Radiation radiator and spacecraft

Abstract

The invention relates to the technical field of spaceflight, in particular to a radiation radiator and a spacecraft, and the radiation radiator comprises a heat conduction support, a pressing and unlocking unit and an expandable heat dissipation unit, one end of the unfoldable heat dissipation unit in the length direction of the unfoldable heat dissipation unit is a fixed end fixed to the heat conduction support, the other end of the unfoldable heat dissipation unit is a connecting end, and the unfoldable heat dissipation unit is used for being arranged to be in a spiral roll shape so that the connecting end can be one end of the inner side of the spiral roll shape; the pressing and unlocking unit is fixed to the heat conduction support, and the pressing and unlocking unit is detachably connected with the connecting end. The invention aims to provide a radiation radiator aiming at at least one technical problem related in the background technology.

Description

Technical Field

[0001] The present application relates to the field of aerospace technology, and in particular to a radiation heat sink and a spacecraft. Background Art

[0002] Due to the high vacuum environment of outer space, heat exchange between spacecraft and the external environment is carried out by radiation. Therefore, radiation radiator is the only heat dissipation method for spacecraft operating in a vacuum environment.

[0003] The radiation heat dissipation capacity of a spacecraft is positively correlated with the area of ​​the radiation heat dissipation surface. For spacecraft with low heat load, the heat dissipation demand can be met by relying solely on the spacecraft structure surface or part of the structure surface as the heat dissipation surface. However, with the expansion of spacecraft functions, the power surface density of spacecraft is getting higher and higher, resulting in a significant increase in the heat load, making the area of ​​the spacecraft body structure insufficient to support the timely dissipation of spacecraft heat. At this time, it is necessary to add independent radiators and conduct the heat generated by the internal or surface equipment of the spacecraft to the independent radiation heat sink through a series of heat conduction methods, so as to increase the effective area of ​​the spacecraft that can radiate heat to outer space.

[0004] In this context, radiant heat sinks have gradually developed into independent devices separated from the main structure of the spacecraft. In order to control the envelope size of the spacecraft in the launch state, radiant heat sinks independent of the spacecraft body are usually folded during the launch phase and unfolded during the orbital phase. The traditional form of deployable radiators is usually a rigid structure, which is pressed to the outer surface of the spacecraft structural plate by a clamping and unlocking mechanism in the folded state. This form of deployable radiant heat sink occupies a large amount of space on the outer surface of the spacecraft, and the outer surface of the spacecraft corresponding to the folded position can no longer be installed with other equipment, which is not conducive to the current high-functional density spacecraft to further develop in the direction of lightness and miniaturization. Summary of the invention

[0005] The purpose of the present application is to provide a radiation heat sink in view of at least one technical problem involved in the background technology.

[0006] In order to achieve the above objectives, this application adopts the following technical solutions:

[0007] One aspect of the present application provides a radiation heat sink, including a thermally conductive support, a compression unlocking unit and an expandable heat dissipation unit, wherein the thermally conductive support is used to be fixed to a spacecraft body, one end of the expandable heat dissipation unit in the length direction of the expandable heat dissipation unit is a fixed end fixed to the thermally conductive support, and the other end of the expandable heat dissipation unit is a connecting end, the expandable heat dissipation unit is used to be arranged in a spiral roll so that the connecting end is an end on the inner side of the spiral roll, the compression unlocking unit is fixed to the thermally conductive support, and the compression unlocking unit is detachably connected to the connecting end.

[0008] Optionally, the expandable heat dissipation unit includes a heat dissipation module and an elastic support member, the heat dissipation module and the elastic support member both extend from the fixed end to the connecting end, the elastic support member is fixedly connected to the heat dissipation module, and the elastic support member is used to expand the expandable heat dissipation unit from a spiral roll shape to a linear extension shape.

[0009] The beneficial effect of this technical solution is that when the expandable heat dissipation unit is in a spiral roll, the heat dissipation module and the elastic support member are both in a spiral roll, and the elastic support member stores elastic potential energy due to elastic deformation. When the control compression unlocking unit is separated from the expandable heat dissipation unit, the elastic support member recovers to a straight extension state under the action of its own elastic potential energy, and at the same time, drives the heat dissipation module to expand at the same time, thereby making the expandable heat dissipation unit expand into a straight extension state, and the elastic action of the elastic support member keeps the expandable heat dissipation unit in a straight extension state.

