JP6986259B2 - Multi-layer insulation material and insulation method using it - Google Patents

Description

The present invention relates to a multi-layer heat insulating material and a heat insulating method using the same.

Multi-layer insulation is used in many spacecraft for radiant insulation, and is a thermal control material that plays an important role in keeping the equipment mounted on the spacecraft at an appropriate temperature from the harsh temperature environment of outer space. It is one. The multi-layer heat insulating material has a structure in which a large number of low emissivity films are laminated, and has much better heat insulating performance than a bulk heat insulating material such as a foam material in a vacuum.

In conventional multi-layer insulation, a net-like spacer is inserted between the low emissivity films to prevent heat from flowing in due to solid heat conduction due to contact between the low emissivity films and degrading the insulation performance. Or, the low emissivity film itself is embossed (dimpled). However, it is not possible to prevent uncertain contact between the low emissivity films or between the low emissivity films and the net-shaped spacer. Therefore, depending on the mounting method on the spacecraft, the presence or absence of contact between the low emissivity film layers and the contact pressure will change significantly, and the heat insulation performance will change significantly accordingly. Is difficult.

In addition, the conventional multi-layer insulation material exhibits extremely high heat insulation performance in a vacuum environment and is effective in outer space, but it is low in a pressure environment with atmosphere during air flight from a range standby. Insulation performance is low due to heat transfer by gas molecules of air between the layers of the radiation rate film.

Further, the conventional multi-layer heat insulating material, which is a flexible structure in which a thin low emissivity film is laminated, is difficult to withstand the dynamic pressure during atmospheric flight, and cannot be directly applied to a spacecraft.

Therefore, the present inventors have improved the heat insulating performance and reduced the uncertainty of the performance by preventing the low emissivity films from coming into contact with each other, which is a problem of the conventional multilayer heat insulating material. We have proposed a "spacer" type multilayer heat insulating material (see Non-Patent Document 1 below). This is done by inserting multiple columnar spacers designed for high thermal resistance between adjacent low emissivity films and arranging the spacers so that the adjacent low emissivity films do not contact each other. , It eliminates heat conduction due to contact between low emissivity films.

However, the interlayer non-contact spacer type multi-layer heat insulating material has low heat insulating performance under a pressure environment like the conventional multi-layer heat insulating material. Therefore, in order to exhibit high heat insulation performance even in this pressure environment, a thin shell and a film that can seal the vacuum (vacuum sealing film) are provided on the outside of the outermost layer of the laminated low emissivity film. The present inventors have proposed a multi-layer heat insulating material (“load-bearing interlayer non-contact spacer” type multi-layer heat insulating material) that evacuates the inside of the multi-layer heat insulating material (see Non-Patent Document 2 below). The inside of the multi-layer insulation is evacuated so that the multi-layer insulation is compressed by the load of atmospheric pressure, but the outer shell and the adjacent low emissivity films are arranged so as not to contact each other. By maintaining the space between the low emissivity films with the spacer, it is possible to realize a lightweight, vacuum-held multi-layer heat insulating material, and it is possible to demonstrate high heat insulating performance even in a pressurized environment. It became.

Ken Miyakita et al., Development of Interlayer Non-contact Spacer MLI, Proceedings of the 56th Space Science and Technology Association Lecture, November 2012 Ken Miyakita et al., Examination of ultra-low temperature new style insulation method for inter-orbit transport aircraft, Proceedings of the 60th Space Science and Technology Association Lecture, September 2016

However, in the load-bearing interlayer non-contact spacer type multilayer heat insulating material, the multilayer heat insulating material is compressed by the load of atmospheric pressure by being evacuated, so that the spacer needs to be able to withstand the compressive force. There is. Therefore, it is necessary to increase the area responsible for the compressive force of the spacer and to make the structure of the spacer strong, thereby reducing the thermal resistance of the spacer and improving the heat insulating performance of the conventional interlayer non-contact spacer type multilayer. Lower than insulation.

Therefore, one of the objects of the present invention is to provide a multi-layer heat insulating material that exhibits high heat insulating performance in both environments with different external pressures, such as a pressure environment and a vacuum environment.

