Radiation radiator and spacecraft

Abstract

The application relates to the field of aerospace technology, in particular to a radiation radiator and a spacecraft. The radiation radiator comprises a heat-conducting support, a solid-pressing unlocking unit and an expandable heat-dissipating unit. The heat-conducting support is used for being fixed to a spacecraft body. One end of the expandable heat-dissipating unit in the length direction of the expandable heat-dissipating unit is a fixed end fixed to the heat-conducting support. The other end of the expandable heat-dissipating unit is a connecting end. The expandable heat-dissipating unit is arranged in a spiral roll shape so that the connecting end is one end inside the spiral roll shape. The solid-pressing unlocking unit is fixed to the heat-conducting support. The solid-pressing unlocking unit is in separable connection with the connecting end. The application aims to solve at least one technical problem in the background art and provides a radiation radiator.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aerospace technology, in particular, to a radiation radiator and a spacecraft. BACKGROUND

[0002] Due to the environment characteristics of high vacuum degree in the universe, the heat exchange between the spacecraft and the external environment is carried out by radiation, so the radiation radiator is the only heat dissipation mode for the spacecraft to run in the vacuum environment.

[0003] The radiation heat dissipation capacity of the spacecraft is positively correlated with the area size of the radiation heat dissipation surface; for the spacecraft with low heat load, only the structure surface or part of the structure surface of the spacecraft can be used as the heat dissipation surface to meet the heat dissipation demand; however, with the expansion of the functions of the spacecraft, the power area density of the spacecraft is higher and higher, which causes the heat load to increase significantly, so the area of the spacecraft structure is insufficient to support the timely dissipation of the heat of the spacecraft, at this time, the independent radiator needs to be added, and the heat generated by the internal or surface equipment of the spacecraft is conducted to the independent radiation radiator through a series of heat conduction means, so as to increase the effective area of the spacecraft for radiation heat dissipation to the universe.

[0004] Under this background, the radiation radiator gradually develops into an independent device separated from the spacecraft structure. In order to control the envelope size of the spacecraft in the launch state, the radiation radiator independent of the spacecraft structure is usually folded in the launch phase and unfolded in the orbiting phase. The deployable radiator in the traditional form is usually a rigid structure, which is pressed and locked to the outer surface of the spacecraft structure plate in the folded state. The deployable radiation radiator in this form occupies a large part of the outer surface of the spacecraft, and the folding position of the deployable radiation radiator corresponds to the outer surface of the spacecraft which cannot be installed with other equipment, which is not conducive to the further development of the high-function-density spacecraft in the direction of light and small size. SUMMARY

[0005] The present application aims to solve at least one technical problem in the background art, and provides a radiation radiator.

[0006] In order to achieve the above-mentioned purpose, the present application adopts the following technical solutions:

[0007] One aspect of the present application provides a radiation radiator, which comprises a heat-conducting support, a press-solidifying unlocking unit and a deployable heat dissipation unit. The heat-conducting support is used to be fixed to the spacecraft structure. One end of the deployable heat dissipation unit in the length direction of the deployable heat dissipation unit is a fixed end fixed to the heat-conducting support, and the other end of the deployable heat dissipation unit is a connecting end. The deployable heat dissipation unit is arranged in a spiral roll shape so that the connecting end is one end inside the spiral roll shape. The press-solidifying unlocking unit is fixed to the heat-conducting support, and the press-solidifying unlocking unit is separably connected with the connecting end.

[0008] Optionally, the deployable heat dissipation unit comprises a heat dissipation module and an elastic support, the heat dissipation module and the elastic support both extend from the fixed end to the connecting end, the elastic support is fixedly connected with the heat dissipation module, and the elastic support is used for deploying the deployable heat dissipation unit from the spiral roll shape into the straight line extension shape.