[0010] Optionally, the heat dissipation module comprises a heat control base layer and a radiation heat dissipation layer, and the radiation heat dissipation layer covers a side surface of the heat control base layer.

[0011] The beneficial effect of this technical solution is that the thermal control base layer, on the one hand, serves as the basic structure of the heat dissipation module, and on the other hand, can further diffuse the heat transferred from the spacecraft body to the heat-conducting support outward. Covering one side surface of the thermal control base layer with the radiation heat dissipation layer can improve the efficiency of heat radiation and dissipation.

[0012] Optionally, a surface of the radiation heat dissipation layer that is disposed away from the thermal control base layer forms an outer surface of the spirally rolled expandable heat dissipation unit.

[0013] The beneficial effect of this technical solution is that when the expandable heat dissipation unit is in an unfolded state, it can still efficiently radiate a certain amount of heat outward through the radiation heat dissipation layer, and has good heat dissipation capacity before the heat dissipation function of the radiation radiator is started.

[0014] Optionally, the heat dissipation module further includes a thermally conductive layer, and the thermally conductive layer covers the other side surface of the thermal control base layer.

[0015] The beneficial effect of this technical solution is that the thermally conductive layer can quickly conduct the heat at the heat source of the thermally conductive support to the thermal control base layer, and then quickly dissipate the heat from the radiation heat dissipation layer, further improving the heat dissipation efficiency.

[0016] Optionally, the elastic support member is located on a side of the thermal control base layer away from the radiation heat dissipation layer, and the elastic support member is fixed to the thermal control base layer.

[0017] The beneficial effect of this technical solution is that: in this way, the elastic support member is arranged relatively far away from the radiation heat dissipation layer, so that the elastic support member is not easy to hinder the heat dissipation of the radiation heat dissipation layer.

[0018] Optionally, the radiation heat sink provided in the present application includes a plurality of the elastic support members, each of which is arranged along the surface of the thermal control base layer.

[0019] The beneficial effect of this technical solution is that when the expandable heat dissipation unit is in a spiral roll, multiple elastic support members can store more elastic potential energy, and the expandable heat dissipation unit can be expanded more quickly when separated from the pressed unlocking unit, thereby shortening the heat dissipation time and improving the heat dissipation efficiency.

[0020] Optionally, the elastic supporting member is a tube.

[0021] The beneficial effect of this technical solution is that when the deployable heat dissipation unit is in a spiral roll, the tubular elastic support is flattened and compressed, occupying a smaller space, thereby making the spirally rolled deployable heat dissipation unit occupy a smaller space, which is conducive to the further development of high-functional density spacecraft in the direction of lightness and miniaturization.

[0022] Optionally, the thermally conductive support includes a support body and an auxiliary heat dissipation layer, and the auxiliary heat dissipation layer covers a surface of the support body.

[0023] The beneficial effect of this technical solution is that, regardless of whether the expandable heat dissipation unit is in the expanded state, the heat-conducting support can diffuse a certain amount of heat outward, so that the radiation radiator has good heat dissipation capacity before the heat dissipation function is fully started, thereby improving the heat dissipation efficiency.

[0024] Another aspect of the present application provides a spacecraft, including a spacecraft body and the radiation heat sink provided in the present application, wherein the heat conductive support is fixed to the spacecraft body.

[0025] The technical solution provided by this application can achieve at least one of the following beneficial effects:

[0026] The radiation radiator and spacecraft provided in the present application are in a collapsed spiral roll before the deployable heat dissipation unit is deployed, occupying a smaller area of ​​the outer surface of the spacecraft body, so that more space on the outer surface of the spacecraft body can be used to install other equipment, which is conducive to the further development of high-functional density spacecraft in the direction of lightness and miniaturization.