One aspect of the present invention is a multi-layer heat insulating material attached to a structure, which is arranged so as to cover the laminated heat insulating films and the laminated heat insulating films, and is between the structures. Adjacent to a plurality of thermal resistance spacers inserted between the adjacent insulating film and supporting the adjacent insulating film so that a closed space is formed in the surrounding member to be bonded to the structure. A plurality of load-bearing spacers inserted between the heat insulating films and supporting the adjacent heat insulating films are provided, and the thermal resistance spacers are elastic against a force applied in the stacking direction of the plurality of heat insulating films. However, the load-bearing spacer has a first attachment portion attached to one of the adjacent heat insulating films, a second attachment portion attached to the other of the adjacent heat insulating films, and the first attachment portion and the above. The second mounting portion is provided with a connecting portion for connecting the first mounting portion and the second mounting portion so as to be separated from each other, and the connecting portion receives external pressure applied to the surrounding member and pressure inside the sealed space. When the compressive force of the difference reaches a predetermined value, the first mounting portion and the second mounting portion abutted by the compressive force support the adjacent heat insulating film. The plurality of thermal resistance spacers and the plurality of load-bearing spacers are arranged so as to be spaced apart from each other, and the plurality of heat insulating films are arranged so as not to come into contact with each other to provide a multilayer heat insulating material. Is.

The external pressure may be atmospheric pressure, and the pressure inside the enclosed space may be a evacuated vacuum pressure.

The first mounting portion and the second mounting portion may be configured to be fitable with the heat insulating film interposed therebetween.

It can be assumed that the outer layer shell is arranged on the outside of the plurality of laminated heat insulating films.

The structure can be a spacecraft.

One aspect of the present invention is a heat insulating method using a multi-layer heat insulating material, which provides a method of evacuating the closed space of the multi-layer heat insulating material before launching the spacecraft. ..

According to the present invention having the above configuration, it is possible to provide a multilayer heat insulating material that exhibits high heat insulating performance in both environments having different external pressures, such as a pressure environment and a vacuum environment.

(A) is a schematic cross-sectional view of the multilayer heat insulating material according to one embodiment of the present invention before evacuation. (B) is a schematic cross-sectional view of the multilayer heat insulating material according to one embodiment of the present invention after evacuation. (C) is a schematic cross-sectional view in outer space of the multilayer heat insulating material according to one embodiment of the present invention. (A) is a top perspective view of a load-bearing spacer used in the multilayer heat insulating material according to one embodiment of the present invention. (B) is a bottom perspective view of a load-bearing spacer used in the multilayer heat insulating material according to one embodiment of the present invention. It is a VI-VI sectional view of the load-bearing spacer used for the multilayer heat insulating material which concerns on one Embodiment of this invention. (A) is a top perspective view of a high heat resistance spacer used in the multilayer heat insulating material according to one embodiment of the present invention. (B) is a bottom perspective view of a high heat resistance spacer used in the multilayer heat insulating material according to one embodiment of the present invention. It is a side view of the high heat resistance spacer used for the multilayer heat insulating material which concerns on one Embodiment of this invention. It is a top view of the 3rd attachment part of the high heat resistance spacer used for the multilayer heat insulating material which concerns on one Embodiment of this invention. It is a top view of the connection part of the high heat resistance spacer used for the multilayer heat insulating material which concerns on one Embodiment of this invention. It is a top view of the 4th attachment part of the high heat resistance spacer used for the multilayer heat insulating material which concerns on one Embodiment of this invention.

Hereinafter, embodiments of the present invention will be described with reference to the drawings. In the present embodiment, a case where the multi-layer heat insulating material is attached to the spacecraft and the inside of the multi-layer heat insulating material is evacuated before the launch of the spacecraft will be described as an example.

