Radiation cooling plate assembly applied to space pump drive fluid loop system

Abstract

The invention discloses a radiant cooling plate assembly applied to a space pump drive fluid loop system. The assembly comprises three or more odd number of radiant cooling plate single plates, and the central radiant cooling plate single plate is fixedly connected with a spacecraft body; each single plate comprises a frame, a rigid fluid pipeline and a flexible radiation film, the rigid fluid pipeline is composed of a liquid inlet main pipeline, a liquid return main pipeline and a plurality of parallel branch pipelines and cooperates with the frame to form a supporting structure, and the flexible radiation film covers the pipelines and is used for radiation heat dissipation. In the launching stage, all the single plates are stacked and folded and locked to a spacecraft body through a pressing and releasing mechanism. In the on-orbit stage, after the pressing and releasing mechanism is unlocked, the single plates are unfolded in different time sequences through the on-orbit unfolding mechanism, and finally the single plates are symmetrically distributed with the center line of the central single plate as the symmetry axis and are kept coplanar. Through the design of the symmetrical configuration, the rigid-flexible composite structure and the parallel flow channels, the envelope adaptability of the launching stage and the heat dissipation efficiency and the structural stability of the on-orbit stage are considered, and the heat management requirement of the high-power spacecraft is met.

Description

Technical Field

[0001] This invention relates to the field of spacecraft thermal control technology, and more specifically to a radiant cooling plate assembly applied to a space pump-driven fluid loop system. Background Technology

[0002] With the continuous increase in spacecraft power levels, the heat load generated by high-power equipment operating in orbit has increased significantly, creating an urgent need for efficient and reliable thermal management systems. Space pump-driven fluid loop systems, as a mainstream technical solution to address this challenge, use a circulating working fluid to transfer waste heat from equipment to a radiating heat dissipation surface, ultimately dissipating it into space through thermal radiation. The system's heat dissipation capacity depends primarily on the area and structural efficiency of the radiating heat dissipation surface.

[0003] Traditional fixed radiating plates are limited by the launch envelope size of spacecraft, and their radiating area is insufficient to meet the heat dissipation requirements of kilowatt-level or higher heat loads. To address this, deployable radiating plate technology has emerged, which deploys in orbit to obtain a larger radiating area. However, this technology still faces a series of challenges in engineering applications: at the structural level, lightweight design, high thermal conductivity, and deployment reliability must be balanced; efficient thermal coupling and coordinated stress distribution between rigid structures and flexible heat dissipation surfaces are design challenges. Regarding multi-plate deployment configuration control, issues such as compact retraction during launch, reliable on-orbit deployment and stable locking in a time-sequential manner, and avoiding interference with spacecraft attitude during deployment must be addressed. At the fluid cooling level, the flow channel design needs to be optimized to avoid localized heat accumulation, and the flow channel layout must be coordinated and compatible with the deployment mechanism.

[0004] In response to the current state of the technology, it is necessary to develop a new type of radiant cooling plate assembly that can be folded up within a limited launch space, reliably deployed in orbit into a large-area, highly stable heat dissipation surface, and possess efficient and uniform heat dissipation performance to meet the thermal management requirements of next-generation high-power spacecraft. Summary of the Invention

[0005] The purpose of this invention is to provide a radiant cooling plate assembly for use in a space pump-driven fluid loop system, which aims to meet the thermal management requirements of high-power spacecraft by optimizing the structural design and deployment mechanism.

[0006] To achieve the above objectives, the present invention adopts the following technical solution: A radiant cooling plate assembly for use in a space pump-driven fluid loop system, the radiant cooling plate assembly comprising at least one radiant cooling plate; Each of the aforementioned radiant cooling plates includes a frame, rigid fluid piping, 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 to the space environment through thermal radiation. During the launch phase, all the single-layer cooling plates are stacked and retracted to form a composite structure, which is then pressed and locked to the spacecraft body by a pressing and releasing mechanism. During the on-orbit phase, after receiving an instruction, the clamping release mechanism releases the lock on the stacked structure. All the radiated cooling plates are then sequentially deployed and locked into the working configuration by the on-orbit deployment mechanism, and all the radiated cooling plates remain coplanar after deployment.