[0027] The additional technical features and advantages of the present application will be more clearly explained in the following description, or can be understood through the specific practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the technical solutions of the specific implementation methods of the present application, the following is a brief introduction to the drawings required for the description of the specific implementation methods. Obviously, the drawings described below are some implementation methods of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0029] FIG. 1( a ) is a schematic diagram of a structure in which a rigid deployable radiant heat sink is installed on a spacecraft body in the prior art, wherein the rigid deployable radiant heat sink is in a closed state;

[0030] FIG1( b ) is a schematic diagram of a structure in which a rigid deployable radiant heat sink is installed on a spacecraft body in the prior art, in which the rigid deployable radiant heat sink is in a deployed state;

[0031] Figure 2 A partial three-dimensional structural schematic diagram of an implementation method of a spacecraft provided in an embodiment of the present application;

[0032] Figure 3 A schematic diagram of the main structure of an implementation method of the radiation heat sink provided in an embodiment of the present application in an unfolded state;

[0033] Figure 4 A schematic diagram of a top view of a radiation heat sink provided in an embodiment of the present application in an unfolded state;

[0034] Figure 5 A right-side structural schematic diagram of an implementation manner of a radiant heat sink provided in an embodiment of the present application in an unfolded state;

[0035] Figure 6 A partial structural schematic diagram of an implementation manner of a radiant heat sink provided in an embodiment of the present application;

[0036] Figure 3 and Figure 5 The middle arrows represent radiative heat dissipation.

[0037] Reference numerals:

[0038] 100, radiation radiator; 110, expandable heat dissipation unit; 111, elastic support; 112, radiation heat dissipation layer; 113, thermal control base layer; 114, thermal conductive layer; 120, thermal conductive support; 130, pressing and unlocking unit; 131, pressing and locking device; 132, unlocking device; 132a, memory alloy drive tube; 132b, heating sleeve; 132c, slotted bolt;

[0039] 200. Spacecraft body; 210. Installation location of heating equipment;

[0040] 300. Rigid expandable radiation radiator; 310. Compression unlocking mechanism; 320. Installation hinge; 330. Pipe heat conduction system. DETAILED DESCRIPTION

[0041] The technical solution of the present application will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the present application, rather than all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present application.

[0042] In the description of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present application. In addition, the terms "first", "second", and "third" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance.

[0043] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0044] As shown in FIG. 1(a) and FIG. 1(b), in the conventional technical solution, before the spacecraft is launched into orbit, the rigid deployable radiant heat sink 300 is mechanically fixedly connected with the spacecraft body 200 and folded on the outer surface of the spacecraft body 200 by the joint action of the installation hinge 320 and the pressing and unlocking mechanism 310; after the spacecraft is launched into orbit, the pressing and unlocking mechanism 310 is powered on and unlocked, and the rigid deployable radiant heat sink 300 rotates and unfolds around the installation hinge 320 along the arrow direction in FIG. 1(a); the rigid deployable radiant heat sink 300 and the spacecraft body 200 are thermally coupled through a complex heat transfer system (pipeline heat conduction system 330) such as a fluid circuit and a loop heat pipe, so as to realize the transfer of heat from the spacecraft body 200 to the rigid deployable radiant heat sink 300, and dissipate heat to space in the form of radiation. The rigid deployable radiant heat sink 300 in the conventional technical solution has a complex system structure and a large weight, and even in the folded state, it occupies the potential installation space of the equipment outside the spacecraft body 200.

[0045] like Figures 2 to 5 As shown, one aspect of the present application provides a radiation heat sink 100, comprising a thermally conductive support 120, a compression unlocking unit 130 and an expandable heat dissipation unit 110, wherein the thermally conductive support 120 is used to be fixed to a spacecraft body 200, and in the length direction of the expandable heat dissipation unit 110, one end of the expandable heat dissipation unit 110 is a fixed end fixed to the thermally conductive support 120, and the other end of the expandable heat dissipation unit 110 is a connecting end, and the expandable heat dissipation unit 110 is used to be arranged in a spiral roll so that the connecting end is one end on the inner side of the spiral roll, and the compression unlocking unit 130 is fixed to the thermally conductive support 120, and the compression unlocking unit 130 is detachably connected to the connecting end.

