raising the heat insulating material 22 by the heat insulating material 22 so as to have the same thickness at the step portion as shown in FIG. It is disadvantageous in weight. Specifically, the heat insulating material 20 has a thickness of about 38 mm and a heat insulating material 2.
There is a place where the thickness of 1 is about 25 mm, and the heat insulating material 22 that fills the step needs to be 13 mm thick, which is a wasteful increase in spacecraft that requires light weight. .

[0005]

As described above, in order to avoid an unnecessary increase in the weight of the heat insulating material applied to the spacecraft, the heat insulating material having a different thickness depending on the heating rate distribution is used. The material is attached, which results in a step at the adjacent joint. If there is a step, the heating rate is increased in the step, exceeding the heat resistant temperature of the heat insulating material, and the strength of the material is reduced and the material is melted. In addition, when the dynamic pressure P is applied to the step, the heat insulating material is deformed and the surface is destroyed, and the broken part gradually expands, and high heat enters the inside from this part, causing serious trouble. become.

Therefore, according to the present invention, by inserting a spacer into a connecting portion of a heat insulating material applied to a space shuttle, etc., a steep step at the connecting portion is eliminated, and a straight, gentle slope or a smooth curve is obtained. An object of the present invention is to provide such a heat-resistant felt spacer.

[0007]

The present invention provides the following means (1) to (4) to solve the above-mentioned problems.

(1) Applied to the joint of the heat insulating material of the body of the spacecraft, the thickness is determined according to the heating rate distribution of the body, and the step of connecting the heat insulating materials having different thicknesses to each other is eliminated. A spacer, which is inserted between the heat insulating material on the side where the thickness of the connecting portion is small and the machine body side, equalizes the surface heights of both heat insulating materials at the connecting portion, and has the side where the thickness is small. A heat-resistant felt spacer having a wedge shape inclined toward the heat insulating material.

(2) The spacer is divided into a number of wedge-shaped heat-resistant felt pieces, and the plurality of felt pieces are bonded to one sheet-like heat-resistant felt. The heat-resistant felt spacer described in parentheses.

(3) The heat-resistant felt spacer according to (1), wherein the spacer is integrally formed.

(4) The heat-resistant felt spacer according to (1), wherein the wedge-shaped tapered surface of the spacer has a smooth curved surface.

In (1) of the present invention, the wedge-shaped spacers equalize the surface heights of the connecting portions of the heat insulating materials having different thicknesses, eliminate the steps, and gently incline toward the side having the smaller thickness. . Therefore, the heat-insulating material on the thinner side can be connected to the heat-insulating material on the larger-thickness side at the connection portion without generating a step, and can be gradually inclined and adhered to the machine body side. Therefore, the connection portion of the heat insulating material is not damaged by the step, and the heat insulating effect is maintained.

In (2) of the present invention, since the spacer is divided into a number of felt pieces, the spacer can be adhered closely along the curved surface on the fuselage side, and can be constructed without wrinkles or the like. it can. In this case, the bonding surface of the spacer to the fuselage side is the surface opposite to the sheet-shaped felt when the surface is bonded to a convex curved surface, and the sheet-shaped felt when the bonding surface is a concave curved surface. If the surfaces are bonded to each other, the felt pieces are compressed, and the heat insulating material can be applied without generating a gap between the adjacent felt pieces.

In the method (3) or (4) of the present invention, since the spacer is integrally formed, the work can be easily performed on a portion having a linear bonding surface or a bonding surface with little change. Further, even if the tapered surface is a curved surface as in (4) of the present invention, the same effects as those of the above (1) can be obtained.

[0015]

Embodiments of the present invention will be specifically described below with reference to the drawings. FIG. 1 is an overall perspective view of the heat-resistant felt spacer according to the first embodiment of the present invention. In (a), 10 indicates a spacer,
The spacer 10 is formed by arranging a large number of wedge-shaped felts 1 having the same shape in contact with one sheet-like felt 2 and adhering to the sheet-like felt 2.

The wedge-shaped spacer 1 is constituted by arranging a large number of felt pieces 1a as shown in FIG. Felt piece 1
a has a wedge shape, and an example of specific dimensions thereof is as follows:
It is a small piece of about L = 70 mm, H = 12 mm, and W = 10 mm. In order to process a thin wedge-shaped piece of about W = 10 mm, a 10 mm flat felt is cut out. This is adhered to the sheet-like felt 2 to manufacture the spacer 10. This felt is made of heat-resistant fiber and has a heat-resistant temperature of 30.
It can be used up to about 0 ° C and has the characteristic of insulating heat transmitted through the outer surface of the fuselage.

