Flexible radiation cooling plate for space

Abstract

The invention discloses a flexible radiation cooling plate for space, and belongs to the technical field of spacecraft thermal management. The flexible radiation cooling plate comprises at least one radiation cooling plate single plate, and each radiation cooling plate single plate is composed of a frame, a rigid fluid pipeline and a flexible radiation film. Wherein the rigid fluid pipeline is fixed on the frame and cooperates with the frame to form an integral supporting structure, the rigid fluid pipeline specifically comprises a liquid inlet main pipeline and a liquid return main pipeline which are oppositely arranged on the edges of the two sides of the frame, and a plurality of branch pipelines which are parallelly connected between the liquid inlet main pipeline and the liquid return main pipeline at intervals, and a parallel flow channel structure is formed; the flexible radiation film covers the rigid fluid pipeline and is used for transmitting heat carried by a working medium flowing through the pipeline to the space environment in a heat radiation mode. Through the rigid-flexible composite modular structure and the parallel flow channel design, the effects that the heat dissipation area can be expanded, and heat transfer is uniform and efficient are achieved, and the comprehensive heat dissipation requirements of a high-power spacecraft for the large heat dissipation area, light weight and high reliability are met.

Description

Technical Field

[0001] This invention relates to the field of spacecraft thermal control technology, specifically to a flexible radiant cooling plate for space applications. Background Technology

[0002] With the development of space computing missions, the thermal management requirements of high-power spacecraft such as computing satellites and space data centers continue to increase. The high-performance computing payloads carried by these spacecraft generate a large amount of waste heat during on-orbit operation. Due to the failure of convection cooling in the vacuum environment of space, this waste heat can only be dissipated into the cold, dark space through radiation. Therefore, the heat dissipation capacity directly affects the stability of equipment performance and the reliability of on-orbit operation.

[0003] To overcome the limitation of rocket envelope size on heat dissipation area during launch, flexible deployable radiators have become an important technological direction. However, existing solutions still face multiple technical challenges in practical applications: At the structural design level, the fluid circuit must simultaneously meet the requirements of pressure-bearing and sealing reliability as well as structural deployability. Purely flexible fluid pipelines are difficult to withstand the system's operating pressure and have poor adaptability to the mechanical vibration environment during the launch phase; although traditional fully rigid pipelines can meet the pressure-bearing and mechanical requirements, their rigidity prevents them from achieving high-compact folding, making it difficult to overcome the launch envelope limitations.

[0004] In terms of heat conduction, a stable and efficient thermal path needs to be established between the flexible radiating surface and the pressurized fluid circuit. In existing solutions, simple physical contact can easily lead to high interfacial thermal resistance, affecting heat transfer efficiency; conventional adhesive methods may experience aging and debonding under alternating high and low temperatures and vacuum environments, resulting in decreased reliability of the thermal interface.

[0005] At the flow channel layout level, the flow channel configuration is crucial to heat dissipation uniformity and system reliability. When using a single series flow channel or an improperly designed parallel flow channel, uneven distribution of the working fluid is likely to occur, reducing the utilization rate of the radiation area. At the same time, an improper flow channel layout may also increase the risk of single-point failure, such as causing local overheating, which in turn affects the long-term operational stability of the system.

[0006] Therefore, it is necessary to propose a novel flexible radial cooling plate solution for space applications to address the problems existing in the aforementioned prior art. Summary of the Invention

[0007] The purpose of this invention is to provide a flexible radiating cooling plate for space applications, which solves the problems in the prior art such as the difficulty in balancing pressure-bearing and sealing with deployability, insufficient reliability of thermal interfaces and heat dissipation efficiency, uneven heat dissipation caused by flow channel layout and single-point failure risk. It realizes a space heat dissipation solution that combines structural reliability, high efficiency of heat transfer and uniform flow channels, and meets the comprehensive thermal management requirements of high-power spacecraft for large heat dissipation area, lightweight and high reliability.

[0008] To achieve the above objectives, the present invention adopts the following technical solution: A flexible radiant cooling plate for space applications includes: at least one radiant cooling plate panel; The radiant cooling plate includes a frame, rigid fluid pipelines, and a flexible radiant membrane; The rigid fluid pipeline is fixed to the frame and forms an integral support structure with the frame. The rigid fluid pipeline includes an inlet main pipeline, a return main pipeline and multiple branch pipelines. The inlet main pipeline and the return main pipeline are arranged opposite to each other on the two sides of the frame. The multiple branch pipelines are arranged in parallel and spaced between the inlet main pipeline and the return main pipeline, and the two ends of the multiple branch pipelines are respectively connected to the inlet main pipeline and the return main pipeline to form a parallel flow channel configuration. The flexible radiant membrane covers the rigid fluid pipeline and is used to radiate the heat carried by the working fluid flowing through the rigid fluid pipeline into the space environment through thermal radiation.

[0009] Compared with the prior art, the flexible radial cooling plate for space applications proposed in this invention has the following advantages: 1) Good structural reliability and scalability. The frame and rigid fluid pipeline work together to form an overall support structure, which not only ensures the pressure bearing capacity and mechanical stability of the fluid circuit, and can adapt to mechanical loads such as vibration and impact during the launch phase; but also supports multi-board expansion and combination through the modular design of "at least one radiant cooling plate", which can break through the limitation of the launch envelope on the heat dissipation area and flexibly adapt to the heat dissipation requirements of different power loads.

[0010] 2) Excellent thermal management efficiency. The main inlet and return pipelines are arranged opposite each other, and multiple branch pipelines are connected in parallel to form a uniform flow channel configuration, which enables the working fluid to be evenly distributed to each branch and avoids local overheating; a flexible radiant membrane covers the rigid fluid pipeline, forming a low thermal resistance interface, which can transfer the heat carried by the working fluid to the cold black space in the form of thermal radiation, thereby improving heat dissipation efficiency.

[0011] 3) High system operational stability. The parallel flow channel configuration enables multi-path diversion of the working fluid, reducing the risk of single-point failure in a single series flow channel and improving system redundancy and reliability; the synergistic support of rigid fluid pipelines and frame, combined with the space environment adaptability of the flexible radiation membrane, ensures that the radiant cooling plate can work stably for a long time in complex space environments such as vacuum and alternating high and low temperatures.

[0012] 4) Strong adaptability to the space environment. Rigid fluid pipelines ensure the sealing reliability of the fluid circuit, while the flexible radiating membrane has good flexibility and resistance to aging in the space environment. The rigid-flexible composite structural design can not only adapt to the folding / deployment mechanical requirements during the launch phase, but also achieve heat radiation heat dissipation during on-orbit, fully matching the special working conditions of spacecraft.