[0046] The radiation heat sink 100 provided in the present application, when in use, can flexibly and specifically select the fixed position of the heat-conducting support 120 on the outer surface of the spacecraft body 200 according to the position of the heat-generating device, and one or more radiation heat sinks 100 can be selectively arranged on the outer surface of the same side of the spacecraft body 200. Before heat radiation heat dissipation is required, the expandable heat dissipation unit 110 is in a state of being folded into a spiral package, and is connected to the compression and unlocking unit 130 so that the expandable heat dissipation unit 110 can remain in the state of being folded into the spiral package. When heat radiation heat dissipation is required, the compression and unlocking unit 130 is controlled to separate from the expandable heat dissipation unit 110, so that the expandable heat dissipation unit 110 is gradually unfolded and finally in a fully unfolded state. At this time, the expandable heat dissipation unit 110 will radiate outward the heat transferred from the spacecraft body 200 and the heat-conducting support 120 in turn, so as to achieve the purpose of heat dissipation.

[0047] The radiation radiator 100 provided in the present application is in a retracted spiral roll before the deployable heat dissipation unit 110 is deployed, and occupies a smaller area of ​​the outer surface of the spacecraft body 200, so that more space on the outer surface of the spacecraft body 200 can be used to install other equipment, which is conducive to the further development of high-functional density spacecraft in the direction of lightness and miniaturization; at the same time, the radiation radiator 100 is in a retracted spiral roll, and the overall volume is small, which is more conducive to the miniaturization development of high-functional density spacecraft; and the radiation radiator 100 provided in the present application has the heat dissipation performance of the traditional deployable radiation radiator 100, and has the advantages of high surface-to-mass ratio (ratio of heat dissipation area to mass), light weight and high efficiency, and decoupling from the complex thermal control system of the entire spacecraft, and can be flexibly set on the spacecraft body 200. ; Moreover, the radiation radiator 100 provided in the present application has the characteristics of small shrinkage envelope and flexible setting, which is conducive to shortening the heat conduction distance from the heat source to the radiation radiator 100 and improving the heat dissipation efficiency; in addition, the radiation radiator 100 provided in the present application has low complexity, simplifies the complex heat transfer system between the heat source and the radiation radiator 100, shortens the heat conduction path and reduces the heat transfer thermal resistance, reduces the complexity of the entire heat dissipation system (including the heat transfer system for heat conduction from the heat source to the radiation radiator 100, and the radiation heat dissipation system for the radiation radiator 100 to expand heat and dissipate heat to the space environment) and improves the reliability of the heat dissipation system; the design and implementation method of the radiation radiator 100 provided in the present application has strong adaptability and versatility, and can be mass-produced and assembled on mass production lines in the form of unit modules. Optionally, the expandable heat dissipation unit 110 includes a heat dissipation module and an elastic support member 111, both of which extend from the fixed end to the connection end, and the elastic support member 111 is fixedly connected to the heat dissipation module, and the elastic support member 111 is used to expand the expandable heat dissipation unit 110 from a spiral roll to a linear extension. In this way, when the expandable heat dissipation unit 110 is in a spiral roll, the heat dissipation module and the elastic support member 111 are both in a spiral roll, and the elastic support member 111 stores elastic potential energy due to elastic deformation. When the control pressing and unlocking unit 130 is separated from the expandable heat dissipation unit 110, the elastic support member 111 returns to a linear extension under the action of its own elastic potential energy, and at the same time, drives the heat dissipation module to be expanded at the same time, so that the expandable heat dissipation unit 110 is expanded into a linear extension, and the expandable heat dissipation unit 110 is kept in a linear extension under the elastic action of the elastic support member 111.

[0048] Optionally, the heat dissipation module includes a thermal control base layer 113 and a radiation heat dissipation layer 112, and the radiation heat dissipation layer 112 covers one side surface of the thermal control base layer 113. The thermal control base layer 113 serves as the basic structure of the heat dissipation module on the one hand, and can further diffuse the heat transferred from the spacecraft body 200 to the heat conductive support 120 to the outside on the other hand. Covering one side surface of the thermal control base layer 113 with the radiation heat dissipation layer 112 can improve the efficiency of heat radiation and dissipation. In the embodiment of the present application, the radiation heat dissipation layer 112 can be made of, but not limited to, a flexible thermal control material with low absorption and high emissivity, such as a thin-film secondary surface mirror.