[0009] The beneficial effects of the technical scheme are that when the deployable heat dissipation unit is in the spiral roll shape, the heat dissipation module and the elastic support are both in the spiral roll shape, the elastic support stores elastic potential energy due to elastic deformation, when the control pressure fixing unlocking unit is separated from the deployable heat dissipation unit, the elastic support restores to the straight line extension shape under the action of the elastic potential energy, at the same time, the heat dissipation module is also deployed, so that the deployable heat dissipation unit is deployed into the straight line extension shape, and the deployable heat dissipation unit is kept in the straight line extension shape under the elastic action of the elastic support.

[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 one side surface of the heat control base layer.

[0011] The beneficial effects of the technical scheme are that the heat control base layer serves as the basic structure of the heat dissipation module and can further diffuse the heat transferred from the spacecraft body to the heat conduction support outward, and covering the radiation heat dissipation layer on one side surface of the heat control base layer can improve the efficiency of heat radiation and dissipation.

[0012] Optionally, the surface of the radiation heat dissipation layer away from the heat control base layer forms the outer surface of the deployable heat dissipation unit in the spiral roll shape.

[0013] The beneficial effects of the technical scheme are that when the deployable heat dissipation unit is in the unexpanded state, a certain amount of heat can still be radiated outward by the radiation heat dissipation layer efficiently, and good heat dissipation capacity is achieved before the heat dissipation function of the radiation heat dissipation device is started.

[0014] Optionally, the heat dissipation module further comprises a heat conduction paving layer, and the heat conduction paving layer covers the other side surface of the heat control base layer.

[0015] The beneficial effects of the technical scheme are that the heat conduction paving layer can quickly guide the heat of the heat conduction support to the heat control base layer, and then quickly dissipate the heat from the radiation heat dissipation layer, thereby further improving the heat dissipation efficiency.

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

[0017] The beneficial effects of the technical scheme are that the elastic support is arranged relatively far from the radiation heat dissipation layer, and thus the elastic support is less likely to hinder the radiation heat dissipation layer by dissipating heat.

[0018] Optionally, the radiation heat radiator provided in the application comprises a plurality of the elastic supports, and each of the elastic supports is arranged along the surface of the thermal control base layer.

[0019] The beneficial effects of the technical scheme are that when the expandable heat dissipation unit is in the spiral roll shape, the plurality of elastic supports can store more elastic potential energy, and the expandable heat dissipation unit can be more quickly unfolded when separated from the pressure-solidification unlocking unit, thereby shortening the heat dissipation time and improving the heat dissipation efficiency.

[0020] Optionally, the elastic support is a pipe.

[0021] The beneficial effects of the technical scheme are that when the expandable heat dissipation unit is in the spiral roll shape, the tubular elastic support is flattened and compressed, and occupies a smaller space, and thus the spiral roll-shaped expandable heat dissipation unit occupies a smaller space, which is conducive to the further development of high-function-density spacecraft in the direction of miniaturization.

[0022] Optionally, 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.

[0023] The beneficial effects of the technical scheme are that no matter whether the expandable heat dissipation unit is in the unfolded state or not, the heat-conducting support can diffuse a certain amount of heat outward, so that the radiation heat radiator has good heat dissipation capacity before the heat dissipation function is completely started, thereby improving the heat dissipation efficiency.

[0024] Another aspect of the application provides a spacecraft, which comprises a spacecraft body and the radiation heat radiator provided in the application, and the heat-conducting support is fixed to the spacecraft body.

[0025] The technical scheme provided in the application can achieve at least one of the following beneficial effects:

[0026] The radiation heat radiator and the spacecraft provided in the application are in the folded spiral roll shape before the expandable heat dissipation unit is unfolded, and thus the radiation heat radiator occupies a smaller area on the outer surface of the spacecraft body, so that more space on the outer surface of the spacecraft body can be used for installing other equipment, which is conducive to the further development of high-function-density spacecraft in the direction of miniaturization.

[0027] The additional technical features of the application and their advantages will be more apparent in the following description or can be understood through the specific implementation of the application. BRIEF DESCRIPTION OF DRAWINGS

[0028] In order to more clearly illustrate the technical solutions in the specific embodiments of the present application, the drawings needed to be used in the specific embodiment description will be briefly introduced. Obviously, the drawings described below are some embodiments of the present application, and other drawings can also be obtained by those skilled in the art without any creative effort on the basis of these drawings.