[0013] In summary, this invention, through the modular design of rigid-flexible composite structure and the synergistic cooperation of parallel uniform flow channel configuration, achieves the effects of expandable heat dissipation area and efficient and uniform heat transfer while ensuring structural reliability, sealing stability and adaptability to the space environment. It comprehensively meets the lightweight, high reliability and large heat dissipation requirements of high-power spacecraft for heat dissipation systems. Attached Figure Description

[0014] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort. In the drawings: Figure 1 This is a schematic diagram of a flexible radiant cooling plate for space applications proposed in this invention; Figure 2 This is a schematic diagram of another structure of the flexible radiant cooling plate for space applications proposed in this invention; Figure 3 This is a schematic diagram showing the state in which all the single-layer cooling plates of the flexible radiant cooling plate for space use proposed in this invention are stacked and gathered together in the spacecraft body. Figure 4 This is a schematic diagram showing the unfolded state of all the individual radiating plates of the flexible radiating cooling plate for space applications proposed in this invention. Figure 5 This is a schematic diagram of the internal interface between adjacent radiant cooling plates proposed in this invention; Figure 6 This is a partial view of the internal interface and fluid circuit between adjacent radiant cooling plates proposed in this invention; Figure 7 This is a schematic diagram of the fluid circuit between adjacent radiant cooling plates proposed in this invention; Figure 8 This is a schematic diagram of the rotating water-passing joint proposed in this invention; Figure 9 for Figure 8 A cross-sectional view; Figure 10 for Figure 8 A schematic diagram of the explosion of a rotating water-transfer joint; Figure 11 A cross-sectional view of the outer tube of the rotating water-passing joint; Figure 12 This is a cross-sectional schematic diagram of the inner tube of the rotating water-passing joint.

[0015] In the diagram: 10. Spacecraft body; 30. Cooling plate; 31. Branch pipe; 32. Frame; 33. Flexible radiant membrane; 34. Deployment hinge; 341. First connecting arm; 342. Second connecting arm; 343. Hinge shaft; 35. Rotary water-passing joint; 310. Outer tube; 311. First end of outer tube; 312. Second end of outer tube; 313. Flow guide channel; 314. First pipe joint; 315. Third annular groove; 320. Inner tube; 321. First end of inner tube; 322. Second end of inner tube; 323. Insert tube; 324. First annular groove; 325. Shoulder; 326. Sheath; 327. Second pipe joint; 328. Second annular groove; 331. Hole snap ring; 332. Shaft snap ring; 340. Seal; 351. First bearing; 352. Second bearing; 353. Bushing; 36. Metal hose; 38. Inlet main pipeline; 39. Return main pipeline; 391. First parallel section; 392. Bend section; 393. Second parallel section; 394. Vertical section; 40. Plunger type connector; 51. Inlet port; 52. Return port. Detailed Implementation

[0016] The technical solutions in the embodiments of the present invention will now be clearly and completely described with reference to the accompanying drawings. The described embodiments are only a part of the implementation of the present invention, not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0017] It should be noted that, in the description of this invention, "an embodiment" or "an embodiment of the invention" refers to a specific feature, structure, or characteristic that can be included in at least one implementation of the invention. The phrase "in one embodiment" appearing in different places in the specification does not necessarily refer to the same embodiment, nor are they mutually exclusive individual or selective embodiments. This invention can also be implemented in ways other than those described herein, and any equivalent modifications made by those skilled in the art without departing from the concept of the invention fall within the scope of protection of this invention.

[0018] Before describing the present invention, the term "radiative cooling plate" should be explained: The radiative cooling plate in this invention, also known as a radiative cooling plate or radiative cooling plate, is a device that dissipates heat to the space environment through thermal radiation. Unless otherwise stated, "radiative cooling plate" has the same meaning as "radiative cooling plate" or "radiative cooling plate".

[0019] In high-power spacecraft applications such as space computing, heat dissipation systems must simultaneously meet the comprehensive requirements of large heat dissipation area, lightweight design, and high reliability. Traditional rigid heat sinks are limited by the envelope constraints during the launch phase, making it difficult to further expand the heat dissipation area; while purely flexible thermal control structures have significant shortcomings in terms of pressure resistance, structural stiffness, and long-term reliability of the thermal interface.

[0020] The design concept of this invention is to construct a rigid-flexible composite modular heat dissipation structure. Specifically, this is achieved by: using rigid fluid pipelines and a frame to form a supporting skeleton, ensuring the mechanical stability of the structure and the reliability of fluid sealing; using a flexible radiant membrane as a lightweight and efficient heat radiation interface to achieve efficient heat transfer to the space environment; and using a parallel flow channel configuration to ensure that the working fluid flows evenly through each branch, achieving uniform heat dissipation. Ultimately, while meeting the mechanical requirements of spacecraft launch and on-orbit operation, the invention also achieves the expandability (e.g., multi-plate deployment) and large-area heat dissipation function of the radiant cooling plate.

[0021] The present invention will now be described in detail with reference to the accompanying drawings.

[0022] See Figure 1 As shown, this invention proposes a flexible radiant cooling plate for space applications, comprising at least one radiant cooling plate 30. Each radiant cooling plate 30 is composed of a frame 32, rigid fluid pipelines, and a flexible radiant membrane 33. The rigid fluid pipelines are fixed to the frame 32, forming an integral support structure together with the frame 32. Specifically, the rigid fluid pipelines include a main inlet pipe 38, a main return pipe 39, and multiple branch pipes 31. The main inlet pipe 38 and the main return pipe 39 are arranged opposite each other on the two sides of the frame 32. The multiple branch pipes 31 are distributed parallel to each other between them, and both ends of the multiple branch pipes 31 are connected to the main inlet pipe 38 and the main return pipe 39, respectively, forming a parallel flow channel configuration. The flexible radiant membrane 33 covers the rigid fluid pipelines and is used to transfer the heat carried by the working fluid flowing through the pipelines to the space environment via thermal radiation.

[0023] The layout of the rigid fluid piping and the working fluid flow logic work together to ensure heat dissipation efficiency. The working fluid flows from the main inlet pipe 38 to each branch pipe 31. During the flow through each branch pipe 31, heat is radiated outward through the flexible radiant membrane 33, and finally converges to the main return pipe 39 to form a circulation. This parallel flow channel configuration expands the heat dissipation area through multiple branch pipes 31, achieving uniform distribution of the working fluid within the single board, which helps to reduce the temperature difference between the inlet and outlet and promote a balanced temperature field on the board surface. At the same time, it has the characteristics of flow channel redundancy. Even when a single pipe is partially blocked, it can still maintain some heat dissipation capacity. Moreover, the parallel and spaced branch pipes 31 shorten the flow path of the working fluid, reduce flow channel turning losses, and reduce the overall flow resistance of the system and the load requirements of the drive pump.