FIG. 1A is a schematic cross-sectional view of the multilayer heat insulating material according to one embodiment of the present invention before evacuation. FIG. 1B is a schematic cross-sectional view of the multilayer heat insulating material according to one embodiment of the present invention after evacuation. FIG. 1 (c) is a schematic cross-sectional view of the multilayer heat insulating material according to one embodiment of the present invention in outer space. FIG. 2A is a top perspective view of a load-bearing spacer used in the multilayer heat insulating material according to one embodiment of the present invention. FIG. 2B is a bottom perspective view of a load-bearing spacer used in the multilayer heat insulating material according to one embodiment of the present invention. FIG. 3 is a VI-VI cross-sectional view of a load-bearing spacer used in the multilayer heat insulating material according to one embodiment of the present invention. FIG. 4A is a top perspective view of the high heat resistance spacer used in the multilayer heat insulating material according to one embodiment of the present invention. FIG. 4B is a bottom perspective view of the high heat resistance spacer used in the multilayer heat insulating material according to one embodiment of the present invention. FIG. 5 is a side view of a high heat resistance spacer used in the multilayer heat insulating material according to one embodiment of the present invention. FIG. 6 is a top view of a third mounting portion of the high heat resistance spacer used in the multilayer heat insulating material according to one embodiment of the present invention. FIG. 7 is a top view of a connection portion of a high heat resistance spacer used in the multilayer heat insulating material according to one embodiment of the present invention. FIG. 8 is a top view of a fourth mounting portion of the high heat resistance spacer used in the multilayer heat insulating material according to one embodiment of the present invention.

As shown in FIGS. 1A to 1C, the multilayer heat insulating material 1 according to the present embodiment includes a plurality of laminated heat insulating films 2, an outer layer shell 3, a surrounding member 4, and a plurality of load-bearing spacers. 5. A plurality of high heat resistance spacers 6 are provided.

The plurality of laminated heat insulating films 2 are low emissivity films, which are obtained by vapor-filming a metal such as aluminum on a resin film such as polyimide. The composition of the heat insulating film 2 is not limited to this, and may be the composition of any other suitable material. In the plurality of laminated heat insulating films 2, the innermost heat insulating film 2 is attached to the structure 10 by a hook-and-loop fastener 7. The attachment configuration of the innermost heat insulating film 2 to the structure 10 is not limited to this, and for example, the first attachment portion 51 of the load-bearing spacer 5 and the third attachment of the high heat resistance spacer 6 described later are not limited to this. A structure similar to that of the portion 61 may be provided in the structure 10 to have any other suitable configuration such as a configuration in which the structure 10 is attached by fitting. In this embodiment, the structure 10 is a spacecraft. A plurality of high heat resistance spacers 6 and a plurality of load-bearing spacers 5, which will be described later, are inserted between the adjacent heat insulating films 2. The plurality of high heat resistance spacers 6 and the plurality of load-bearing spacers 5 are attached to the adjacent heat insulating films 2 and support the adjacent heat insulating films 2.

An outer layer shell 3 is arranged on the outside of the outermost heat insulating film 2 of the plurality of laminated heat insulating films 2. A plurality of high heat resistance spacers 6 and a plurality of load-bearing spacers 5 are inserted between the outer layer shell 3 and the outermost heat insulating film 2 as in the case of the adjacent heat insulating films 2. The plurality of high heat resistance spacers 6 and the plurality of load-bearing spacers 5 have a terminal member having the same structure as the first mounting portion 51 of the load-bearing spacer 5 and the third mounting portion 61 of the high heat resistance spacer 6, which will be described later. The outermost layer heat insulating film 2 is sandwiched and fitted to the outer layer shell 3 and the outermost layer heat insulating film 2, and the outer layer shell 3 is supported by a plurality of high heat resistance spacers 6 and a plurality of load-bearing spacers 5. To. The configuration for attaching the outer layer shell 3 to the heat insulating film 2 is not limited to this, and may be any other suitable configuration such as a configuration for attaching with a hook-and-loop fastener or an adhesive.

The outer layer shell 3 is a thin plate made of thermosetting CFRP. The outer layer shell 3 is not limited to a thin plate made of thermosetting CFRP, and can be made of any other suitable material. For example, it can be made of thermoplastic CFRP or an aluminum alloy. As will be described later, when the closed space 8 is evacuated, atmospheric pressure is applied from the outside, and the pressure from the outside is basically supported by the high heat resistance spacer 6 and the load-bearing spacer 5. At this time, the outer layer shell 3 prevents the portion of the heat insulating film 2 that is not supported by the high heat resistance spacer 6 and the load-bearing spacer 5 from being deformed and the plurality of heat insulating films 2 from coming into contact with each other. The outer layer shell 3 can be omitted by increasing the arrangement interval of the high heat resistance spacer 6 and the load bearing spacer 5.