[0029] Fig. 1(a) is a structural schematic diagram of a rigid deployable radiation heat sink mounted on a spacecraft body in the prior art, in which the rigid deployable radiation heat sink is in a closed state;

[0030] Fig. 1(b) is a structural schematic diagram of a rigid deployable radiation heat sink mounted on a spacecraft body in the prior art, in which the rigid deployable radiation heat sink is in an expanded state;

[0031] Figure 2 Fig. 2 is a partial perspective structural schematic diagram of an embodiment of a spacecraft provided by the present application;

[0032] Figure 3 Fig. 3 is a front view structural schematic diagram of an embodiment of a radiation heat sink provided by the present application in an expanded state;

[0033] Figure 4 Fig. 4 is a top view structural schematic diagram of an embodiment of a radiation heat sink provided by the present application in an expanded state;

[0034] Figure 5 Fig. 5 is a right view structural schematic diagram of an embodiment of a radiation heat sink provided by the present application in an expanded state;

[0035] Figure 6 Fig. 6 is a partial structural schematic diagram of an embodiment of a radiation heat sink provided by the present application;

[0036] Figure 3 Fig. 7 is a partial structural schematic diagram of an embodiment of a radiation heat sink provided by the present application; Figure 5 Fig. 8 is a partial structural schematic diagram of an embodiment of a radiation heat sink provided by the present application, in which the arrow represents radiation heat dissipation.

[0037] Reference signs:

[0038] 100, radiation heat sink; 110, deployable heat dissipation unit; 111, elastic support; 112, radiation heat dissipation layer; 113, thermal control base layer; 114, heat conduction laying layer; 120, heat conduction support; 130, press-solidification unlocking unit; 131, press-solidification device; 132, unlocking device; 132a, memory alloy driving tube; 132b, heating sleeve; 132c, slotted bolt;

[0039] 200, spacecraft body; 210, heat generating equipment mounting position;

[0040] 300, rigid deployable radiator; 310, compression unlocking mechanism; 320, mounting hinge; 330, pipeline heat conduction system. DETAILED DESCRIPTION

[0041] The technical solutions of the present application will be described clearly and completely below in combination with the drawings. Obviously, the described embodiments are part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application.

[0042] In the description of the present application, it should be noted that the orientations or positional relationships indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application. In addition, the terms "first", "second", "third" are only for the purpose of description, and cannot be understood as indicating or implying relative importance.

[0043] In the description of the present application, it should be noted that unless otherwise explicitly specified and limited, the terms "mounting", "connecting", "connecting" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium; it can be the communication inside two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0044] As shown in FIG. 1(a) and FIG. 1(b), in the prior art, before the spacecraft is launched into orbit, the rigid deployable radiator 300 is mechanically fixedly connected with the spacecraft body 200 and is folded on the outer surface of the spacecraft body 200 through the joint action of the mounting hinge 320 and the compression unlocking mechanism 310; after the spacecraft is launched into orbit, the compression unlocking mechanism 310 is unlocked by power, and the rigid deployable radiator 300 rotates and expands along the arrow direction in FIG. 1(a) around the mounting hinge 320; the rigid deployable radiator 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, to realize the transfer of heat on the spacecraft body 200 to the rigid deployable radiator 300, and radiate heat to space in the form of radiation. The rigid deployable radiator 300 system in the prior art has complex structure and large weight, and even in the folded state, it also occupies the potential installation space of the outer equipment of the spacecraft body 200.

[0045] As Figures 2 to 5 shown, one aspect of the present application provides a radiation heat sink 100, comprising a heat-conducting support 120, a press-fixing unlocking unit 130 and an expandable heat-dissipating unit 110, the heat-conducting support 120 is used to be fixed to a spacecraft body 200, one end of the expandable heat-dissipating unit 110 in the length direction of the expandable heat-dissipating unit 110 is a fixed end fixed to the heat-conducting support 120, the other end of the expandable heat-dissipating unit 110 is a connecting end, the expandable heat-dissipating unit 110 is used to be arranged in a spiral winding shape so that the connecting end is one end inside the spiral winding shape, the press-fixing unlocking unit 130 is fixed to the heat-conducting support 120, and the press-fixing unlocking unit 130 is detachably connected with the connecting end.