[0007] Compared with the prior art, the radiant cooling plate assembly proposed in this invention has the following beneficial effects: 1) Flexible configuration to adapt to different needs: The design adopts at least one radiant cooling plate. A single plate can be directly adapted to the heat dissipation requirements of small and medium power loads. When multiple plates are combined, they can be stacked and deployed in sequence to adapt to high power heat dissipation scenarios, providing a foundation for thermal management applications of spacecraft of different power levels.

[0008] 2) Balancing structural reliability and thermal efficiency: The rigid fluid pipeline and frame work together to form an overall support structure, which can ensure the structural integrity of the components under launch vibration and on-orbit thermal cycling environment; the flexible radiation film covers the rigid pipeline, forming a tight thermal coupling path, which improves the efficiency of heat dissipation from the working fluid to the space environment while achieving lightweight design.

[0009] 3) Improved heat dissipation uniformity: The rigid fluid pipeline adopts a configuration of main inlet pipeline, main return pipeline and multiple parallel branch pipelines, so that the working fluid flows through similar paths in each branch pipeline, reducing the difference in flow resistance between different pipelines, avoiding local heat accumulation, and effectively improving the temperature uniformity of the heat dissipation surface.

[0010] 4) Launch and on-orbit adaptation: During the launch phase, all the single-plate cooling plates are stacked and retracted to form a compact stacked structure, which, together with the clamping and release mechanism, achieves reliable constraint and adapts to the requirements of the launch envelope; during the on-orbit phase, the clamping and release mechanism unlocks after receiving the command, and all single plates are deployed in sequence through the on-orbit deployment mechanism and locked to the working configuration, ensuring a reliable transition from the retracted state to the working state.

[0011] 5) Good scalability: Based on the modular design of at least one radiant cooling plate, the total radiation area can be flexibly adjusted by increasing or decreasing the number of plates. Without major changes to the core structure such as the frame and pipeline, it can be adapted to the heat dissipation requirements of different spacecraft, enhancing the application adaptability of the component.

[0012] In summary, this invention provides specific technical guarantees for achieving the dual requirements of reliable retraction of the radiated cooling plate assembly during launch and stable deployment during on-orbit phase through the coordinated support structure of the frame and rigid fluid pipeline, as well as the synergistic effect of the compression release mechanism and the on-orbit deployment mechanism. It also forms an integrated solution in terms of configuration stability, thermal management efficiency, and deployment reliability. Attached Figure Description

[0013] 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 the structure of the single-layer cooling plate proposed in this invention; Figure 3 This is a schematic diagram of the connection structure between the radiation cooling plate assembly and the spacecraft body proposed in this invention; Figure 4 This is a schematic diagram of the unfolding process of the radiant cooling plate assembly proposed in this invention; Figure 5 This is a schematic diagram of the basic components of the motor assembly proposed in this invention; Figure 6 This is a schematic diagram of the internal interface between adjacent radiant cooling plates proposed in this invention; Figure 7 This is a partial view of the internal interface and fluid circuit between adjacent radiant cooling plates proposed in this invention; Figure 8 This is a schematic diagram of the fluid circuit between adjacent radiant cooling plates proposed in this invention; Figure 9 This is a schematic diagram of the rotating water-passing joint proposed in this invention; Figure 10 for Figure 9 A cross-sectional view; Figure 11 for Figure 9 A schematic diagram of the explosion of a rotating water-transfer joint; Figure 12 A cross-sectional view of the outer tube of the rotating water-passing joint; Figure 13 This is a cross-sectional schematic diagram of the inner tube of the rotating water-passing joint.