The surrounding member 4 is arranged so as to cover the plurality of laminated heat insulating films 2 and the outer layer shell 3, and is coupled to the structure 10 so that a closed space 8 is formed between the surrounding member 4 and the structure 10. The surrounding member 4 is made of a laminated (heat-fused) film having an aluminum layer. An outer layer shell 3 exists directly under the surrounding member 4, and the compressive force when the closed space 8 is evacuated under a pressure environment is supported by the outer layer shell 3, the load-bearing spacer 5, and the high heat resistance spacer 6. No large force acts in the in-plane direction on the surrounding member 4. Further, since the time for holding the closed space 8 in the vacuum is short as the time during the atmospheric navigation immediately after the launch, it is desirable that the surrounding member 4 is made of a material as light as possible. However, if the enclosing member 4 is composed of only a resin layer, the gas permeability is high, so that it is preferable to provide a metal layer, but it is not necessary to provide the metal layer when the time for holding in a vacuum is shorter. Further, when it is attached to a structure 10 having a large area, it is convenient to have a structure in which it can be easily joined. Therefore, in the present embodiment, the surrounding member 4 is a laminated (heat-fused) film having an aluminum layer. The surrounding member 4 is not limited to this, and any other suitable film can be used. Further, as the enclosing member 4, instead of the film, any other suitable enclosing member such as a highly elastic rubber material may be used. The surrounding members 4 are fused by a double-sided heat-sealing film around the closed space 8 and are sealed to each other. The configuration for connecting the enclosing member and the structure is not limited to this, for example, a configuration in which the enclosing member is sandwiched by an O-ring or the like provided on the structure and sealed to each other, and an adhesive material for the enclosing member to the structure. It can be any other suitable configuration, such as a configuration that is sealed to each other by adhering with.

The load-bearing spacer 5 includes a first mounting portion 51, a connecting portion 52, and a second mounting portion 53. The load-bearing spacer 5 is manufactured by injection molding using polyetheretherketone (PEEK), which has high heat resistance, as a material. The structure of the load-bearing spacer 5 is not limited to this, and may be the structure of any other suitable material.

The first mounting portion 51 has a disk-shaped shape. The first mounting portion 51 has a partially chipped annular (C-shaped) first element 511 having one end and the other end facing in the circumferential direction, and one end and the other end of the first element 511. A pair of linear second elements extending radially across the center of the annulus and connected to a portion of the first element 511 radially opposed to one end and the other end of the first element 511. It is composed of an element 512 and a base 513 formed between a pair of second elements 512 so as to project from a portion of the first element 511 radially opposed to one end and the other end of the first element 511. To. At the central portion in the longitudinal direction of the pair of second elements 512, a receiving portion 512a that is curved outward in an arc shape is formed. The width of the receiving portion 512a is made larger than the width of the other portion of the second element 512 so that the outer circumference of the receiving portion 512a is larger than the outer circumference of the main portion 531 of the second mounting portion 53 described later. Has been done. The receiving portion 512a constitutes a locking portion that allows the insertion portion 532, which will be described later, to be fitted.

The second mounting portion 53 includes a substantially columnar main portion 531 and an insertion portion 532 provided on a surface orthogonal to the axial direction of the main portion 531 opposite to the first mounting portion 51. The insertion portion 532 has a chamfered substantially cylindrical head 532a and a cylindrical small diameter having a diameter smaller than the diameter of the bottom surface of the head 532a, with one end connected to the bottom surface of the head 532a. It is composed of a part 532b. Then, the stepped portion between the bottom surface of the head portion 532a and the small diameter portion 532b constitutes the engaging portion 532c.

With such a structure, one load-bearing spacer 5 can be fitted and connected to another load-bearing spacer 5. That is, when the insertion portion 532 of one load-bearing spacer 5 is inserted into the receiving portion 512a of the other load-bearing spacer 5, the engaging portion 532c of the insertion portion 532 is engaged with the receiving portion 512a and locked. The load-bearing spacers 5 can be fixed to each other.

Further, a substantially columnar recess 531a that can accommodate the insertion portion 532 is formed on the bottom surface of the main portion 531. As a result, when the connection portion 52 is broken as described later, the bottom surface of the main portion 531 is formed. It comes into contact with the receiving portion 512a of the first mounting portion 51, and can support the heat insulating film 2 and the compressive force.