[0024] Frame 32 serves as the foundation support for the radiant cooling plate, working in conjunction with rigid fluid piping to enhance structural performance. Frame 32 can be constructed from carbon fiber composite materials or a titanium alloy honeycomb sandwich structure, achieving lightweighting of the plate while ensuring structural performance. During launch, it ensures the structural integrity of the plate; during orbit, it maintains the stability of the heat dissipation surface shape and position; and it precisely positions the spacing and routing of multiple branch pipes 31, ensuring uniform distribution of the working fluid and a balanced temperature field. The combined support structure maintains its integrity in the vacuum and alternating high and low temperature space environment, adapting to the load requirements of mechanical vibrations during launch and orbital attitude adjustments.

[0025] The combination of the flexible radiating membrane 33 and the rigid fluid pipeline further optimizes thermal management and lightweight characteristics. The flexible radiating membrane 33 tightly covers the rigid fluid pipeline, forming a low thermal resistance heat conduction path. Its high infrared emissivity can efficiently convert the heat of the working fluid into infrared radiation and transfer it to the cold black space. At the same time, the flexible radiating membrane 33 is lighter than traditional rigid radiating panels. Combined with the structured distribution of the rigid fluid pipeline, it reduces the overall weight of a single panel while ensuring support strength, meeting the requirements of lightweight and miniaturized design for spacecraft.

[0026] The modular design of this invention further enhances system adaptability. Based on the design of "at least one radiant cooling plate," a single plate can adapt to the heat dissipation requirements of small to medium power payloads, with a compact structure and convenient installation. When multiple plates are combined, they can be folded and collapsed to adapt to the rocket launch envelope constraints, and unfolded to the working position during the on-orbit phase to form a heat dissipation area larger than the spacecraft body, meeting the heat dissipation requirements of high-power equipment. This modular architecture also facilitates ground testing and assembly, providing a foundation for system expansion.

[0027] In summary, this invention achieves system optimization in terms of launch adaptability, structural stability, and thermal management performance through the coordinated design of modular configuration, rigid-flexible composite support structure, and parallel flow channel layout, and can be adapted to the heat dissipation requirements of high-power spacecraft.

[0028] In one embodiment, see still Figure 1The cooling plate 30 is provided with a liquid inlet 51 and a liquid return 52. The liquid inlet main pipeline 38 is connected to the liquid inlet 51 for introducing the working fluid, and the liquid return main pipeline 39 is connected to the liquid return 52 for discharging the working fluid. The liquid return main pipeline 39 is arranged on one side edge of the corresponding frame 32 and includes two parallel sections 391 and 393 arranged in the same direction, a bend section 392, and a vertical section 394. The bend section 392 coaxially connects the top end of the first parallel section 391 to the top end of the second parallel section 393, and the vertical section 394 vertically penetrates the bottom end of the second parallel section 393 and connects to the liquid return 52. The ends of multiple branch pipes 31 that are away from the main inlet pipe 38 are all vertically connected to the first parallel section 391 of the return pipe 39, which is closer to the branch pipe 31. After the working fluid flows through the branch pipe 31, it gathers in the first parallel section 391, is guided through the bend section 392 to the second parallel section 393, and then guided from the second parallel section 393 to the vertical section 394, and finally forms a working fluid return channel through the return interface 52.

[0029] The structural design of the main return pipeline 39 and its connection with the fluid circuit bring about several technical benefits: ① The segmented arrangement of the main return pipeline 39 closely fits the contours of the frame 32, avoiding spatial interference with components such as branch pipelines 31 and flexible radiant membrane 33. This allows for a compact layout of the return pipeline within the limited installation space of the single cooling plate, ensuring the overall structural integrity; ② The segmented connection between the bend section 392 and the vertical section 394 reduces the abruptness of pipeline corners, preventing dead volumes or sharp turns in the flow channel, thus helping to reduce the flow resistance of the working fluid and ensuring the flow stability of the working fluid during the return process; ③ Multiple branch pipelines 31 are uniformly connected to the first... Parallel section 391 allows the working fluid to converge and avoid local working fluid stagnation caused by dispersed convergence points, ensuring that the heat carried by the working fluid can be evenly introduced into the return liquid main line 39, providing stable conditions for subsequent heat to be discharged through the loop; ④ The corresponding connection between the liquid inlet main line 38 and the liquid inlet interface 51, and the return liquid main line 39 (through vertical section 394) and the return liquid interface 52, makes the fluid loop of the radiant cooling plate form a clear closed loop with the external system, reducing the ambiguity of the connection at the interface, and the direct connection between the vertical section 394 and the return liquid interface 52 optimizes the end point positioning of the return liquid channel, which helps to reduce the risk of working fluid leakage at the interface and improve the overall reliability of the fluid loop.

[0030] In summary, the embodiments of the present invention achieve synergistic optimization in terms of space utilization, working fluid flow stability, heat flow uniformity, and loop connection reliability through the L-shaped segmented adaptation design of the return liquid main pipeline 39, the precise connection of each pipeline segment, the centralized convergence of multiple branch pipelines 31 and the first parallel section 391, and the corresponding connection of fluid loops and interfaces. This provides structural and fluid transport-level guarantees for the efficient heat dissipation function of the radiant cooling plate.

[0031] In one embodiment, the flexible radiation film is a graphene-based composite film, which is formed by combining graphene and polyimide.

[0032] Graphene and polyimide can be combined in various ways, including but not limited to: graphene as a surface coating covering a polyimide film; graphene dispersed in the form of two-dimensional nanosheets in a polyimide matrix to form a three-dimensional thermally conductive network; graphene and polyimide can be blended and combined through solution mixing or copolymerization; or a multilayer stacked structure with alternating graphene and polyimide layers can be used.

[0033] In this composite film, the graphene component provides a high in-plane thermal conductivity, promoting the lateral diffusion of heat along the radiating surface, which helps improve the uniformity of the temperature distribution on the surface of the radiating plate and reduces the risk of local overheating. At the same time, the high infrared emissivity of graphene material enables the composite film to maintain effective space thermal radiation capability.

[0034] The polyimide substrate provides the necessary flexibility for the composite structure, enabling it to adapt to the folded state of the radiation-cooled plate during launch and its deployment in orbit. Furthermore, the radiation resistance and antigenic oxygen erosion resistance of the polyimide material ensures the long-term service of the composite film in the space environment.

[0035] In addition, both graphene and polyimide are low-density materials, and the film formed by their composite can help achieve overall lightweighting of the radiant cooling plate structure while maintaining functional properties.

