Expand Panel

Abstract

An object of the present invention is to provide an expandable panel that can expand the heat dissipation surface without using an expansion mechanism. [Solution] The unfoldable panel (100) has a first surface (41) and a second surface (42), and a main portion (40) on which a heat-generating device (50) is placed on the first surface (41). A first metal sheet material (20) is provided contiguous with and flush with the first surface (41). A folding material (10) is connected to the first metal sheet material (20) and expands as the temperature increases and contracts as the temperature decreases. A second metal sheet material (30) is connected to the folding material (10) and, when the folding material (10) is contracted, is disposed contiguous with and flush with the second surface (42).

Description

[Technical Field]

[0001] The present disclosure relates to deployable panels aboard satellites. [Background technology]

[0002] In the past, in artificial satellites, the heat generated by onboard equipment was conducted through the panel on which the equipment was mounted and then discharged into deep space through the panel's heat dissipation surface. Therefore, when the amount of heat to be dissipated increased due to the improved performance of onboard equipment, it was necessary to increase the heat dissipation area. Increasing the heat dissipation area meant increasing the size of the panel. On the other hand, because the satellite structure is mounted inside the launch vehicle, its envelope is limited. In other words, it has become difficult to expand the satellite structure's equipment mounting panel to accommodate high-heat-generating equipment. Therefore, a heat-dissipating surface that is folded inside the rocket fairing during launch and deployed in actual orbit, i.e., a deployable radiator panel, is becoming more useful.

[0003] Patent Document 1 discloses a deployable radiator panel that increases or decreases the heat dissipation area in orbit, thereby improving the efficiency of thermal control. [Prior art documents] [Patent documents]

[0004] [Patent Document 1] International Publication No. 2018-116490 Summary of the Invention [Problem to be solved by the invention]

[0005] The deployable radiator panel described in Patent Document 1 has the following problems because it has a deployment mechanism. - Mass increases due to the need for a deployment mechanism, deployment control equipment, and power source. -The deployment mechanism limits heat conduction, making it less effective as a heat dissipation surface. Additional power is required to control the deployment mechanism.

[0006] An object of the present disclosure is to provide an expandable panel that can expand the heat dissipation surface without using an expansion mechanism. [Means for solving the problem]

[0007] The deployment panel according to the present disclosure comprises: a main portion having a first surface portion and a second surface portion, with a heat-generating device being placed on the first surface portion; a first metal sheet material provided on the same surface as and continuous with the first surface portion; a bending member connected to the first metal sheet material, the bending member expanding as the temperature increases and contracting as the temperature decreases; The device further includes a second metal sheet material connected to the folding member and arranged continuously and flush with the second surface portion when the folding member is contracted. [Effects of the Invention]

[0008] The deployable panel according to the present disclosure has the advantage of being able to expand the heat dissipation surface without using a deployment mechanism. [Brief explanation of the drawings]

[0009] [Figure 1] 3A and 3B are diagrams illustrating a stored state of the deployment panel according to the first embodiment. [Figure 2] 3A and 3B are diagrams showing the deployed state of the deployment panel according to the first embodiment. [Figure 3] FIG. 2 is a diagram showing a connection configuration of a deployment panel to a satellite structure according to the first embodiment, in a stored state. [Figure 4] FIG. 2 is a diagram showing a connection configuration of a deployment panel to a satellite structure according to the first embodiment, in a deployed state. DETAILED DESCRIPTION OF THE INVENTION

[0010] The present embodiment will be described below with reference to the drawings. In each drawing, identical or corresponding parts are designated by the same reference numerals. In the description of the embodiment, the description of identical or corresponding parts will be omitted or simplified as appropriate. Furthermore, the size relationships of the components in the following drawings may differ from the actual ones. Furthermore, in the description of the embodiment, directions or positions such as up, down, left, right, front, rear, front and back may be indicated. These notations are provided for the convenience of explanation and do not limit the arrangement, direction or orientation of devices, instruments, parts, etc.

[0011] Embodiment 1 ***Configuration Description*** FIG. 1 is a diagram showing a deployed panel 100 according to this embodiment in a stored state. FIG. 2 is a diagram showing the deployed state of the deployment panel 100 according to this embodiment. FIG. 3 shows the connection structure of the deployable panel 100 according to this embodiment to the satellite structure 60, in a retracted state. FIG. 4 shows the connection configuration of the deployable panel 100 according to this embodiment to the satellite structure 60, in the deployed state.

[0012] <Configuration, arrangement, and connection relationship of each component of the deployment panel 100> As shown in FIGS. 1 and 2, the deployable panel 100 according to this embodiment includes a folding member 10, a first metal sheet member 20, a second metal sheet member 30, and a main portion 40.

[0013] The main portion 40 has a first surface portion 41 and a second surface portion 42. The main portion 40 is a honeycomb sandwich panel having a honeycomb core 43 between the first surface portion 41 and the second surface portion 42. A heat-generating device 50 is installed on the first surface portion 41.