[0049] Optionally, the surface of the radiation heat dissipation layer 112 that is away from the heat control base layer 113 forms the outer surface of the spirally rolled expandable heat dissipation unit 110. In this way, when the expandable heat dissipation unit 110 is in an unfolded state, it can still efficiently radiate a certain amount of heat outward through the radiation heat dissipation layer 112, and has good heat dissipation capacity before the heat dissipation function of the radiation radiator 100 is started.

[0050] Optionally, the heat dissipation module further includes a heat conductive layer 114, which covers the other side surface of the thermal control base layer 113. The heat conductive layer 114 can quickly guide the heat at the heat point of the thermal conductive support 120 to the thermal control base layer 113, and then quickly dissipate it from the radiation heat dissipation layer 112, further improving the heat dissipation efficiency. In the embodiment of the present application, the heat conductive layer 114 can be made of, but not limited to, a high thermal conductivity material such as graphite film, copper sheet, indium foil or asphalt-based carbon fiber.

[0051] Optionally, the elastic support member 111 is located on the side of the thermal control base layer 113 away from the radiation heat dissipation layer 112, and the elastic support member 111 is fixed to the thermal control base layer 113. In this way, the elastic support member 111 is arranged relatively far away from the radiation heat dissipation layer 112, so that the elastic support member 111 is not easy to hinder the heat dissipation of the radiation heat dissipation layer 112. In the embodiment of the present application, the elastic support member 111 and the thermal control base layer 113 are preferably integratedly processed or integratedly molded, or other fixed connection methods. When the heat dissipation module includes a thermal conductive layer 114, the elastic support member 111 passes through the thermal conductive layer 114 and is connected to the thermal control base layer 113.

[0052] Optionally, the radiation heat sink 100 provided in the embodiment of the present application includes a plurality of the elastic support members 111, and each of the elastic support members 111 is arranged along the surface of the thermal control base layer 113. In this way, when the expandable heat dissipation unit 110 is in a spiral roll, the plurality of elastic support members 111 can store more elastic potential energy, and the expandable heat dissipation unit 110 can be expanded more quickly when separated from the pressed unlocking unit 130, thereby shortening the heat dissipation time and improving the heat dissipation efficiency. In the embodiment of the present application, the number of the elastic support members 111 can be 2 to 5, for example, 3 or 4, and preferably, the number of the elastic support members 111 is 3. It can be understood that the situation in which the radiation heat sink 100 includes only one elastic support member 111 is also within the protection scope of the present application.

[0053] Optionally, the elastic support member 111 is a tube. In this way, when the expandable heat dissipation unit 110 is in a spiral roll, the tubular elastic support member 111 is flattened and compressed, and occupies a smaller space, thereby making the spirally rolled expandable heat dissipation unit 110 occupy a smaller space, which is conducive to the further development of high-function density spacecraft in the direction of lightness and miniaturization. Of course, the elastic support member 111 can also be a solid rib-shaped member, but it occupies more space than making the elastic support member 111 a tube.

[0054] Optionally, the heat-conducting support 120 includes a support body and an auxiliary heat-dissipating layer, and the auxiliary heat-dissipating layer covers the surface of the support body. In this way, regardless of whether the expandable heat-dissipating unit 110 is in the expanded state, the heat-conducting support 120 can diffuse a certain amount of heat outward, so that the radiation radiator 100 has a good heat-dissipating ability before the heat-dissipating function is fully started, thereby improving the heat-dissipating efficiency.

[0055] Another aspect of the present application provides a spacecraft, including a spacecraft body 200 and the radiation heat sink 100 provided in an embodiment of the present application, wherein the heat conducting support 120 is fixed to the spacecraft body 200. Figure 2 As shown, the radiation heat sink 100 is arranged at the heating device installation position 210 marked by Xu Xuankuang on the spacecraft body 200. It can be understood that the spacecraft in the embodiment of the present application includes at least one radiation heat sink 100, for example, 2 to 5 radiation heat sinks 100 can be arranged on one side surface of the spacecraft body 200, for example, 3 or 4 radiation heat sinks 100 can be arranged.

[0056] The spacecraft provided in the present application adopts the radiation heat sink 100 provided in the present application. Before the expandable heat dissipation unit 110 is expanded, the radiation heat sink 100 is in a collapsed spiral roll, occupying a smaller area of ​​the outer surface of the spacecraft body 200, so that more space on the outer surface of the spacecraft body 200 can be used to install other equipment, which is conducive to the further development of high-functional density spacecraft in the direction of lightness and miniaturization.