[0036] Preferably, the graphene-based composite film has an in-plane thermal conductivity of not less than 1200 W / m·K and an infrared emissivity of not less than 0.9. The in-plane thermal conductivity of not less than 1200 W / m·K supports efficient lateral heat diffusion within the film layer, promotes uniform temperature on the radiating surface, and reduces the risk of localized overheating. The infrared emissivity of not less than 0.9 ensures that heat can be radiated to the cold black space with high efficiency. The synergistic effect of these two properties provides a material basis for addressing high power density heat dissipation.

[0037] In summary, the embodiments of the present invention optimize thermal management performance, space environment adaptability and lightweight characteristics by using a graphene-polyimide composite system as a flexible radiation film material.

[0038] In one embodiment, the flexible radiative film has a functional coating sprayed onto its sun-facing side to reduce solar heat absorption. This functional coating can be selected from materials with low solar absorption characteristics, such as aerospace organic white paint, nano-ceramic coatings, or metal oxide coatings. Preferably, the infrared emissivity of this functional coating is not less than 0.85, and the solar absorptivity is not greater than 0.15. Taking aerospace organic white paint as an example, its measured infrared emissivity is 0.87, and its measured solar absorptivity is 0.13.

[0039] This functional coating structure creates a spectrally selective surface: it exhibits high reflectivity in the solar radiation band (mainly visible and near-infrared), reducing external heat input; simultaneously, it maintains high emissivity in the infrared band, preserving radiative heat dissipation capabilities. This low absorption and high emissivity helps optimize the surface's thermal balance and reduce net heat load: when the surface is exposed to sunlight, it reflects most solar radiation, reducing external heat input; when the surface is facing away from the sun, it still assists in heat dissipation. Combined with the high in-plane thermal conductivity of the flexible radiative film itself, this functional coating can suppress the rise in film surface temperature under solar irradiation conditions, mitigate the decrease in radiative heat dissipation efficiency caused by high temperatures, and provide a thermal safety margin for the system in high-temperature environments.

[0040] This treatment, combined with the original high infrared emissivity surface of the flexible radiating film on the shaded side, forms an asymmetric functional structure. The shaded side relies on the high infrared emissivity of the flexible radiating film itself to achieve efficient heat dissipation; while the sun-facing side uses a functional coating to suppress external heat input. This dual-sided partitioned design allows the radiating cooling plate to optimize its overall thermal performance under different external heat flow conditions.

[0041] In practical applications, the orientation of the radiating cooling plate can be adjusted so that the shaded side faces the cold space while the sun-facing side faces direct sunlight, achieving a synergy between heat dissipation requirements and thermal reflection management. This feature enhances the system's thermal control stability throughout the entire orbital cycle.

[0042] In summary, the embodiments of the present invention achieve optimized surface energy management, guaranteed heat dissipation under high-temperature conditions, and improved adaptability to the orbital environment by setting a functional coating with specific spectral characteristics on the sun-facing side of the flexible radiation film.

[0043] In one embodiment, the flexible radiative film is bonded to the surface of a rigid fluid conduit using a low thermal resistance adhesive. The low thermal resistance adhesive is selected from materials with good thermal conductivity, such as thermally conductive adhesives, thermally conductive phase change materials, thermally conductive gels, or thermally conductive double-sided adhesives.

[0044] This low thermal resistance adhesive can fill the microscopic gaps between the flexible radiant membrane and the surface of the rigid fluid conduit, replacing the poorly conductive air layer and forming a more continuous heat conduction path. This interface treatment helps reduce contact thermal resistance and improves the efficiency of heat transfer from the rigid fluid conduit to the flexible radiant membrane.

[0045] While achieving mechanical fixation, the adhesive possesses a degree of flexibility, which can absorb and buffer thermal stress caused by differences in the coefficients of thermal expansion of the materials to some extent. This helps maintain the integrity of the adhesive interface and improves the long-term reliability of the structure under alternating temperature environments.

[0046] From a process implementation perspective, bonding is suitable for combining flexible materials with surfaces that have complex curves or parallel piping structures, facilitating large-area, uniform conformal contact. This tight interfacial contact provides a complete channel for heat flow transfer and plays a positive role in promoting the uniform diffusion of heat within the radiating surface.

[0047] Preferably, the low thermal resistance adhesive also possesses properties such as resistance to atomic oxygen etching, vacuum resistance, and resistance to alternating high and low temperatures to enhance its adaptability to the space environment. Specifically, resistance to atomic oxygen etching helps maintain the integrity of the bonding interface in the low Earth orbit environment; vacuum resistance prevents material volatilization or performance degradation in the space vacuum environment; and resistance to alternating high and low temperatures enables it to maintain stable mechanical and thermal properties under extreme temperature cycling conditions. The combined effect of these properties provides a reliable guarantee for the long-term operation of the connection structure in orbit.

[0048] In summary, the embodiments of the present invention establish a connection interface with low thermal resistance, good stress adaptability and process applicability by using a low thermal resistance adhesive with spatial environmental adaptability for interface connection, thus providing a specific implementation scheme for achieving a stable heat conduction path.

[0049] In one embodiment, a thermally conductive enhancement layer is disposed between the flexible radiative membrane and the rigid fluid pipeline. This thermally conductive enhancement layer has a micro-nano trench structure and can be selected from high thermally conductive materials such as graphite foil or metal mesh.

[0050] The in-plane thermal conductivity of the thermally reinforcing layer is generally superior to that of a single adhesive material, allowing heat to diffuse laterally across the interface layer before reaching the flexible radiant film. This thermal diffusion characteristic helps promote heat distribution over a wider area, positively impacting the surface temperature uniformity of the radiant cooling plate.

[0051] In terms of heat transfer pathways, the micro-nano trench structure provides denser heat flow channels by increasing the effective contact area with adjacent interfaces. This structural feature can effectively reduce interfacial contact thermal resistance and improve the efficiency of heat transfer from rigid fluid channels to flexible radiative films.

[0052] In terms of structural design, micro- and nano-grooves can be designed with specific orientations or patterns, which can guide the heat flow path and promote heat diffusion along a predetermined direction, thereby further optimizing the temperature distribution within the radiating surface. Simultaneously, this structure enhances interlayer adhesion by increasing the mechanical interlocking between interfaces, contributing to improved long-term stability of the interface structure under mechanical and thermal cycling conditions.

[0053] From a process implementation perspective, micro-nano trench structures can be realized on various high thermal conductivity materials through processes such as etching and imprinting. This design, while maintaining the flexibility and lightweight properties of the materials, provides excellent conformal contact capability with complex curved surfaces, providing a technical foundation for achieving stable large-area thermal contact in structures such as parallel pipelines.