[0014] 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; 37. Rotary hinge; 38. Inlet main pipeline; 39. Return main pipeline; 391. First parallel section; 392. Bend section; 393. Second parallel section; 394. Vertical section; 40. Piston connector; 41. Motor assembly; 42. Hose fastener; 51. Inlet port; 52. Return port. Detailed Implementation

[0015] 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.

[0016] 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.

[0017] 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".

[0018] In space pump-driven fluid loop systems, radiating cooling plates play a crucial role in radiating and dissipating the heat carried by the circulating working fluid into the cold black space. With the increasing power levels of spacecraft, the demand for radiating cooling plate area has significantly increased, making deployable multi-plate configurations an inevitable choice. However, existing technologies still face challenges such as the stability of the deployed configuration and its compatibility with spacecraft attitude control, the efficient synergy between rigid support structures and flexible heat dissipation materials, and the impact of flow channel layout on heat dissipation uniformity. More comprehensive solutions are needed for these issues.

[0019] Based on the above background, the design concept of this invention focuses on constructing a systematic solution. This solution adopts an odd-numbered block symmetrical configuration with a central single plate as a fixed reference, aiming to control the overall mass distribution after deployment from the source and reduce interference with the spacecraft's attitude. By integrating the rigid fluid pipelines with the frame, a main structure with both load-bearing and heat-conducting functions is formed. This is further combined with a flexible radiating membrane to expand the heat dissipation area, achieving a balance between structural reliability and thermal performance. In terms of mechanism function, the synergistic effect of the compression release and on-orbit deployment mechanisms ensures that the components can reliably retract to fit the payload envelope during launch, and can sequentially deploy and stably lock into their working position during on-orbit deployment. Simultaneously, a flow channel configuration using main inlet and return pipelines combined with multiple parallel branch pipelines aims to optimize the working fluid flow path and improve the temperature uniformity of the heat dissipation surface.

[0020] The present invention will now be described in detail with reference to the accompanying drawings.

[0021] See Figures 1-4 The present invention proposes a radiated cooling plate assembly for use in a space pump-driven fluid circuit system, comprising at least one radiated cooling plate 30.

[0022] Each cooling plate 30 includes a frame 32, rigid fluid pipelines, and a flexible radiant membrane 33. The rigid fluid pipelines are fixed to the frame 32 and work together with the frame 32 to form an integral support structure. The rigid fluid pipelines include an inlet main pipeline 38, a return main pipeline 39, and multiple branch pipelines 31. The inlet main pipeline 38 and the return main pipeline 39 are arranged opposite each other on both sides of the frame 32. The multiple branch pipelines 31 are arranged in parallel and spaced between the inlet main pipeline 38 and the return main pipeline 39, and the two ends of the multiple branch pipelines 31 are respectively connected to the inlet main pipeline 38 and the return main pipeline 39 to form a parallel flow channel configuration. The flexible radiant membrane 33 covers the rigid fluid pipelines and is used to radiate the heat carried by the working fluid flowing through the rigid fluid pipelines to the space environment through thermal radiation.

[0023] During the launch phase, all 30 layers of the radiant cooling plates are stacked together to form a composite structure, which is then pressed and locked to the spacecraft body 10 by a pressing and releasing mechanism.

[0024] During the on-orbit phase, after receiving the command, the clamping release mechanism releases the lock on the stacked structure. All the radiated cooling plate 30 is deployed in sequence through the on-orbit deployment mechanism (including the deployment hinge 34) and locked into the working configuration. After deployment, all the radiated cooling plate 30 remain coplanar.