[0046] The radiation heat sink 100 provided by the present application can flexibly 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 equipment in use, and one or more radiation heat sinks 100 can be selected to be arranged on the same side of the outer surface of the spacecraft body 200, the expandable heat-dissipating unit 110 is in a state of being rolled up into a spiral winding before heat radiation and dissipation, and the expandable heat-dissipating unit 110 can be kept in the state of being rolled up into a spiral winding through the connection with the press-fixing unlocking unit 130, when heat radiation and dissipation are needed, the press-fixing unlocking unit 130 is controlled to be separated from the expandable heat-dissipating unit 110, so that the expandable heat-dissipating unit 110 is gradually expanded and finally in a fully expanded state, at this time, the expandable heat-dissipating unit 110 will radiate the heat transferred from the spacecraft body 200 and the heat-conducting support 120 outward in sequence to achieve the purpose of heat dissipation.

[0047] The radiation radiator 100 provided in the present application is in a coiled form before the deployable heat dissipation unit 110 is deployed, occupies a small area of the outer surface of the spacecraft body 200, and makes more space of the outer surface of the spacecraft body 200 available for installing other equipment, which is conducive to the development of high-function-density spacecraft in the direction of light and miniaturization. Meanwhile, the radiation radiator 100 is in a coiled form, and has a small overall volume, which is more conducive to the development of high-function-density spacecraft in the direction of miniaturization. Moreover, the radiation radiator 100 provided in the present application has the advantages of high area-to-mass ratio (ratio of heat dissipation area to mass), light weight and high efficiency, decoupling from the complex thermal control system of the entire spacecraft, and flexible setting on the spacecraft body 200, while having the heat dissipation performance of a traditional radiation radiator 100. Furthermore, the characteristics of small coiled envelope and flexible setting of the radiation radiator 100 provided in the present application are 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, which 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 resistance, reduces the complexity of the entire heat dissipation system (including the heat transfer system from the heat source to the radiation radiator 100, and the radiation heat dissipation system of the radiation radiator 100 itself for spreading heat and dissipating 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 universality, and can be mass-produced and assembled in a production line in the form of a unit module. Optionally, the deployable heat dissipation unit 110 includes a heat dissipation module and an elastic support 111, the heat dissipation module and the elastic support 111 both extend from the fixed end to the connecting end, the elastic support 111 is fixedly connected with the heat dissipation module, and the elastic support 111 is used for unfolding the deployable heat dissipation unit 110 from a coiled form into a straight-line extension form. In this way, when the deployable heat dissipation unit 110 is in a coiled form, the heat dissipation module and the elastic support 111 are both in a coiled form, the elastic support 111 stores elastic potential energy due to elastic deformation, when the control and fixation unlocking unit 130 is separated from the deployable heat dissipation unit 110, the elastic support 111 restores to a straight-line extension form under the action of the elastic potential energy, and at the same time, drives the heat dissipation module to be unfolded, so that the deployable heat dissipation unit 110 is unfolded into a straight-line extension form, and the deployable heat dissipation unit 110 is kept in a straight-line extension form under the elastic action of the elastic support 111.

[0048] Optionally, the heat dissipation module comprises a heat control base layer 113 and a radiation heat dissipation layer 112, the radiation heat dissipation layer 112 covers one side surface of the heat control base layer 113. The heat control base layer 113 serves as the basic structure of the heat dissipation module on one hand, and can further spread the heat transferred from the spacecraft body 200 to the heat conducting support 120 on the other hand. Covering one side surface of the heat 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 but is not limited to a thin film type secondary surface mirror or other low-absorption high-emissivity flexible heat control material.