[0054] In summary, the embodiments of the present invention achieve the technical effects of enhanced interface heat transfer, optimized temperature distribution, improved mechanical bonding reliability, and improved process adaptability by employing a thermally conductive enhancement layer with a micro-nano trench structure.

[0055] In one embodiment, see Figures 2 to 4 As shown, the flexible radiant cooling plate for space use comprises three or more odd-numbered radiant cooling plate panels 30. The central radiant cooling plate panel 30 is fixedly connected to the spacecraft body 10, providing a stable motion reference and force transmission path for the folding and unfolding of the entire assembly. During the launch phase in orbit, all radiant cooling plate panels 30 are stacked and folded together with the central radiant cooling plate panel 30 as the reference to form a composite structure. The radiant cooling plate panels 30 on the left and right sides are folded towards the sides of the central radiant cooling plate panel 30, respectively. During the orbital phase, all radiant cooling plate panels 30 unfold symmetrically and sequentially to both sides based on the central reference. After unfolding, the radiant cooling plate panels 30 on the left and right sides are symmetrically distributed with the centerline of the central radiant cooling plate panel 30 as the axis of symmetry, and all radiant cooling plate panels 30 remain coplanar. The unfolding angle between adjacent radiant cooling plate panels 30 is 180°±5°.

[0056] The retractable structure in non-operational state has significant launch adaptability: the stacked retractable form can greatly reduce the radial and axial space occupation of the components, strictly adapt to the limited envelope constraints of rocket launch, and avoid spatial interference with other spacecraft components; at the same time, the integrated structure after retraction, combined with the fixed connection between the central radiating cooling plate 30 and the spacecraft body 10, can effectively resist mechanical loads such as vibration and impact during the launch phase, and ensure the structural integrity of the radiating cooling plate 30 during transportation and launch.

[0057] The deployed structure in the working state is optimized in terms of both heat dissipation efficiency and structural stability. On the one hand, the deployment of three or more odd-numbered radiant cooling plates 30 significantly increases the total radiation area of ​​the flexible radiant film, forming a heat dissipation surface far exceeding that of the spacecraft body 10. This meets the waste heat dissipation requirements of high-power payloads (such as space computing equipment) and solves the problem of insufficient heat dissipation area of ​​traditional single radiant cooling plates. On the other hand, the symmetrical distribution configuration ensures that the center of gravity of the overall structure after deployment is consistent with the center of gravity of the spacecraft body 10, avoiding on-orbit attitude disturbances caused by center of gravity shift. Furthermore, the microgravity, solar radiation pressure, and other space environment loads borne by each radiant cooling plate 30 can be evenly distributed, reducing local stress concentration. In addition, the basically coplanar design ensures that the flexible radiant film of all radiant cooling plates 30 can face the cold black space, avoiding radiation surface obstruction or heat dissipation direction shift caused by angle deviation. The deployment angle accuracy of 180°±5° can match the working angle requirements of the deployment hinges and rotating water-passing joints between adjacent plates, avoiding component jamming or sealing failure, and ensuring the reliability of the fluid circuit and structural connection.

[0058] It is worth noting that the layout of the odd number of radiant cooling plates 30 forms a stable symmetrical mechanical configuration: it avoids the configuration uncertainty that may occur during the unfolding process in the layout of even number of plates, and can flexibly adapt to the heat dissipation requirements of different power loads by increasing or decreasing the number of radiant cooling plates 30 (such as 3 plates, 5 plates, etc.), thus providing a basis for system expansion.

[0059] In summary, the embodiments of the present invention, through the synergistic design of the above features, achieve comprehensive optimization in terms of adapting to rocket launch envelope, ensuring on-orbit structural stability, optimizing heat dissipation efficiency, improving component adaptability, and reserving system expansion space, thereby meeting the core performance requirements of flexible radiant cooling plates for space applications.

[0060] In one embodiment, see Figure 5 As shown, adjacent radiant cooling plates are connected by a deployable hinge 34. The deployable hinge 34 is installed at the mating edge of the adjacent radiant cooling plates and includes a hinge body, a locking mechanism, and a limit switch, all mechanically assembled as a whole. The hinge body contains a built-in elastic torsion spring, which stores elastic potential energy through pre-deformation to provide the deploying driving force when the radiant cooling plate unfolds. The hinge body consists of a first connecting arm 341, a second connecting arm 342, the elastic torsion spring, and a hinge shaft 343. The first connecting arm 341 is fixed to the side of the frame of one radiant cooling plate, and the second connecting arm 342 is fixed to the corresponding side of the frame of an adjacent radiant cooling plate. The two are connected by the hinge shaft 343, which provides the center of relative rotation for the two connecting arms during unfolding. The elastic torsion spring is sleeved on the hinge shaft, and its two lever arms act on the two connecting arms respectively.

[0061] When the cooling plate is in the retracted state, the torsion spring is in a pre-tensioned state, storing elastic potential energy. When the cooling plate is deployed in orbit, the torsion spring releases the stored potential energy, driving the two connecting arms to rotate the individual cooling plates in the deployment direction. The deployment torque provided by this elastic torsion spring provides an independent power source for the deployment action between adjacent plates, without relying on the onboard power system, reducing the risk of deployment failure due to external power failure.

[0062] The locking mechanism's locking tongue is located on one of the connecting arms or its linked parts, while the locking buckle is located on the other connecting arm or its linked parts, for rigid fixation of the single panel after it is unfolded. When the two connecting arms rotate to the unfolding endpoint (e.g., 180°), the locking tongue automatically springs into the locking buckle under spring force or the action of the mechanism, achieving rigid mechanical locking. This locking mechanism provides structural connection for adjacent single panels after unfolding, resisting the effects of environmental factors such as on-track micro-vibration and thermal deformation, and helps maintain the stability of the working configuration.

[0063] Limit switches (or travel switches) are mounted on the bottom of the bolt or latch in the form of contacts or buttons to provide feedback on the locking status. When the locking mechanism achieves rigid mechanical locking, that is, when the bolt is fully inserted into the latch and locked, the limit switch is triggered simultaneously to generate a telemetry signal indicating that the bolt has been fully extended, thus confirming that the extension action was successfully performed.

[0064] The unfolding hinge 34 operates according to the following logic: When the cooling plate is in the retracted state, the elastic torsion spring undergoes elastic deformation and stores elastic potential energy; during the on-rail unfolding stage, when a single cooling plate unfolds, the elastic potential energy stored in the elastic torsion spring is released, providing unfolding driving force for adjacent cooling plates, while the hinge shaft 343 provides a stable relative rotation center for the plates; when the two connecting arms rotate to a working angle of 180°±5°, the locking tongue automatically springs into the latch under the spring force or the linkage of the mechanism, achieving rigid mechanical locking; after the locking tongue is fully engaged in the latch, the limit switch is triggered synchronously, and a telemetry signal is generated through contact closure to confirm that the unfolding is in place.