[0057] like Figure 6 As shown, in the embodiment of the present application, the pressing and unlocking unit 130 includes a pressing device 131 and an unlocking device 132, wherein the unlocking device 132 can adopt different types of unlocking devices 132 such as pyrotechnic unlocking, hot knife unlocking or memory alloy unlocking. Taking the compression unlocking unit 130 unlocked by memory alloy as an example, when the radiation heat sink 100 is in the folded state, the compression unlocking unit 130 is in the compressed state. At this time, the slotted bolt 132c is used as a normal connecting bolt to play a role of fixing the connection between the compression device 131 and the unlocking device 132. The compression device 131 is located on the inner side of the spirally rolled expandable heat dissipation unit 110. The slotted bolt 132c passes through the expandable heat dissipation unit 110 (especially through the connecting end) and is connected to the compression device 131; during the expansion process of the radiation heat sink 100, the compression unlocking unit 130 is unlocked and released. At this time, the heating sleeve 132b heats the memory alloy driving tube 132a. The memory alloy driving tube 132a is axially deformed after being heated, and the slotted bolt 132c is pushed off from the slotted part, completing the unlocking and releasing of the compression unlocking unit 130. The expandable heat dissipation unit 110 is gradually expanded, thereby further realizing the expansion of the radiation heat sink 100.

[0058] Figure 6 In the embodiment of the present application, the radiation heat sink 100 provided in the embodiment of the present application preferably includes two sets of compression and unlocking units 130. In the embodiment of the present application, one or more compression and unlocking units 130 can be provided according to the size of the radiation heat sink 100.

[0059] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit it. Although the present application has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present application.

Claims

1. A radiant heat sink, characterized in that: It includes a thermally conductive support, a compression unlocking unit and an expandable heat dissipation unit, the thermally conductive support is used to be fixed to the spacecraft body, one end of the expandable heat dissipation unit in the length direction of the expandable heat dissipation unit is a fixed end fixed to the thermally conductive support, and the other end of the expandable heat dissipation unit is a connecting end, the expandable heat dissipation unit is used to be arranged in a spiral roll so that the connecting end is an end on the inner side of the spiral roll, the compression unlocking unit is fixed to the thermally conductive support, and the compression unlocking unit is detachably connected to the connecting end.

2. The radiant heat sink according to claim 1, characterized in that: The expandable heat dissipation unit includes a heat dissipation module and an elastic support member, both of which extend from the fixed end to the connecting end, and the elastic support member is fixedly connected to the heat dissipation module. The elastic support member is used to expand the expandable heat dissipation unit from a spiral roll to a linear extension.

3. The radiant heat sink according to claim 2, characterized in that: The heat dissipation module comprises a heat control base layer and a radiation heat dissipation layer, and the radiation heat dissipation layer covers a side surface of the heat control base layer.

4. The radiant heat sink according to claim 3, characterized in that: The surface of the radiation heat dissipation layer that is disposed away from the thermal control base layer forms the outer surface of the spirally rolled expandable heat dissipation unit.

5. The radiant heat sink according to claim 3, characterized in that: The heat dissipation module further comprises a thermally conductive layer, and the thermally conductive layer covers the other side surface of the thermal control base layer.

6. The radiant heat sink according to claim 3, characterized in that: The elastic support member is located on a side of the thermal control base layer away from the radiation heat dissipation layer, and the elastic support member is fixed to the thermal control base layer.

7. The radiant heat sink according to claim 6, characterized in that: It comprises a plurality of elastic supporting members, each of which is arranged along the surface of the thermal control base layer.

8. The radiant heat sink according to claim 2, characterized in that: The elastic supporting member is a pipe.

9. The radiant heat sink according to any one of claims 1 to 8, characterized in that: The heat-conducting support comprises a support body and an auxiliary heat dissipation layer, and the auxiliary heat dissipation layer covers the surface of the support body.

10. A spacecraft, characterized in that It comprises a spacecraft body and a radiation heat sink as claimed in any one of claims 1 to 9, wherein the heat conductive support is fixed to the spacecraft body.

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