FIG. 2 is a perspective view of a heat-resistant felt spacer according to a second embodiment of the present invention, in which a spacer 10 having the same shape as that of FIG. Such a spacer according to the second embodiment is effective when the height H of the spacer is relatively thick and the shape can be easily integrated, and the surface of the body to be bonded has a linear shape as described later. It is advantageous when applied to places where there is little change.

FIG. 3 is a perspective view of a heat-resistant felt spacer according to a third embodiment of the present invention. FIGS. 3A and 3B are manufactured by integral processing, and the tapered portion is shown in FIGS. The spacers shown are straight, but all have a smooth arcuate curved surface. (A) has a tapered portion formed with a convex smooth curved surface, and (b) has a concave curved surface formed on the contrary.

FIG. 4 shows an example in which the heat-resistant felt spacer according to the first to third embodiments of the present invention is applied to a connection portion of a heat insulating material. FIG. 4A shows the first embodiment of the present invention for convenience of explanation. In the example using the spacer 10, a cross-sectional view thereof is shown,
(B) is an AA sectional view in (a).

In FIG. 4A, reference numerals 20 and 21 denote heat insulating materials having different thicknesses. The connecting portions have a step, and the spacer 10 is inserted into the step. A spacer 10 is inserted between the heat insulating material 21 having a small thickness and the body-side structure 30 at a connection portion between the two heat-insulating materials 20 and 21, and the end face of the heat-insulating material 20, the body-side structure 30 and the heat insulating material 21 are inserted. Glued to the bottom. As a result, the surfaces of the connecting portions of the heat insulating materials 20 and 21 are connected at the same height, and the heat insulating material 21 is connected to the heat insulating material 20 by a linear gentle slope, so that the conventional sharp step Disappears.

The spacer 10 is inserted so that the adjacent felt pieces 1a are compressed as shown in FIG.
In the illustrated example, the sheet-like felt 2 of the spacer 10 is attached to the fuselage-side structure 30 by bonding. If the surface on which the heat insulating material is to be attached to the fuselage-side structural portion 30 is a convex curved surface as shown in the figure, the sheet-like felt 2 is bonded to the fuselage-side structural portion 30 so that the side surfaces of a large number of felt pieces 1a are joined together. Are in contact with each other, the gap 40 is not generated, and the spacer 10 is divided into a large number of felt pieces 1a. Therefore, the adhesive can be easily formed along the curved surface without wrinkles or the like.

FIG. 5 shows a state in which the spacer 10 is adhered to the body-side structure 30 in the first embodiment, and shows a case where the mounting surface of the spacer 10 is a convex curved surface. (A) is an example in which the sheet-like felt 2 is bonded to the fuselage-side structure 30. In this case, since the curved surface to be bonded is convex, each felt piece 1a is attached to the side surface of the adjacent felt piece 1a. A gap 40 is generated, and this gap 4
In addition, since the heat insulating effect is reduced due to 0, the adhesive invades into the gap 40 at the time of mounting, and the weight increases by that amount, which is not preferable.

On the other hand, in (b), the surface to be bonded to the machine body side structural portion 30 is bonded to the opposite side of the sheet-like felt 2. When bonded in this manner, the side surfaces of the felt pieces 1a adjacent to each other are compressed with each other, so that no gap is generated. Therefore, the close contact along the curved surface is improved by the large number of divided felt pieces 1a, and a good mounting state is maintained without any gap.

The application example of the above-described spacer has been described with reference to the example of the spacer 10 of the first embodiment. However, in a similar manner, the spacers 11, 12, and 13 of the second and third embodiments are used.
Can also be applied. These spacers 11, 12,
Reference numeral 13 denotes an integrally processed product, which is not divided by the felt pieces 1a unlike the spacer 10, so that it is an effective spacer in the case of bonding to a place having a small curvature and a straight surface with little change. The same effects as in the first embodiment can be obtained. Note that the spacers 12 and 13 of the third embodiment shown in FIG. 3 may be divided into a number of felt pieces and used as in FIG.