[0065] This integrated design brings multiple technical benefits: the hinge body has a built-in elastic torsion spring that can autonomously provide the deployment driving force, eliminating the need for additional drive devices such as motors and cylinders, thus reducing system weight, volume, and energy consumption, and meeting the lightweight and low-power design requirements of spacecraft; the rigid locking structure can resist the influence of environmental factors such as on-orbit micro-vibration and thermal deformation, fixing the relative position of adjacent single plates, avoiding angular deviation, and ensuring that all single plates maintain a basically coplanar heat dissipation attitude; the status feedback function of the limit switch allows the spacecraft control system to determine in real time whether the cooling plate is fully deployed and locked, promptly detecting anomalies such as unlocking or partial locking, reducing the risk of structural interference or impaired heat dissipation; the integrated assembly of the hinge body, locking mechanism, and limit switch is compact and highly integrated, simplifying the assembly process of inter-plate connections, and the three form a complete closed loop of "drive-lock-confirmation", ensuring orderly and controllable deployment actions and improving the reliability of the deployment process.

[0066] In summary, the embodiments of the present invention integrate the driving function, locking function and status confirmation function into a single design, thereby achieving functional integration and collaborative operation. This simplifies the structural design and assembly process of the unfolding hinge, while ensuring the stability, controllability and on-orbit reliability of the unfolding process of the cooling plate, and fully adapts to the usage requirements of the space environment.

[0067] In one embodiment, see Figure 6 and Figure 7 As shown, the main inlet pipe 38 and the main return pipe 39 between adjacent cooling plates are connected by a combination of independent rotating water-passing joints 35 and metal hoses 36. Specifically, the main inlet pipe 38 of adjacent plates is connected by a rotating water-passing joint 35, with a metal hose 36 connected to each end of the joint. Similarly, the main return pipe 39 of adjacent plates is connected by another rotating water-passing joint 35, with a metal hose 36 connected to each end of this joint. The metal hoses 36 are fixed to the frame by bundling to ensure the stability of the flexible piping installation. Depending on the connection target, the rotating water-passing joints 35 can be divided into an inlet rotating water-passing joint adapted for the inlet pipe and a return rotating water-passing joint adapted for the return pipe.

[0068] In terms of specific connection structure, the first pipe joint 314 on the upper side of the rotating water-passing joint 35 is fixed to the frame of the left-side radiant cooling plate, and the second pipe joint 327 on the lower side is fixed to the frame of the right-side radiant cooling plate. The metal hose 36 is connected between the rotating water-passing joint 35 and the inlet main line 38 (or return main line 39) to form a complete fluid passage. The working fluid flows out from the inlet main line 38 (or return main line 39) of one side plate, flows through the metal hose 36, the rotating water-passing joint 35, and the metal hose 36 on the other side in sequence, and finally enters the inlet main line 38 (or return main line 39) of the adjacent plate.

[0069] The functional synergy of this combined structure is reflected in the following aspects: the rotating water-passing joint 35 ensures fluid sealing during relative rotation, preventing working fluid leakage; the metal hose 36, with its inherent flexibility, compensates for installation errors and multi-degree-of-freedom displacement caused by thermal deformation, reducing assembly stress and vibration transmission at pipe connection points. Together, they can precisely adapt to the relative rotational movement of the cooling plate from folding to unfolding (e.g., from a retracted state to a working angle of 180°±5°) and during on-orbit angle adjustments, avoiding pipe pulling or twisting caused by rigid connections, ensuring that the fluid channels of the inlet main pipeline 38 and the return main pipeline 39 remain connected without interrupting the working fluid circulation. Simultaneously, the two independent "rotating water-passing joint 35 + metal hose 36" structures respectively adapt to the inlet and return circuits, preventing single-path failures from affecting the entire fluid system and ensuring stable heat dissipation. Furthermore, this combination possesses vibration resistance and resistance to alternating high and low temperatures, maintaining connection reliability in both the mechanical environment during launch and the on-orbit space environment. It will not leak due to vibration or fail due to temperature changes, ensuring long-term stable operation of the fluid circuit.

[0070] In summary, the embodiments of the present invention construct a dedicated rotating liquid-passing mechanism adapted to multi-plate deployment systems by combining a rotating water-passing joint with a metal hose. This not only solves the pipeline adaptation problem when adjacent single plates move relative to each other, but also ensures the reliability of fluid communication and the adaptability of the structure to the spatial environment, providing fluid transmission support for the stable realization of the heat dissipation function of multi-plate radiated cooling plates.

[0071] In one embodiment, see Figures 8-12 As shown, the rotating water-passing joint 35 includes an outer tube 310, an inner tube 320, and a locking device. Both the outer tube 310 and the inner tube 320 are stainless steel tubes. When the outer tube 310 and the inner tube 320 are fixedly connected to two adjacent cooling plates, the flow channel 313 of the outer tube 310 and the inner wall of the inner tube 320 form a passage for fluid to flow between the cooling plates. When the cooling plates are unfolded from the folded state, the inner tube 320 and the outer tube 310 can rotate relative to each other to avoid damage to the connecting pipes and realize the cooling of the fluid by the multi-radial cooling plates.

[0072] The outer tube 310 is a circular tube structure with a flow channel 313 inside for fluid to flow through. The axis of the flow channel 313 coincides with the axis of the outer tube 310 itself, and the flow channel 313 is located at the first end 311 of the outer tube. The inner diameter of the outer tube 310 from the second end 312 of the outer tube to the flow channel 313 is larger than the inner diameter of the flow channel 313. The outer tube 310 is also provided with a first pipe joint 314 that communicates with the flow channel 313. The first pipe joint 314 may be provided with a connecting pipe port structure for connecting to the heat dissipation system pipe of one of the radiant cooling plates.

[0073] The inner tube 320 is rotatably connected to the inside of the outer tube 310. The first end 321 of the inner tube is provided with an insert tube 323, which can be inserted into the flow channel 313 and its axis coincides with the axis of the inner tube 320 itself. A sealing element 340 is provided between the outer wall of the insert tube 323 and the inner wall of the flow channel 313. In this embodiment, the outer wall of the insert tube 323 is provided with one or more first annular grooves 324. The sealing element 340 is installed in the first annular groove 324, or it can be sealed by packing or mechanical seal. The second end 322 of the inner tube is sleeved with a sheath 326. A second pipe joint 327 is connected to the sheath 326. The second pipe joint 327 can be provided with a connecting pipe structure for connecting to the heat dissipation system pipeline of another radiant cooling plate to realize the connection of different radiant cooling plate heat dissipation systems.