[0049] Optionally, the surface of the radiation heat dissipation layer 112 away from the heat control base layer 113 forms the outer surface of the expandable heat dissipation unit 110 in a spiral roll shape. In this way, when the expandable heat dissipation unit 110 is in an unexpanded state, a certain amount of heat can still be efficiently radiated outward by the radiation heat dissipation layer 112, and the heat dissipation module has good heat dissipation capacity before the heat dissipation function of the radiation heat dissipation device 100 is started.

[0050] Optionally, the heat dissipation module further comprises a heat conducting paving layer 114, the heat conducting paving layer 114 covers the other side surface of the heat control base layer 113. The heat conducting paving layer 114 can quickly guide the heat of the heat conducting support 120 to the heat control base layer 113, and then quickly dissipate from the radiation heat dissipation layer 112, further improving the heat dissipation efficiency. In the embodiment of the present application, the heat conducting paving layer 114 can be but is not limited to graphite film, copper sheet, indium foil or pitch-based carbon fiber or other high-thermal-conductivity materials.

[0051] Optionally, the elastic support 111 is located on the side of the heat control base layer 113 away from the radiation heat dissipation layer 112, and the elastic support 111 is fixed to the heat control base layer 113. In this way, the elastic support 111 is arranged relatively far away from the radiation heat dissipation layer 112, so that the elastic support 111 is less likely to hinder the radiation heat dissipation layer 112 from dissipating heat. In the embodiment of the present application, the elastic support 111 and the heat control base layer 113 are preferably integrally processed or integrally formed, or other fixed connection modes. When the heat dissipation module comprises the heat conducting paving layer 114, the elastic support 111 passes through the heat conducting paving layer 114 and is connected to the heat control base layer 113.

[0052] Optionally, the radiation heat sink 100 provided by the embodiment of the present application comprises a plurality of elastic supporting members 111, and each elastic supporting member 111 is arranged along the surface of the thermal control base layer 113. In this way, when the deployable heat dissipation unit 110 is in the spiral roll shape, the plurality of elastic supporting members 111 can store more elastic potential energy, and the deployable heat dissipation unit 110 can be more quickly deployed when separated from the pressure-solidification 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 supporting members 111 can be 2 to 5, for example, can be 3 or 4, and preferably, the number of the elastic supporting members 111 is 3. It can be understood that the case where the radiation heat sink 100 only comprises one elastic supporting member 111 is also within the protection scope of the present application.

[0053] Optionally, the elastic supporting member 111 is a pipe. In this way, when the deployable heat dissipation unit 110 is in the spiral roll shape, the tubular elastic supporting member 111 is flattened and compressed, occupies a smaller space, and thereby the spiral roll-shaped deployable heat dissipation unit 110 occupies a smaller space, which is beneficial for the high-function-density spacecraft to further develop in the direction of light and miniaturization. Of course, the elastic supporting member 111 can also be a solid rib member, but compared with the case where the elastic supporting member 111 is a pipe, it occupies a larger space.

[0054] Optionally, the heat-conducting support 120 comprises a support body and an auxiliary heat dissipation layer, and the auxiliary heat dissipation layer covers the surface of the support body. In this way, whether the deployable heat dissipation unit 110 is in the deployed state or not, the heat-conducting support 120 can diffuse a certain amount of heat outward, so that the radiation heat sink 100 already has good heat dissipation capacity before the heat dissipation function is completely started, thereby improving the heat dissipation efficiency.

[0055] Another aspect of the present application provides a spacecraft comprising a spacecraft body 200 and the radiation heat sink 100 provided by the embodiment of the present application, and the heat-conducting support 120 is fixed to the spacecraft body 200. As shown in Figure 2 The radiation heat sink 100 is arranged at the heat-generating equipment mounting position 210 marked by the optional marker on the spacecraft body 200. It can be understood that the spacecraft in the embodiment of the present application comprises 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, the number can be 3 or 4, etc.