In the heat-resistant felt spacers according to the first to third embodiments described above, the spacer between the thinner heat insulator 21 and the body-side structure is formed at the connection between the heat insulators 20 and 21. Insert 10, 11, 12, 13 and heat insulating material 21
The surface of the end is combined with the heat insulating material 20 having a large thickness, and the connection is made at a smooth inclination to eliminate a sudden step, so that damage at the connection portion is prevented and the reliability of the heat insulating material construction is improved. is there.

[0026]

The heat-resistant felt spacer of the present invention is
(1) A spacer that is applied to the thermal insulation joints of the spacecraft of the space shuttle and whose thickness is determined according to the heating rate distribution of the aircraft and that eliminates the level difference between the joints of the thermal insulations with different thicknesses. The heat insulating material is inserted between the heat insulating material on the side where the thickness of the connecting portion is small and the body side, and makes the surface heights of both heat insulating materials equal at the connecting portion, and the heat insulating material on the side where the thickness is small It is characterized in that it has a wedge shape that slopes toward. With such a spacer, the surface heights of the connecting portions of the heat insulating materials having different thicknesses are made equal, the step is eliminated, and the connecting portions are gently inclined toward the side having the smaller thickness. for that reason,
The heat-insulating material having a smaller thickness can be connected to the heat-insulating material having a larger thickness at the connection portion without forming a step, and can be gradually inclined and adhered to the body side. Therefore, the connection part of the heat insulating material is not damaged by the step, and a local increase in the heating rate can be prevented.

In (2) of the present invention, since the spacer is divided into a number of felt pieces, it can be adhered closely along the curved surface on the fuselage side, and can be constructed without wrinkles or the like. it can. In this case, the bonding surface of the spacer to the fuselage side is the surface opposite to the sheet-shaped felt when the surface is bonded to a convex curved surface, and the sheet-shaped felt when the bonding surface is a concave curved surface. If the surfaces are bonded to each other, the felt pieces are compressed, and the heat insulating effect is improved without forming a gap between the adjacent felt pieces.

In the method (3) or (4) of the present invention, since the spacer is integrally formed, the work can be easily performed on a portion having a linear bonding surface or a bonding surface with little change. Further, even if the tapered surface is a curved surface as in (4) of the present invention, the same effects as those of the above (1) can be obtained.

[Brief description of the drawings]

FIGS. 1A and 1B show a heat-resistant felt spacer according to a first embodiment of the present invention, wherein FIG. 1A is an overall perspective view, and FIG.
It is a perspective view of the spacer piece in FIG.

FIG. 2 is a perspective view of a heat-resistant felt spacer according to a second embodiment of the present invention.

FIGS. 3A and 3B show a heat-resistant felt spacer according to a third embodiment of the present invention, wherein FIGS.
It is a perspective view of the spacer which has a concave curved surface.

4A and 4B show application examples of the heat-resistant felt spacer according to the first embodiment of the present invention, wherein FIG. 4A is a cross-sectional view, and FIG. 4B is a cross-sectional view taken along the line AA in FIG.

FIGS. 5A and 5B are cross-sectional views showing application examples of the heat-resistant felt spacer according to the first embodiment of the present invention, wherein FIG. 5A shows an unfavorable example and FIG. 5B shows a preferable application example.

6A and 6B show a connection portion of a conventional heat insulating material, in which FIG. 6A is a cross-sectional view of a stepped portion, FIG. 6B is a cross-sectional view of a broken portion of the connection portion, and FIG. FIG.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Wedge-like felt 1a Felt piece 2 Sheet-like felt 10, 11, 12, 13 Spacer 12a, 13a Curved surface 20, 21 Insulation material 30 Airframe side structural part 40 Gap

Claims (4)

[Claims] The present invention is applied to a heat insulating material joint portion of a body of a spacecraft, and has a thickness determined in accordance with a heating rate distribution of the body and eliminates a step in a connecting portion of heat insulating materials having different thicknesses. A spacer, which is inserted between the heat insulator on the side where the thickness of the connecting portion is small and the machine body side, equalizes the surface heights of both heat insulators at the connection portion, and A heat-resistant felt spacer having a wedge shape inclined toward a heat insulating material. 2. The heat-sensitive felt is divided into a plurality of wedge-shaped pieces of heat-resistant felt, and the plurality of pieces of felt are bonded to one sheet-like heat-resistant felt. Heat resistant felt spacer as described. 3. The heat-resistant felt spacer according to claim 1, wherein the spacer is formed integrally. 4. The heat-resistant felt spacer according to claim 1, wherein the wedge-shaped tapered surface of the spacer has a smooth curved surface.