[0014] The bending member 10 is connected to the first metal sheet material 20 and is made of an alloy that expands as the temperature increases and contracts as the temperature decreases. Specifically, the bending member 10 is made of a shape memory alloy. The bending member 10 is also called a shape memory alloy bending member.

[0015] The first metal sheet material 20 is a metal sheet material that is continuous with and is provided on approximately the same plane as the first surface portion 41. For example, the first metal sheet material 20 is an aluminum alloy sheet material. When the first metal sheet material 20 is attached to the satellite structure 60, it becomes the inner surface on the satellite structure 60 side.

[0016] The second metal sheet material 30 is a metal sheet material connected to the folding member 10. When the folding member 10 is contracted, the second metal sheet material 30 is arranged continuously with and substantially flush with the second surface portion 42 as shown in FIG. 1. On the other hand, when the folding member 10 is extended, the second metal sheet material 30 is arranged outside the satellite structure 60, away from the second surface portion 42 as shown in FIG. 2. For example, the second metal sheet material 30 is an aluminum alloy sheet material. The second metal sheet material 30 is attached to the satellite structure 60, and forms the outer surface of the satellite structure 60 when the folding member 10 is contracted.

[0017] The deployable panel 100 is connected to the satellite structure 60 of the satellite, as shown in FIGS. A structure surface portion 61 that constitutes the surface of the satellite structure 60 includes, for example, a honeycomb sandwich panel. The main section 40 is connected to a structure surface section 61 of a satellite structure 60, the structure surface section 61 comprising a honeycomb sandwich panel.

[0018] 3, the unfolded panel 100 is stored in the body structure surface portion 61 with the folding members 10 contracted. The second metal sheet material 30 is arranged on approximately the same plane as the body structure surface portion 61 with the folding members 10 contracted.

[0019] As shown in Fig. 4, the unfoldable panel 100 has the second metal sheet material 30 disposed outside from the body structure surface portion 61 with the folding members 10 in an extended state. The second metal sheet material 30 is disposed outside from the body structure surface portion 61 with the folding members 10 in an extended state. At this time, the folding members 10 are extended, and the heat dissipation area is enlarged.

[0020] <Operation and Function of Deployment Panel 100> In the deployable panel 100 according to this embodiment, a honeycomb sandwich panel with high out-of-plane rigidity is used in the main section 40, which is the equipment mounting section requiring high out-of-plane rigidity. In addition, in areas where it is sufficient to ensure a minimum level of rigidity that does not affect the launch of the rocket, a shape memory alloy folded member 10, and an aluminum alloy first metal sheet member 20 and a second metal sheet member 30 are used.

[0021] As shown in FIGS. 1 and 2, the heat generating device 50 is installed in the main portion 40. 3, the deployable panel 100 is used as part of the structure surface portion 61, which is a constituent panel of the satellite structure 60. The main portion 40, which is a honeycomb sandwich panel of the deployable panel 100, and the honeycomb sandwich panel in the satellite structure 60 are connected. In most cases, the satellite structure 60 is assembled by combining honeycomb sandwich panels in a box shape. However, the satellite structure 60 may be configured with shapes other than honeycomb sandwich panels. There are various methods for joining the satellite structure 60 and the honeycomb sandwich panels. For example, one method is to fasten the surface portion 61 of the structure and the second metal sheet material 30 shown in Figure 3 by passing bolts or other structures through the honeycomb sandwich panels in the thickness direction.

[0022] 1 and 2, in the deployment panel 100, the folding members 10 expand or contract in response to temperature changes. The expansion or contraction of the folding members 10 allows the deployment panel 100 to reversibly change between a stored state and an deployed state.

[0023] During rocket launch, the deployable panel 100 is in a stowed state. Therefore, the deployable panel 100 does not pose a problem of constraints of the rocket envelope during rocket launch. Also, as shown in Figure 3, the main section 40 of the deployable panel 100 is connected to the honeycomb sandwich panel in the satellite structure 60. This supports the heat-generating equipment 50 during rocket launch, and ensures the strength and rigidity of the area where the heat-generating equipment 50 is installed.

[0024] 2 and 4, in outer space after launch by a rocket, the temperature rises due to heat generated by the heat-generating device 50, causing the folding material 10 to expand. The expansion of the folding material 10 causes the unfoldable panel 100 to automatically expand. In this way, the temperature rise of the heat-generating device 50 causes the folding material 10 to expand, and the heat dissipation surface of the unfoldable panel 100 automatically expands.

[0025] Conversely, as shown in Figures 1 and 3, when the heat-generating device 50 is not generating heat, heat dissipation is not necessary. At this time, the temperature of the folding material 10 is low, so the folding material 10 contracts. As the folding material 10 contracts, the unfoldable panel 100 automatically retracts. In this way, when the temperature of the heat-generating device 50 is low, the folding material 10 contracts, and the heat-dissipating surface of the unfoldable panel 100 is automatically retracted.

[0026] The surface area of ​​the deployable panel 100 exposed to the deep space environment is larger in the deployed state than in the stowed state. This allows for efficient heat dissipation. On the other hand, when the heat-generating device 50 generates only a small amount of heat, the deployable panel 100 is stowed, allowing the heat to be retained within the satellite structure 60.