[0025] The design improvements of this invention are mainly reflected in four aspects: configuration, structure, flow channel, and mechanism. At least one radiant cooling plate 30 is used, and the number of plates can be flexibly configured according to heat dissipation requirements. Structurally, each plate adopts an integral support structure formed by a frame 32 and rigid fluid pipelines, with a flexible radiant film 33 covering the surface. The flow channel design adopts a parallel flow channel configuration where the inlet main pipeline 38 and the return main pipeline 39 are arranged opposite each other on both sides of the frame 32, connected by multiple parallel branch pipelines 31 in the middle. The mechanism design achieves stacked and fixed assembly during the launch phase through a clamping and releasing mechanism, and achieves time-sequential deployment and coplanar locking during the on-orbit phase through an on-orbit deployment mechanism.

[0026] like Figure 2 As shown, each cooling plate 30 consists 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. Specifically, they include a main inlet pipeline 38, a main return pipeline 39, and multiple branch pipelines 31. The main inlet pipeline 38 and the main return pipeline 39 are arranged opposite each other on both sides of the frame 32, and the multiple branch pipelines 31 are distributed in parallel at intervals, with their ends connected to the main pipelines to form parallel flow channels. The flexible radiant membrane 33 covers the surface of the rigid fluid pipelines and is used to transfer the heat of the working fluid flowing through the pipelines to the space environment by thermal radiation.

[0027] In the flow channel design, the working fluid is diverted from the main inlet pipe 38 to each branch pipe 31. During the flow, it radiates heat outward through the flexible radiant membrane 33, and finally converges to the main return pipe 39 to complete the circulation. This parallel flow channel expands the heat dissipation area through multiple branch pipes 31, achieving uniform distribution of the working fluid, which helps to reduce the temperature difference between the inlet and outlet and promotes a balanced temperature field on the plate surface. It also has flow channel redundancy characteristics, maintaining some heat dissipation capacity even when a single pipe is partially blocked. The parallel and spaced branch pipes 31 shorten the flow path of the working fluid, reduce flow channel turning losses, thereby reducing the overall flow resistance of the system and the load requirements of the drive pump.

[0028] 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 utilizes carbon fiber composite materials or a titanium alloy honeycomb sandwich structure, achieving lightweighting of the plate while ensuring structural performance. This design ensures the structural integrity of the plate during launch and maintains the stability of the heat dissipation surface during on-orbit operation. Simultaneously, it precisely positions the spacing and routing of multiple branch pipes 31, guaranteeing uniform distributing of the working fluid and a balanced temperature field. The resulting support structure maintains integrity in vacuum and alternating high and low temperature environments, adapting to the load requirements of mechanical vibrations during launch and on-orbit attitude adjustments.

[0029] The combination of the flexible radiating membrane 33 and the rigid fluid piping further optimizes thermal management and lightweight characteristics. The flexible radiating membrane 33 tightly covers the surface of the rigid fluid piping, forming a low thermal resistance heat conduction path. Its high infrared emissivity efficiently converts the heat of the working fluid into infrared radiation, transferring it to the cold black space. Simultaneously, the flexible radiating membrane 33 is lighter than traditional rigid radiating panels. Combined with the structured distribution of the rigid fluid piping, it reduces the overall weight of a single panel while ensuring support strength, meeting the lightweight design requirements of spacecraft.

[0030] Modular design enhances system adaptability. Based on the single-board module design concept, a single radiant cooling plate (board 30) can adapt to the heat dissipation requirements of small and medium power loads, with a compact structure and convenient installation. When multiple boards are combined, they can be stacked and folded to adapt to the rocket launch envelope constraints, and unfolded 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.

[0031] like Figure 3 and Figure 4 As shown, during the launch phase, all the individual cooling plates 30 are compressed into a whole by the clamping and releasing mechanism, stacked and folded onto one side of the spacecraft body 10, forming a compact structure that meets the requirements of the launch envelope. During the on-orbit phase, the clamping and releasing mechanism first receives a command to release the lock on the stacked structure; then, the on-orbit deployment mechanism drives all the individual cooling plates to deploy in a time-sequential manner: first, it drives the overall assembly to rotate to the pre-deployment position, then releases the plates on both sides, and finally deploys all the individual cooling plates into the working configuration and maintains a coplanar state.

