JP2000335500A - Heat insulating structure - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a heat insulating structure, capable of withstanding the severe vibrational environment in launching of a spacecraft and having a structure panel as a base body not to be broken even if a radiator panel is cooled in an outer space. SOLUTION: A heat insulating structure is constituted of a base body 1, a radiator panel 2 arranged outside the base body 1 and having a long hole 2a, a spacer 3 arranged between the base body 1 and the radiator panel 2, and a rod-shaped fastening means 5 erected on the base body 1 near the spacer 3, inserted in the long hole 2a of the radiator panel 2 and having the linear expansion coefficient different from that of the spacer 3. The rod-shaped fastening means 5 can use a bolt 5 having an external thread part to be screwed to an internal thread part formed on the base body 1.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a heat insulating structure,
In particular, the present invention relates to a heat insulating structure used for a spacecraft or the like.

[0002]

2. Description of the Related Art Conventionally, as a heat insulating mechanism for a spacecraft,
For example, a mechanism described in JP-A-4-19300 has been proposed.

As shown in FIGS. 4 and 5, the heat insulating mechanism described in this publication has a structure panel 1 for a spacecraft.
A heat insulating collar 3 is attached between the radiator panel 2 and the radiator panel 2 disposed outside the structural panel 1 to insulate the structural panel 1 and the radiator panel 2 from each other. Here, since the spacecraft is exposed to a severe vibration environment at the time of launch, the radiator panel 2 is firmly connected to the structural panel 1.

[0004]

However, in the above-mentioned conventional heat insulating mechanism, the radiator panel 2 becomes low in temperature and contracts due to radiant cooling in outer space. However, the temperature of the structural panel 1 is reduced since it is insulated. 6, the compressive load in the direction of the arrow X acts on the structural panel 1 as shown in FIG. 6, and the structural panel 1 may be damaged.

In view of the above, the present invention has been made in view of the above-mentioned problems in the conventional heat insulating structure, and can withstand a severe vibration environment at the time of launching a spacecraft and the like. An object of the present invention is to provide a heat insulating structure in which a structural panel or the like as a base is not damaged even when cooled.

[0006]

In order to achieve the above object, the invention according to claim 1 comprises a base, a radiator panel disposed outside the base and having a long hole, the base and the radiator. A spacer interposed between the panel and
A rod-shaped fastening means which stands on the base in the vicinity of the spacer, is inserted into the elongated hole of the radiator panel, and has a linear expansion coefficient different from the linear expansion coefficient of the spacer. .

The invention according to a second aspect is characterized in that the rod-shaped fastening means is a bolt having a male screw portion screwed into a female screw portion formed on the base.

According to a third aspect of the present invention, the base is a structural panel of a spacecraft, wherein a linear expansion coefficient of the rod-shaped fastening means is smaller than a linear expansion coefficient of the spacer.

According to the first aspect of the present invention, in a normal state, the base and the radiator panel are firmly connected by the rod-shaped fastening means, and the rod-shaped fastening means having a smaller linear expansion coefficient than the spacer is used. When the radiator panel is cooled, the radiator panel shrinks and the spacer shrinks more than the rod-shaped fastening means,
Since the fastening force of the rod-shaped fastening means is lost and the radiator panel slides with respect to the base, no compressive load is applied to the base, and damage to the base can be prevented.

On the other hand, when the rod-shaped fastening means having a larger linear expansion coefficient than that of the spacer is used, when the radiator panel is exposed to a high temperature, the radiator panel expands and the rod-shaped fastening means becomes larger than the spacer. Greatly expanded,
Since the fastening force of the rod-shaped fastening means is lost and the radiator panel slides with respect to the base, no tensile load is applied to the base, and damage to the base can be prevented.

According to a second aspect of the present invention, as a preferred embodiment of the heat insulating structure according to the present invention, the rod-shaped fastening means has a male screw part which is screwed into a female screw part on which the base is formed. It can be configured by bolts, and a simple configuration can provide an inexpensive heat insulating structure.

According to the third aspect of the present invention, the radiator panel is firmly connected to the structural panel in order to withstand a severe vibration environment at the time of launch, and when the radiator panel becomes low temperature in outer space, Even when the panel shrinks, no compression load is applied to the structural panel, and damage to the structural panel can be prevented.

[0013]

Next, a specific example of an embodiment of a heat insulating structure according to the present invention will be described with reference to the drawings.
Note that, also in this embodiment, a case will be described in which the heat insulating structure according to the present invention is applied to a spacecraft.

FIGS. 1 and 2 are sectional views showing a state before launch of a spacecraft having a heat insulating structure according to the present invention. The heat insulating structure 10 includes a structural panel 1 as a base.
A radiator panel 2 having a long hole 2a, a heat insulating collar 3 as a spacer, a heat insulating washer 4, and a bolt 5 as a rod-shaped fastening means.

The radiator panel 2 needs to be firmly connected to the structural panel 1 in order to withstand a severe vibration environment when the spacecraft is launched. Therefore, after placing the heat-insulating collar 3 on the structural panel 1, the long hole 2a is positioned on the heat-insulating collar 3, the heat-insulating washer 4 is further placed on the radiator panel 2, and finally the male screw of the bolt 5 is placed. Part 5
and the female screw portion 1a of the structural panel 1 is screwed.