The connecting portion 52 is composed of a support column 521 having a substantially rectangular parallelepiped shape and a support arm 522 integrally connected to the support column 521. The support column 521 is integrally connected to the base 513 of the first mounting portion 51. Further, the support arm 522 supports the second attachment portion 53 so that the second attachment portion 53 is separated from the first attachment portion 51. A notch 522a is formed on the support pillar side of the support arm 522, and when a constant force is applied to the second attachment portion 53, the connection portion 52 breaks and the support pillar 521 and the support arm 522 are separated from each other. It is configured as follows. In the present embodiment, as will be described later, the connecting portion 52 is configured to break when a compressive force of atmospheric pressure is applied to the surrounding member 4. The configuration of the connecting portion is not limited to this, and when the compressive force applied to the surrounding member changes from a small compressive force to a compressive force larger than the small compressive force by a predetermined magnitude, the connecting portion is not limited to this. Can be any other suitable configuration that separates.

The high heat resistance spacer 6 has a cylindrical shape and has a three-stage structure. The high thermal resistance spacer 6 includes a disk-shaped third mounting portion 61, a thermal resistance enhancing portion 62, and a fourth mounting portion 63 of the same size, which are arranged in parallel so as to be separated from each other. The high heat resistance spacer 6 is manufactured by injection molding using polyetheretherketone (PEEK), which has high heat resistance, as a material. The configuration of the high heat resistance spacer 6 is not limited to this, and may be the configuration of any other suitable material.

The third mounting portion 61 is arranged in parallel with the first element 611 of the annulus with the center of the annulus in between, and both ends of each are a linear pair connected integrally with the first element 611. The second element 612 of the above is provided. At the central portion in the longitudinal direction of the second element 612, a receiving portion 612a that curves in an arc shape on the outside is formed, and the receiving portion 612a constitutes a locking portion that allows the insertion portion 634 described later to be fitted.

The fourth attachment portion 63 is arranged at the same position as the position of the third element 631 which is an annular shape having the same shape as the first element 611 and the second element 612 with respect to the first element 611, and the third element 63. It comprises a pair of linear fourth elements 632 that are integrally connected to the element 631. Further, the fourth mounting portion 63 includes a disc-shaped light-shielding portion 633 concentric with the third element 631. At the center of the light-shielding portion 633, an insertion portion 634 that can be fitted with the receiving portion 612a of the third mounting portion 61 is provided. The light-shielding portion 633 is for preventing light rays from leaking from holes provided in the heat insulating film 2 described later.

The insertion portion 634 includes a head portion 634a composed of a main body portion 634a-1 formed in an inverted taper shape whose diameter expands in the axial direction and a columnar tip portion 634a-2 provided at the end portion of the main body portion. One end thereof is connected to the end portion of the main body portion 634a-1, and the head portion 634a is composed of a columnar small diameter portion 634b having a diameter smaller than the maximum diameter of the head portion 634a. Then, the bottom surface of the main body portion 634a-1 of the head 634a and the stepped portion of the small diameter portion 634b form the engaging portion 634c.

With such a structure, one high heat resistance spacer 6 can be fitted and connected to another high heat resistance spacer 6. That is, when the insertion portion 634 of one high heat resistance spacer 6 is inserted into the receiving portion 612a of the other high heat resistance spacer 6, the insertion is guided by the shape of the head 634a of the insertion portion 634 as described above, and the insertion portion 634 is inserted. The engaging portion 634c of the above is engaged with the receiving portion 612a and locked, and both high heat resistance spacers 6 can be fixed to each other.

The thermal resistance enhancing portion 62 has a pair of left and right arcuate arcs, a pair of fifth elements 621 separated in the radial direction and separated from each other, and a pair of fifth elements 621 with the center interposed therebetween. It is composed of a pair of extending linear sixth elements 622 and a linear seventh element 623 connecting the opposite ends of the sixth element 622. An insertion portion 622a that curves in an arc shape on the outside is formed in the central portion of the sixth element 622 in the longitudinal direction, and the tip portion of the head portion 634a of the insertion portion 634 when the insertion portion 634 is fitted with the receiving portion 612a. 634a-2 can be inserted.

The third mounting portion 61, the thermal resistance enhancing portion 62, and the fourth mounting portion 63 are arranged coaxially, and are a pair of linear elements 612 and a fourth element when viewed from the axial direction. 632 and the sixth element 622 are arranged so as to overlap each other. Then, the other end of one of the pair of fifth elements 621 is integrally connected to the third attachment portion 61 via the linear eighth element 64 extending in the axial direction, and the pair of fifth elements 621 is integrally connected to the third attachment portion 61. The other end of the element is integrally connected to the fourth attachment portion 63 via a linear ninth member 65 extending axially.