[0032] During launch, the stacked and retracted structure is reliably secured via a clamping and releasing mechanism, providing the component with structural stiffness to resist launch vibrations and overloads. During in-orbit deployment, the in-orbit deployment mechanism executes unlocking and deployment actions according to a preset sequence, ensuring a reliable transition from the retracted state to the operational configuration. This collaborative mechanism allows the component to adapt to both the envelope constraints of the launch phase and the operational configuration requirements of the in-orbit phase.

[0033] It should be noted that this embodiment focuses on describing the configuration state of the radiant cooling plate assembly under both launch and on-orbit conditions and its conversion process. The specific implementation of the clamping release mechanism and the on-orbit deployment mechanism can adopt a variety of technical approaches known in the art.

[0034] Based on the above design improvements, the present invention can achieve the following technical effects: 1) In terms of configuration flexibility, based on the design of at least one radiant cooling plate, a single plate can be directly adapted to the heat dissipation requirements of small and medium power loads. When multiple plates are combined, they can be stacked and deployed in sequence to adapt to high power scenarios, providing a flexible adaptation basis for the thermal management requirements of spacecraft of different power levels. 2) In terms of structural reliability, the collaborative support structure formed by the frame and rigid fluid pipeline provides the necessary structural stiffness for the components under launch vibration and on-orbit thermal cycling environment. At the same time, the flexible radiation film covering method achieves lightweight design while ensuring heat dissipation area and thermal coupling efficiency. 3) In terms of heat dissipation uniformity, the parallel flow channel configuration allows the working fluid to flow in parallel in multiple branch pipes, reducing the difference in flow paths between different pipes, avoiding local heat accumulation, and effectively improving the temperature distribution uniformity of the heat dissipation surface. 4) In terms of operational adaptability, through the coordinated action of the clamping and release mechanism and the on-orbit deployment mechanism, the components can be compactly folded and reliably constrained during the launch phase to meet the requirements of the launch vehicle envelope; during the on-orbit phase, the components can be deployed in sequence and locked in working configuration to ensure stable transition between the two operational conditions. 5) In terms of configuration scalability, based on the modular design concept of at least one radiant cooling plate, the total radiation area can be flexibly adjusted by increasing or decreasing the number of plates. It can adapt to different heat dissipation requirements without significantly modifying the core structure, thus significantly enhancing the application adaptability of the components.

[0035] In summary, this invention, through the system integration of a flexible configuration of at least one single plate, a rigid-flexible composite structure, a parallel flow channel design, and a collaborative deployment mechanism, forms a comprehensive technical solution in terms of configuration flexibility, structural reliability, thermal management efficiency, and on-orbit deployment adaptability, which can be adapted to the thermal management requirements of spacecraft with different power.

[0036] In one embodiment, see Figure 2The 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.

[0037] 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.

[0038] 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.

[0039] In one embodiment, the flexible radiation film is a graphene-based composite film, which is formed by combining graphene and polyimide.

[0040] 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.

[0041] 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.

[0042] 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.

[0043] 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.

[0044] 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.

[0045] 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.

[0046] 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.

[0047] 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.

[0048] 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.

[0049] 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.

[0050] 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.

[0051] 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.

[0052] 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.

[0053] 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.

[0054] 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.

[0055] 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.

[0056] 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.

[0057] 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.

[0058] 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.

[0059] 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.

[0060] 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.

[0061] 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.

[0062] 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.

[0063] In one embodiment, the clamping release mechanism employs a release nut, which includes a shape memory alloy puller, a release nut body, and an electrical connector, wherein the shape memory alloy puller has two parallel bridge wires. During launch, the shape memory alloy puller's pin is extended, locking the separation nut body in a locked state, thus pressing and locking the stacked and closed radiant cooling plate assembly to the spacecraft body. After orbiting, the electrical connector receives an electrical command, driving the shape memory alloy puller to retract its pin, releasing the separation nut body, and releasing the pressure constraint on the radiant cooling plate assembly.