Here, the linear expansion coefficient of the bolt 5 is set to be smaller than the linear expansion coefficient of the heat insulating collar 3. For example, when the material of the heat insulating collar 3 is GFRP, the bolt 5 has a linear expansion coefficient higher than that of GFRP. Select a small titanium alloy. If the linear expansion coefficient of the bolt 5 is set to be smaller than that of the heat insulating collar 3, the heat insulating collar 3 and the bolt 5
May be formed of a polymer material or a metal material.

The longitudinal dimension of the elongated hole 2a of the radiator panel 2 is set to be larger than the contraction amount of the radiator panel 2. For example, when the contraction amount S of the radiator panel 2 is 5 mm, the length of the long hole 2a of the radiator panel 2 needs to be 5 mm or more.

Next, the operation of the heat insulating structure 10 having the above configuration will be described.

Before the launch of the spacecraft, the heat insulating structure 10 is in a state as shown in FIGS. 1 and 2, and the radiator panel 2 is firmly connected to the structural panel 1.

When the spacecraft reaches outer space and the radiator panel 1 becomes cold, the heat insulating collar 3 and the bolts 5 in contact with the radiator panel 1 also become cold. Here, since the linear expansion coefficient of the bolt 5 is set smaller than that of the heat insulating collar 3, as shown in FIG.
Contracts more than the bolt 5, and the bolt 5 loses its tightening force. Then, since the radiator panel 2 has the elongated hole 2a, the radiator panel 2 is released from the restraint by the bolt 5, and can be freely contracted in, for example, the arrow Y direction,
No compressive load acts on the structural panel 1. Thereby, damage to the structural panel 1 can be prevented.

In the above embodiment, the case where the radiator panel 2 and the like are exposed to a low temperature environment has been described. Conversely, when the radiator panel 2 and the like are exposed to a high temperature environment, the bolt 5 By setting the linear expansion coefficient of the bolt 5 to be larger than that of the heat insulating collar 3, the bolt 5 can expand more than the heat insulating collar 3 and lose the tightening force of the bolt 5, whereby the elongated hole 2a of the radiator panel 2 can be reduced. As a result, the radiator panel 2 is released from the restraint by the bolt 5 and can expand freely. Therefore, a compressive load does not act on the structural panel 1 and damage to the structural panel 1 can be prevented.

In the above embodiment, the case where the heat insulating structure according to the present invention is applied to a space vehicle has been described. However, the present invention is not limited to the space vehicle, but may be applied to a substrate before being exposed to a low-temperature or high-temperature environment. When the radiator panel that needs to be bonded to the radiator panel needs to be configured to contract or expand when exposed to a low or high temperature environment, the heat insulating structure according to the present invention can be applied.

[0023]

As described above, according to the first aspect of the present invention, in the normal state, the base and the radiator panel are firmly connected by the rod-shaped fastening means, and can withstand a severe vibration environment. Even when the radiator panel is cooled or exposed to a high temperature, it is possible to provide a heat insulating structure in which the substrate is not damaged without reinforcing the substrate as in the related art.

According to the second aspect of the present invention, the rod-shaped fastening means can be constituted by a bolt having a male screw portion which is screwed into the female screw portion on which the base is formed. An inexpensive heat insulating structure can be provided.

Further, according to the second aspect of the present invention, the radiator panel is firmly connected to the structural panel in order to withstand a severe vibration environment at the time of launch, and when the radiator panel becomes cold in space, Even when the radiator panel shrinks, no compressive load is applied to the structural panel, so there is no need to reinforce the structure panel to prevent damage to the structural panel as in the prior art, thereby improving productivity and reducing costs. In addition, it is possible to provide a heat insulating structure capable of improving the directional performance of an optical sensor, an antenna, and the like mounted on the structural panel.

[Brief description of the drawings]

FIG. 1 is a sectional view showing one embodiment of a heat insulating structure according to the present invention.

FIG. 2 is a top view (A arrow view) of the heat insulating mechanism of FIG. 1;

FIG. 3 is an operation explanatory view of the heat insulating mechanism of FIG. 1;

FIG. 4 is a cross-sectional view illustrating an example of a conventional heat insulating mechanism.

FIG. 5 is a top view (a view in the direction of arrow B) of the heat insulating mechanism of FIG. 4;

FIG. 6 is a cross-sectional view showing a damage example of the heat insulating mechanism of FIG.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Structure panel (base) 1a Female screw part 2 Radiator panel 2a Slot 3 Heat insulation collar (spacer) 4 Heat insulation washer 5 Bolt (bar-shaped fastening means) 5a Male screw part 10 Heat insulation structure

Claims (3)

[Claims] 1. A base, a radiator panel disposed outside the base and having a long hole, a spacer interposed between the base and the radiator panel, and the base near the spacer And a bar-shaped fastening means inserted into the elongated hole of the radiator panel and having a linear expansion coefficient different from a linear expansion coefficient of the spacer. 2. The heat insulating structure according to claim 1, wherein said rod-shaped fastening means is a bolt having a male screw portion screwed into a female screw portion formed on said base. 3. The heat insulating structure according to claim 1, wherein the base is a structural panel of a spacecraft, and a linear expansion coefficient of the rod-shaped fastening means is smaller than a linear expansion coefficient of the spacer. .