[0056] The spacecraft provided by the present application adopts the radiation heat sink 100 provided by the present application, and before the deployable heat dissipation unit 110 is deployed, the radiation heat sink 100 is in the folded spiral roll shape, occupies a smaller area on the outer surface of the spacecraft body 200, so that more space on the outer surface of the spacecraft body 200 can be used for mounting other equipment, which is beneficial for the high-function-density spacecraft to further develop in the direction of light and miniaturization.

[0057] As Figure 6 shown, in the embodiment of the present application, the compression and solidification unlocking unit 130 comprises a compression and solidification device 131 and an unlocking device 132, wherein the unlocking device 132 can adopt different types of unlocking devices 132 such as a pyrotechnic unlocking, a hot knife unlocking or a memory alloy unlocking. Taking the compression and solidification unlocking unit 130 adopting the memory alloy unlocking as an example, in the state of the radiation radiator 100 being folded, that is, the compression and solidification unlocking unit 130 being compressed, at this time, the slotted bolt 132c is used as a normal connecting bolt, and plays a role of fixed connection between the compression and solidification device 131 and the unlocking device 132, the compression and solidification device 131 is located at the inner side of the expandable heat dissipation unit 110 in the spiral roll shape, and the slotted bolt 132c passes through the expandable heat dissipation unit 110 (especially the connecting end) and is connected with the compression and solidification device 131; in the process of unfolding the radiation radiator 100, that is, the compression and solidification unlocking unit 130 is unlocked and released, at this time, the heating sleeve 132b heats the memory alloy driving pipe 132a, the memory alloy driving pipe 132a is deformed axially after being heated, and the slotted bolt 132c is broken from the slotted part, and the unlocking and releasing of the compression and solidification unlocking unit 130 is completed, and the expandable heat dissipation unit 110 is gradually unfolded, thereby further realizing the unfolding of the radiation radiator 100.

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

[0059] Finally, it should be noted that: the above embodiments are only used to illustrate the technical solutions of the present application, and not to limit them; although the present application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that they can still modify the technical solutions recorded in the foregoing embodiments, or make equivalent replacement for part or all of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the embodiments of the present application.

Claims

1. A radiation heat spreader, characterized by, The heat-conducting support is used for fixing to a spacecraft body, one end of the expandable heat-dissipating unit in the length direction of the expandable heat-dissipating unit is a fixed end fixed to the heat-conducting support, the other end of the expandable heat-dissipating unit is a connecting end, the expandable heat-dissipating unit is arranged in a spiral roll shape so that the connecting end is one end inside the spiral roll shape, the pressure-fixing and unlocking unit is fixed to the heat-conducting support, and the pressure-fixing and unlocking unit is detachably connected with the connecting end. The expandable heat-dissipating unit includes a heat-dissipating module and an elastic support, the heat-dissipating module and the elastic support both extend from the fixed end to the connecting end, the elastic support is fixedly connected with the heat-dissipating module, and the elastic support is used for unfolding the expandable heat-dissipating unit from the spiral roll shape into a straight-line extending shape. The heat-dissipating module includes a thermal control base layer and a radiation heat-dissipating layer, the radiation heat-dissipating layer covers one side surface of the thermal control base layer. The surface of the radiation heat-dissipating layer arranged away from the thermal control base layer forms an outer surface of the expandable heat-dissipating unit in the spiral roll shape. The heat-dissipating module further includes a heat-conducting paving layer, and the heat-conducting paving layer covers the other side surface of the thermal control base layer. The elastic support is a pipe. The heat-conducting support includes a support body and an auxiliary heat-dissipating layer, and the auxiliary heat-dissipating layer covers the surface of the support body.

2. The radiation heat sink of claim 1, wherein The elastic support is located on the side of the thermal control base layer away from the radiation heat-dissipating layer, and the elastic support is fixed to the thermal control base layer.

3. The radiation heat sink of claim 2, wherein, A plurality of elastic supports are included, and each elastic support is arranged along the surface of the thermal control base layer.

4. Spacecraft, characterized in that, The radiation heat-dissipating device includes a spacecraft body and the radiation heat-dissipating device as claimed in any one of claims 1 to 3, and the heat-conducting support is fixed to the spacecraft body.

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