[0064] During launch, the extension state of the shape memory alloy puller pin locks the separation nut body, providing stable clamping constraints for the stacked and retracted cooling plate assembly, helping the assembly resist the mechanical environment during launch. The pin retraction is achieved using the shape memory alloy phase change principle; this non-explosive unlocking method does not generate impact loads during operation, reducing potential impact on the cooling plate assembly and surrounding equipment. The shape memory alloy puller employs a dual-parallel bridge wire design, forming a dual command path. Even if one bridge wire fails, the other unlocking capability is retained, providing redundancy for on-orbit unlocking operations. Unlocking is triggered by receiving electrical commands via an electrical connector, achieving coordination with the spacecraft control system and meeting the remote control and precise timing requirements of on-orbit missions for unlocking actions. The locking and unlocking mechanism of the separation nut is adapted to the stacked and retracted assembly configuration, providing effective clamping constraints during launch and completely releasing the clamping force in orbit without interfering with subsequent deployment actions.

[0065] In summary, the clamping release mechanism of this invention, through the mechanical locking and electronic unlocking mechanism of the shape memory alloy puller, combined with the redundant design of dual parallel bridge wires, ensures the structural constraint reliability during the launch phase while achieving on-orbit shock-free unlocking and command control operability, providing effective technical support for the configuration conversion of the radiated cooling plate assembly.

[0066] In one embodiment, the on-orbit deployment mechanism includes a motor assembly, a constraint release pin, and a deployment hinge. The motor assembly is installed between the spacecraft body and the central radiant cooling plate and is used to drive the central radiant cooling plate, along with the two side plates, to perform an initial flip. The constraint release pin is used to release the connection constraint between adjacent radiant cooling plates after the initial flip is completed. The deployment hinge is connected between adjacent radiant cooling plates and, after the constraint release pin releases the connection constraint, drives the adjacent radiant cooling plates to deploy to the working configuration and lock them.

[0067] The motor assembly is installed between the spacecraft body and the central radiant cooling plate. It can provide stable power to drive the central radiant cooling plate and the two side plates to perform an initial overall rotation. It can precisely control the rotation angle and speed to ensure that the assembly smoothly transitions from the folded state to the ready-to-deploy position, creating suitable attitude conditions for the subsequent deployment between the plates.

[0068] The constraint release pin is installed between two adjacent radiated cooling plates. It releases the connection constraint between the radiated cooling plates after the motor assembly has completed its overall flipping but before the side plates unfold, allowing the left and right side plates to unfold under the action of the unfolding hinge. Its implementation is similar to the release nut of a clamping release mechanism.

[0069] The constraint release pins release the connection constraints between adjacent cooling plates only after the initial flip is completed, achieving an orderly connection between the overall flip and the release between plates. This avoids the connection constraints between plates affecting the flipping action during the initial flip, or premature release causing the plates to shake or collide, ensuring the smoothness of the unfolding process.

[0070] The unfolding hinge connects adjacent radiated cooling plate panels. After the constraint release pin releases the constraint, it can provide continuous unfolding driving force to push the adjacent panels to unfold accurately into the working configuration. It also has a locking function, which can fix the relative position of the panels after unfolding to the correct position, ensuring the coplanarity and symmetrical distribution of all radiated cooling plate panels and resisting load interference such as on-orbit micro-vibration.

[0071] The motor assembly, constraint release pin, and unfolding hinge each perform their respective functions and work together. The motor assembly is responsible for overall posture adjustment, the constraint release pin controls the timing of constraints between boards, and the unfolding hinge enables precise unfolding and locking between boards, forming a hierarchical unfolding logic of the whole and the parts, adapting to the unfolding needs of 3 or more odd-numbered single boards, and avoiding action conflicts during the unfolding of multiple boards.