[0074] A bearing is installed between the inner tube 320 and the outer tube 310. In this embodiment, the bearing is a deep groove ball bearing, including a first bearing 351 and a second bearing 352. The first bearing 351 and the second bearing 352 are both fitted onto the outer wall of the inner tube 320, and a bushing 53 is provided between them. The bushing 353 is fitted onto the outer wall of the inner tube 320 and its two ends abut against the inner rings of the first bearing 351 and the second bearing 352, respectively. The first bearing 351 and the second bearing 352 can support the inner tube 320, so that the insertion tube 323 and the guide channel 313 remain coaxial, and at the same time reduce the resistance of the inner tube 320 to rotate relative to the outer tube 310, so as to avoid the cold plate from not unfolding smoothly. The first end 321 of the inner tube is provided with a shoulder 325, which cooperates with the inner ring of the first bearing 351 to achieve precise positioning of the first bearing 351 and prevent it from falling out of the inner tube 320.

[0075] The locking device is used to rotatably lock the inner tube 320 to the outer tube 310, preventing the insertion tube 323 from disengaging from the guide channel 313. It includes a shaft retaining ring 332 and a hole retaining ring 331. The outer wall of the inner tube 320 is provided with a second annular groove 328. The shaft retaining ring 332 is located in the second annular groove 328, outside the second bearing 352, and limits its inner ring. The inner wall of the outer tube 310 is provided with a third annular groove 315. The hole retaining ring 331 is located in the third annular groove 315, outside the second bearing 352, and limits its outer ring. After installation, the second annular groove 328 and the third annular groove 315 are aligned. Alternatively, the locking device can be replaced by a thin nut, which requires corresponding threaded structures on the inner tube 320 and the outer tube 310 to cooperate with the thin nut.

[0076] The assembly steps of the rotating water-passing joint are as follows: First, the first bearing 351, bushing 353, and second bearing 352 are sequentially fitted onto the outer wall of the inner tube 320, so that the inner ring of the first bearing 351 abuts against the shoulder 325. Then, the shaft retaining ring 332 is installed into the second annular groove 328 to fix the second bearing 352 to the inner tube 320. The sealing element 340 (O-ring) is installed into the first annular groove 324. Then, the inner tube 320 is inserted into the outer tube 310, so that the insertion tube 323 is inserted into the guide channel 313. The hole retaining ring 331 is installed into the third annular groove 315 to fix the outer tube 310 to the outer ring of the second bearing 352. Finally, the sheath 326 is connected to the inner tube 320 by means of threaded connection or bonding, and the second pipe joint 327 is connected to the sheath 326, and the first pipe joint 314 is connected to the outer tube 310 to complete the assembly.

[0077] In use, the outer tube 310 is connected to the pipeline of one radiant cooling plate through the first pipe connector 314, and the inner tube 320 is connected to the pipeline of another radiant cooling plate through the second pipe connector 327, so that the heat dissipation system pipelines between different radiant cooling plates can be connected.

[0078] In summary, this rotating water-passing joint, through the rotatable core structure of the outer and inner pipes, combined with the leak-proof design of the sealing components, the smooth rotational support of the bearing assembly (first bearing 351, second bearing 352, bushing 353), and the structural fixing function of the locking device, not only solves the problem of easy damage to the pipeline during the folding and unfolding of multiple radiated cooling plates, but also achieves reliable fluid transmission when adjacent radiated cooling plates rotate relative to each other, ensuring long-term working stability in complex spatial environments.

[0079] In one embodiment, see Figure 5 and Figure 6 The end of the metal hose 36 is connected to the inlet main line 38 or the return main line 39 within the cooling plate via a plunger-type connector 40 with double O-ring seals. The plunger-type connector 40 includes a plunger adapted to the main line interface and a perforated connector. The plunger is fixed to the end of the metal hose 36 and inserted into the perforated connector corresponding to the inlet main line 38 or the return main line 39 interface. Two O-rings are axially spaced between the plunger and the perforated connector, forming a double radial sealing interface.

[0080] From the perspective of sealing reliability, the dual radial sealing interface effectively reduces the risk of working fluid leakage compared to a single sealing structure. Even if one O-ring fails, the other O-ring can still maintain the sealing function, providing sealing redundancy. This allows it to adapt to complex environments such as vibrations during spacecraft launch and alternating high and low temperatures in orbit, ensuring pressure stability and working fluid loss control in the fluid circuit. Regarding connection stability, the rigid fit structure of the plunger and orifice connector provides a tight and precise connection, resisting mechanical disturbances such as launch vibrations and micro-vibrations in orbit, preventing loosening or displacement of the connection. Simultaneously, this structure provides a stable transition between the metal hose 36 and the inlet main pipeline 38 and the return main pipeline 39, reducing stress concentration at pipeline connections and improving long-term operational reliability.

[0081] Furthermore, the plunger-type connector 40 features a simple structure, requiring no complex tools during assembly, facilitating assembly and maintenance during ground testing. Its components, such as the plunger, orifice connector, and O-ring, are highly versatile, making it easy to replace seals or connector parts, thus meeting the practical requirements of spacecraft equipment. Simultaneously, this connection structure can accommodate the interface requirements of both the inlet main line 38 and the return main line 39. Two independent connection and sealing structures serve the dual loops respectively, preventing a single-path seal failure from affecting the entire fluid system, ensuring continuous transmission of the working fluid between the individual boards, and maintaining stable heat dissipation.

[0082] In summary, the embodiments of the present invention, by employing a plunger-type connector 40, combined with a double radial sealing design of double O-rings and a rigid fit structure of plunger-orifice connector, not only improve the sealing reliability and mechanical stability of the connection between the metal hose 36 and the main pipeline, but also provide convenience for system ground integration, testing and subsequent maintenance, and adapt to the fluid loop connection requirements of flexible radiant cooling plates for space applications.