As described above, since the high heat resistance spacer 6 has a coil-like structure, it has elasticity (restoring force). Further, since the heat transfer path having a small cross-sectional area is formed long in the thermal resistance enhancing portion 62, the thermal resistance of the high thermal resistance spacer 6 increases.

The heat insulating film 2 is provided with holes according to the distance between the high heat resistance spacer 6 and the load bearing spacer 5. Insert the insertion portion 634 of the fourth mounting portion 63 of the high heat resistance spacer 6 and the insertion portion 532 of the second mounting portion 53 of the load-bearing spacer 5 into this hole, and sandwich the heat insulating film 2 to provide another high heat resistance. By fitting the spacer 6 into the receiving portion 612a of the third mounting portion 61 and the receiving portion 512a of the first mounting portion 51 of the load-bearing spacer 5, the high heat resistance spacer 6, the heat insulating film 2, and the load-bearing spacer 5 are formed. The heat insulating films 2 are fixed to each other, and the heat insulating films 2 are supported by the high heat resistance spacer 6 and the load bearing spacer 5.

In the plurality of high heat resistance spacers 6 and the plurality of load-bearing spacers 5, the plurality of laminated heat insulating films 2 are evacuated in consideration of the mutual spacing (which may be a constant spacing or a fluctuating spacing). After that, that is, even when a compressive force of atmospheric pressure is applied to the surrounding member 4, they are arranged so as not to come into contact with each other. With such a configuration, even after evacuation, the films are arranged at intervals so as not to come into contact with each other, so that contact between the heat insulating films that causes deterioration of the heat insulating performance is prevented. Further, the thickness of the outer layer shell 3 can be reduced by dispersing and taking charge of the compressive force received by the outer layer shell 3 by the plurality of high heat resistance spacers 6 and the plurality of load-bearing spacers. Therefore, according to the present embodiment, it is possible to realize a lightweight, vacuum-held multi-layer heat insulating material that can exhibit high heat insulating performance even in a pressurized environment.

Subsequently, with reference to FIGS. 1 (b) and 1 (c), the operation of the multilayer heat insulating material of the present embodiment and the heat insulating method using the multilayer heat insulating material of the present embodiment will be described.

(1) Vacuuming On the ground, a vacuum pump or the like (not shown) is used to evacuate the closed space 8 of the multilayer heat insulating material 1. With reference to FIG. 1 (b), when the evacuation is completed, the external pressure applied to the enclosing member 4 is atmospheric pressure, and the pressure inside the closed space 8 is the vacuum pressure. The compressive force of atmospheric pressure, which is the difference between the external pressure applied to the air pressure and the pressure inside the closed space 8, is applied. This compressive force is applied to the high heat resistance spacer 6 and the load-bearing spacer 5, but since the connection portion 52 of the load-bearing spacer 5 is configured to be broken by this compressive force, it is separated by the connection portion 52. The first mounting portion 51 and the second mounting portion 53 come into contact with each other due to this compressive force. As a result, the load-bearing spacer 5 can still support the heat insulating film 2 and the compressive force.

As described above, the plurality of high heat resistance spacers 6 and the plurality of load-bearing spacers 5 are provided because the plurality of heat insulating films 2 are arranged at intervals so as not to come into contact with each other even after evacuation. It is possible to realize a lightweight, vacuum-held multi-layer heat insulating material that can exhibit high heat insulating performance even in a pressure environment.

(2) After the launch When the spacecraft to which the multi-layer heat insulating material 1 is attached is launched, the external pressure applied to the surrounding member 4 gradually decreases, and becomes a vacuum pressure in outer space. With reference to FIG. 1 (c), the encircling member 4 expands because the evacuation pressure in outer space is smaller than the evacuation pressure due to evacuation. Since the high heat resistance spacer 6 has elasticity (restoring force) in the stacking direction, the distance between the heat insulating films 2 is widened, and the first mounting portion 51 and the second mounting portion 53 of the load-bearing spacer 5 are fitted by fitting. Since it is fixed to the heat insulating film 2, the first mounting portion 51 and the second mounting portion 53 of the load-bearing spacer 5 whose connection by the connecting portion 52 is disconnected are separated again. As a result, the heat transfer path is cut in the load-bearing spacer 5, so that the heat transfer due to conduction through the load-bearing spacer 5 can be reduced to zero, and even higher heat transfer performance than after evacuation can be realized. Can be done.