[0072] The unfolding hinge connection does not affect the stacking and folding during the launch phase. It can be folded and folded together with the single board to meet the requirements of the carrier envelope. When unfolded in orbit, it can give full play to the driving and locking functions without occupying too much additional installation space, thus balancing structural compactness and functional integrity.

[0073] In summary, the on-orbit deployment mechanism of this invention achieves hierarchical control from overall initial flipping to local inter-plate deployment through the functional division and timing coordination of the motor assembly, constraint release pin, and deployment hinge. This ensures the orderliness of actions at each stage during deployment and provides stability assurance for the working configuration through the final mechanical locking mechanism, thus forming a deployment control scheme adapted to the characteristics of multi-plate assemblies.

[0074] In one embodiment, see Figure 3 and Figure 5 As shown, the motor assembly 41 includes a dual-winding stepper motor, a harmonic reducer, an encoder angle measuring assembly, a platform mounting flange, and a radiant cooling plate mounting flange. The dual-winding stepper motor provides power. The harmonic reducer is connected to the output shaft of the dual-winding stepper motor to reduce the rotational speed and increase the torque. The encoder angle measuring assembly is connected to the output end of the harmonic reducer to detect the rotational angle of the output shaft of the harmonic reducer. The platform mounting flange is used to fix the motor assembly to the spacecraft body. The radiant cooling plate mounting flange is used to fix and connect to the centrally located radiant cooling plate. The platform mounting flange, dual-winding stepper motor, harmonic reducer, encoder angle measuring assembly, and radiant cooling plate mounting flange are stacked and integrated sequentially along the same axis.

[0075] The motor assembly, as an independent drive module, is mechanically connected to the spacecraft body and the central radiant cooling plate via platform mounting flanges at both ends and radiant cooling plate mounting flanges, respectively, for torque transmission. The motor assembly contains two stepper motors with different functions: one is an SADM motor (Solar Array Drive Mechanism), used to drive the overall rotation of the radiant cooling plate assembly, adjusting its angle relative to the sun and space cooling source to optimize heat dissipation attitude; the other is a deployment motor, specifically used to drive the folding or unfolding of the radiant cooling plate itself. By providing torque to overcome the rotational hinge 37 and structural resistance, it enables the smooth unfolding of the radiant cooling plate assembly from the folded state to the working position.

[0076] The rotation range of the motor assembly is constrained by both electrical and mechanical limits on both sides, and the overall architecture adopts a "stepper motor + harmonic reducer + angle sensor" scheme. The stepper motor is responsible for outputting torque and features simple control and smooth operation; the harmonic reducer achieves torque amplification and speed reduction through a high reduction ratio, enabling a small motor to drive a large load; the angle sensor is used to detect the rotation angle in real time, working in conjunction with the loop controller to achieve closed-loop precise position control.

[0077] In practical implementation, the motor assembly uses a dual-winding stepper motor as the power source, in conjunction with a harmonic reducer to convert the high-speed, low-torque output into the low-speed, high-torque required to drive the cooling plate. The dual-winding design provides redundancy, ensuring operation can continue even if one winding fails. The low backlash characteristic of the harmonic reducer helps improve angle control accuracy, ensuring accurate positioning of the cooling plate within the 0–90° range.

[0078] Angle detection is achieved through an encoder angle measurement component, which directly monitors the rotation angle of the harmonic reducer's output shaft, providing position feedback for closed-loop control. Simultaneously, a temperature sensor is installed on the motor body to monitor the operating temperature in real time, providing a basis for thermal management control.

[0079] The functional components are stacked and integrated sequentially along the same axis to form a compact modular structure. The platform mounting flange ensures a reliable connection with the spacecraft body, while the radiant cooling plate mounting flange ensures a stable connection with the central radiant cooling plate. This integrated design satisfies both installation space constraints and ensures the coaxiality requirements of the transmission system.