[0083] The above are merely preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention. For those skilled in the art, the present invention can have various modifications and variations. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A flexible radiating panel for space use, characterized by The application relates to a space flexible radiative cold plate, which comprises at least one radiative cold plate single plate. The radiative cold plate single plate comprises a frame, rigid fluid pipes and a flexible radiative film. The rigid fluid pipes are fixed to the frame and cooperatively form an integral support structure with the frame; the rigid fluid pipes comprise a liquid inlet main pipe, a liquid return main pipe and a plurality of branch pipes; the liquid inlet main pipe and the liquid return main pipe are oppositely arranged at two side edges of the frame; the plurality of branch pipes are parallelly and spacedly arranged between the liquid inlet main pipe and the liquid return main pipe, and the two ends of the plurality of branch pipes are communicated with the liquid inlet main pipe and the liquid return main pipe to form a parallel flow channel structure. The flexible radiative film is arranged on the rigid fluid pipes and is used for radiating heat carried by working medium flowing through the rigid fluid pipes to a space environment through a heat radiation mode. The radiative cold plate single plate is provided with a liquid inlet interface and a liquid return interface; the liquid inlet main pipe is connected to the liquid inlet interface for introducing working medium; and the liquid return main pipe is connected to the liquid return interface for leading out working medium.

2. The flexible radiation cold plate for space use according to claim 1, characterized by The liquid return main pipe is arranged at a side edge of the corresponding frame and comprises two first parallel sections and two second parallel sections which are parallelly and spacedly arranged in the same direction, a bend pipe section and a vertical section. The bend pipe section coaxially connects the top end of the first parallel section and the top end of the second parallel section; and the vertical section vertically penetrates the bottom end of the second parallel section and is connected to the liquid return interface. The ends of the plurality of branch pipes away from the liquid inlet main pipe are all vertically communicated to the first parallel section of the liquid return main pipe close to one side of the branch pipes; the first parallel section is used for collecting working medium flowing through the branch pipes, conducting the working medium to the second parallel section through the bend pipe section, conducting the working medium to the vertical section from the second parallel section, and finally forming a working medium return channel through the liquid return interface. The flexible radiative film is a graphene-based composite film which is formed by compounding graphene and polyimide.

3. The flexible radiation cold plate for space use according to claim 1, characterized by The flexible radiative film is sprayed with a functional coating for reducing solar heat absorption on a sun-facing surface.

4. The flexible radiation cold plate for space use according to claim 1, characterized by The flexible radiative film is bonded to the surface of the rigid fluid pipes through a low-thermal-resistance adhesive.

5. The flexible radiant panel for a space as defined in claim 1, wherein A heat conduction enhancement layer is arranged between the flexible radiative film and the rigid fluid pipes, and the heat conduction enhancement layer has a micro-nano groove structure.

6. The flexible radiant panel for a space as defined in claim 1, wherein The space flexible radiative cold plate comprises three or more odd-numbered radiative cold plate single plates; and a central radiative cold plate single plate is used for fixedly connecting with a spacecraft body.

7. The flexible radiant panel for a space as defined in claim 1, wherein In a non-working state, all the radiative cold plate single plates are stacked and folded to form a folded structure; and left and right radiative cold plate single plates are respectively folded to two sides of the central radiative cold plate single plate. In a working state, all the radiative cold plate single plates are unfolded; after being unfolded, the left and right radiative cold plate single plates are symmetrically distributed with the center line of the central radiative cold plate single plate as a symmetric axis; and all the radiative cold plate single plates are kept coplanar. Adjacent radiative cold plate single plates are connected through unfolding hinges; and the unfolding hinges comprise a hinge body, a locking mechanism and a travel switch which are mechanically assembled into an integral whole.

8. The flexible radiation cold plate for space use according to claim 7, characterized by The hinge body is internally provided with an elastic torsion spring which stores elastic potential energy through pre-deformation and is used for providing an unfolding driving force when the radiative cold plate single plates are unfolded. ​ The locking mechanism is used for realizing rigid locking through mechanical cooperation of the lock tongue and the lock catch when the hinge body drives the radiative plate single plate to unfold to a working angle; The travel switch is a mechanical contact switch, which is used for generating a locking state confirmation signal through contact closure after the lock tongue of the locking mechanism is completely clamped into the lock catch.

9. The flexible radiation cold plate for space use according to claim 7, characterized by, Liquid inlet main pipelines between adjacent radiative plate single plates are communicated through a rotating water joint, two ends of the rotating water joint are respectively connected with a metal hose; liquid return main pipelines between adjacent radiative plate single plates are communicated through another rotating water joint, two ends of the rotating water joint are also respectively connected with a metal hose; The combination of the rotating water joint and the metal hose is used for adapting relative movement of adjacent radiative plate single plates when the radiative plate single plates are folded or unfolded, and ensuring continuity of working medium flow.

10. The flexible radiation cold plate for space use according to claim 9, characterized by The rotating water joint comprises an outer pipe, an inner pipe, a sealing element, a first bearing, a second bearing, a bushing, a shaft clamp spring, a hole clamp spring, a first pipe joint, a sheath and a second pipe joint; wherein, The outer pipe is internally provided with a flow guide channel, an axis of the flow guide channel coincides with an axis of the outer pipe, the first pipe joint in communication with the flow guide channel is fixed on the outer pipe, and the first pipe joint is used for connecting the main pipeline of the radiative plate single plate on one side; The inner pipe is rotatably arranged in the outer pipe, a first end of the inner pipe is provided with a spigot inserted into the flow guide channel, a second end of the inner pipe is sleeved with the sheath, the sheath is fixed with the second pipe joint, the second pipe joint is used for connecting the main pipeline of the radiative plate single plate on the other side, and the flow guide channel and an inner wall of the inner pipe jointly form a fluid passage; The sealing element is arranged in a first annular groove of an outer wall of the spigot and clamped between the outer wall of the spigot and the inner wall of the flow guide channel, so as to realize radial dynamic sealing; The first bearing and the second bearing are sequentially sleeved on an outer wall of the inner pipe, the bushing is sleeved on the outer wall of the inner pipe and clamped between the first bearing and an inner ring of the second bearing, and a shaft shoulder of the first end of the inner pipe abuts against the inner ring of the first bearing to realize positioning; The shaft clamp spring is arranged in a second annular groove of the outer wall of the inner pipe and abuts against an inner ring of the second bearing, and the hole clamp spring is arranged in a third annular groove of an inner wall of the outer pipe and abuts against an outer ring of the second bearing; the shaft clamp spring and the hole clamp spring jointly form a locking device to prevent the spigot of the inner pipe from being separated from the flow guide channel of the outer pipe, and do not affect relative rotation of the inner pipe and the outer pipe.

11. The flexible radiation cold plate for space use according to claim 9, characterized by An end of the metal hose and a liquid inlet main pipeline interface or a liquid return main pipeline interface in the radiative plate single plate are connected through a plunger type joint sealed by double O rings; The plunger type joint comprises a plunger matched with the main pipeline interface and a hole type joint, the plunger is fixed on the end of the metal hose and inserted into the hole type joint of the main pipeline interface, two O rings are arranged between the plunger and the hole type joint in an axial direction to form double radial sealing interfaces.

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