According to this embodiment, it is possible to realize high heat insulating performance that cannot be realized by the conventional interlayer non-contact type spacer type multilayer heat insulating material under a pressure environment. Further, in a vacuum environment, it is possible to realize higher heat transfer performance than the conventional interlayer non-contact type multilayer heat insulating material and load-bearing interlayer non-contact type multilayer heat insulating material. That is, according to the present embodiment, high heat insulation performance can be realized in both a pressure environment and a vacuum environment.

In the above embodiment, the case where the multi-layer insulation material is attached to the spacecraft and the inside of the multi-layer insulation material is evacuated before the launch of the spacecraft has been described as an example, but the structure to which the multi-layer insulation material is attached is , And the multi-layer insulation shall be used in any suitable environment with different pressures, i.e. different degrees of vacuum, not under pressure and vacuum. be able to.

Although the present invention has been described above with respect to some embodiments for illustration purposes, the present invention is not limited thereto, and the embodiments and details are described without departing from the scope and spirit of the present invention. It will be apparent to those skilled in the art that various modifications and modifications can be made.

1 Multi-layer insulation 2 Insulation film 3 Outer layer shell 4 Surrounding member 5 Load-bearing spacer 51 First mounting part 511 First element 512 Second element 512a Receiving part 513 Base 52 Connection part 521 Support pillar 522 Support arm 522a Notch part 53 Second mounting part 531 Main part 531a Recessed part 532 Inserting part 532a Head 532b Small diameter part 532c Engaging part 6 High thermal resistance spacer 61 Third mounting part 611 First element 612 Second element 612a Receiving part 62 Heat Resistance enhancement part 621 5th element 622 6th element 622a Insertion part 623 7th element 63 4th mounting part 631 3rd element 632 4th element 633 Shading part 634 Inserting part 634a Head 634a-1 Main body Part 634a-2 Tip part 634b Small diameter part 634c Engagement part 64 Eighth element 65 Ninth element 7 Face fastener 8 Sealed space 10 Structure

Claims (6)

A multi-layer insulation that can be attached to structures
With multiple laminated heat insulating films
A surrounding member that is arranged so as to cover the plurality of laminated heat insulating films and is bonded to the structure so as to form a closed space with the structure.
A plurality of thermal resistance spacers inserted between the adjacent insulating films and supporting the adjacent insulating films,
With a plurality of load-bearing spacers inserted between the adjacent insulating films and supporting the adjacent insulating films,
Equipped with
The thermal resistance spacer has elasticity against a force applied in the stacking direction of the plurality of heat insulating films.
The load-bearing spacer has a first attachment portion attached to one of the adjacent heat insulating films, a second attachment portion attached to the other of the adjacent heat insulating films, the first attachment portion, and the second attachment portion. A connection portion for connecting the first mounting portion and the second mounting portion so as to be separated from each other is provided.
The connecting portion is separated when the compressive force of the difference between the external pressure applied to the surrounding member and the pressure inside the enclosed space reaches a predetermined value, and the first mounting portion abutted by the compressive force. And the second mounting portion are configured to support the adjacent insulating film.
The plurality of thermal resistance spacers and the plurality of load-bearing spacers are arranged apart from each other, and the plurality of heat insulating films are arranged so as not to come into contact with each other.
Multi-layer insulation. The multilayer heat insulating material according to claim 1, wherein the external pressure is atmospheric pressure, and the pressure inside the closed space is a evacuated vacuum pressure. The multilayer heat insulating material according to claim 1 or 2, wherein the first mounting portion and the second mounting portion are configured to be fitable with the heat insulating film interposed therebetween. The multilayer heat insulating material according to any one of claims 1 to 3, wherein an outer layer shell is arranged on the outside of the plurality of laminated heat insulating films. The multi-layer heat insulating material according to any one of claims 1 to 4, wherein the structure is a spacecraft. It is a heat insulating method using multi-layered heat insulating material.
A method of evacuating the enclosed space of the multilayer heat insulating material according to claim 5 before launching the spacecraft.

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