[0027] ***Explanation of the effect of this embodiment*** The deployable panel 100 according to this embodiment has a sandwich panel structure with a core made of a shape memory alloy folded material and a skin made of an aluminum alloy sheet material. The deployable panel 100 according to this embodiment is also called an deployable aluminum panel. The deployable panel 100 according to this embodiment does not require a deployment mechanism, deployment control device, or power source, which has the advantage that the mass of the deployable panel 100 according to this embodiment can be kept small compared to a deployable radiator panel that uses a deployment mechanism. Furthermore, the deployable panel 100 according to this embodiment does not require control or drive power for deployment. Therefore, the deployable panel 100 according to this embodiment has an advantage in terms of power consumption compared to deployable radiator panels that use a deployment mechanism. Furthermore, in the deployable panel 100 according to this embodiment, the heat conduction is not restricted by the deployment mechanism, and therefore there is an advantage that the heat dissipation efficiency is higher than that of a deployable radiator panel.

[0028] Of the above-described first embodiment, multiple parts may be combined and implemented. Alternatively, only one part of the first embodiment may be implemented. In addition, the first embodiment may be implemented in any combination, either as a whole or in part. That is, in the first embodiment, a plurality of parts can be freely combined, or any of the components in the first embodiment can be modified, or any of the components in the first embodiment can be omitted.

[0029] It should be noted that the above-described first embodiment is essentially a preferred example and is not intended to limit the scope of the present disclosure, the scope of application of the present disclosure, and the scope of use of the present disclosure. Various modifications can be made to the first embodiment as necessary.

[0030] Various aspects of the present disclosure are summarized below as appendices.

[0031] (Appendix 1) a main portion having a first surface portion and a second surface portion, with a heat-generating device being placed on the first surface portion; a first metal sheet material provided on the same surface as and continuous with the first surface portion; a bending member connected to the first metal sheet material, the bending member expanding as the temperature increases and contracting as the temperature decreases; a second metal sheet material connected to the folding member and arranged continuously and flush with the second surface portion when the folding member is contracted; An expansion panel comprising: (Appendix 2) 2. The unfoldable panel according to claim 1, wherein the folding member is made of a shape memory alloy. (Appendix 3) The main portion is 3. The deployable panel according to claim 1 or 2, which is a honeycomb sandwich panel having a honeycomb core between the first surface portion and the second surface portion. (Appendix 4) the deployable panel is connected to a satellite structure of a satellite; 4. The deployable panel according to any one of claims 1 to 3, wherein the main portion is connected to a structure surface portion of the satellite structure, the structure surface portion including a honeycomb sandwich panel. (Appendix 5) 5. The deployable panel according to claim 4, wherein the deployable panel is stored in the body structure surface portion in a state in which the folding member is contracted. (Appendix 6) 6. The deployable panel according to claim 4 or 5, wherein the second metal sheet material is disposed outside the surface portion of the body structure when the bent member is extended. (Appendix 7) 7. The unfoldable panel according to any one of claims 4 to 6, wherein the second metal sheet material is arranged on the same plane as the surface portion of the body structure when the folded material is contracted. (Appendix 8) 8. The deployable panel according to any one of claims 4 to 7, wherein the second metal sheet material is arranged outside the surface portion of the body structure with the bent material in an extended state. [Explanation of symbols]

[0032] 10 Bending member, 20 First metal sheet material, 30 Second metal sheet material, 40 Main portion, 41 First surface portion, 42 Second surface portion, 43 Honeycomb core, 50 Heat-generating equipment, 60 Satellite structure, 61 Structure surface portion, 100 Deployment panel.

Claims

1. a main portion having a first surface portion and a second surface portion, the main portion having a heat-generating device disposed on the first surface portion; a first metal sheet material provided on the same surface as and continuous with the first surface portion; a bending member connected to the first metal sheet material, the bending member expanding as the temperature increases and contracting as the temperature decreases; a second metal sheet material connected to the folding member and disposed continuously and flush with the second surface portion when the folding member is contracted; An expansion panel comprising:

2. 2. The deployable panel according to claim 1, wherein the folding member is made of a shape memory alloy.

3. The main portion is 3. The expandable panel according to claim 1 or 2, which is a honeycomb sandwich panel having a honeycomb core between the first surface portion and the second surface portion.

4. the deployable panel is connected to a satellite structure of a satellite; 3. The deployable panel according to claim 1, wherein the main portion is connected to a surface portion of the satellite structure, the surface portion being made of a honeycomb sandwich panel.

5. The deployable panel according to claim 4, wherein the deployable panel is stored in the surface portion of the body structure with the folding members contracted.

6. 5. The deployable panel according to claim 4, wherein the second metal sheet material is disposed outside the surface portion of the body structure when the folded member is in an extended state.

7. 5. The deployable panel according to claim 4, wherein the second metal sheet material is disposed flush with the surface portion of the structure when the folded material is contracted.

8. 5. The deployable panel according to claim 4, wherein the second metal sheet material is disposed outside the surface portion of the structure with the bent material in a stretched state.

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