[0080] In summary, the embodiments of the present invention achieve the following technical effects in terms of drive redundancy, torque adaptability, control accuracy, and system integration through the modular design of the motor components: the dual-winding stepper motor, in conjunction with the harmonic reducer, forms a redundant drive and torque amplification mechanism, which not only ensures the reliability of power output but also meets the drive requirements of large inertia loads; the encoder angle measurement component achieves closed-loop control by directly detecting the output shaft angle, providing accuracy assurance for deployment positioning; the integration method of stacking along the axis optimizes the structural compactness, while the platform mounting flange and the radiant cooling plate mounting flange ensure the stability of the interface connection, thereby improving the overall on-orbit adaptability and control reliability of the deployment mechanism.

[0081] In one embodiment, see Figure 6 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.

[0082] 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.

[0083] 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.

[0084] 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.

[0085] 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.

[0086] 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.

[0087] 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.

[0088] In one embodiment, see Figure 7 and Figure 8 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.

[0089] 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.

[0090] 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.

[0091] 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.

[0092] In one embodiment, see Figures 9-13 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.

[0093] 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.

[0094] 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 whose 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 an O-ring installed in the first annular groove 324, or it can be sealed by packing seal 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 port structure for connecting with the heat dissipation system pipeline of another radiant cooling plate to realize the connection of different radiant cooling plate heat dissipation systems.

[0095] 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.

[0096] 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.

[0097] 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.

[0098] 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.

[0099] 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.

[0100] In one embodiment, see Figure 6 and Figure 7 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.

[0101] 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.

[0102] 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.

[0103] 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.

[0104] In one embodiment, the cooling plate assembly further includes a heating component, which is in the form of a thin-film heating element and is distributed on the outer surface of the fluid pipeline.

[0105] The heating components primarily utilize aerospace-proven thin-film heating elements (heating films), suitable for complex surfaces. They employ a distributed arrangement: for rigid fluid pipelines, the heating elements are adhered to critical locations based on pipe diameter and structural characteristics; for flexible metal hoses connecting to rigid fluid pipelines, a wrapping method is used. This design is mainly used to heat and insulate the working fluid in pipelines at low temperatures, preventing freezing and ensuring the reliability of the fluid circuit under cryogenic conditions.

[0106] By directly attaching the heating film to the pipe surface, a tight-fitting heating interface can be established, which helps to reduce contact thermal resistance and improve the efficiency of heat transfer to the working fluid. The heating film is thin and lightweight, and its adhesive installation has little impact on the original structural layout of the fluid circuit. It can maintain conformal contact with the pipe geometry and does not interfere with the folding and unfolding movement of the flexible cooling plate.

[0107] As a heating element independent of the fluid circuit, the heating component can provide thermal control redundancy under certain conditions. For example, when supplementary heating is needed in a local area or the main thermal control system is ineffective, it provides an auxiliary means to maintain the basic functions of the system.

[0108] In summary, the embodiments of the present invention achieve the technical effects of optimizing interface heat transfer, low-temperature protection, structural compatibility, and auxiliary improvement of system reliability by using an adhesive heating film to heat the fluid pipeline.

[0109] 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 radiated cooling plate assembly for use in a space pump-driven fluid loop system, characterized in that, The radiant cooling plate assembly includes at least one radiant cooling plate; Each of the aforementioned radiant cooling plates includes a frame, rigid fluid piping, 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 to the space environment through thermal radiation. During the launch phase, all the single-layer cooling plates are stacked and retracted to form a composite structure, which is then pressed and locked to the spacecraft body by a pressing and releasing mechanism. During the on-orbit phase, after receiving an instruction, the clamping release mechanism releases the lock on the stacked structure. All the radiated cooling plates are then sequentially deployed and locked into the working configuration by the on-orbit deployment mechanism, and all the radiated cooling plates remain coplanar after deployment.

2. The radiant cooling plate assembly according to claim 1, characterized in that, The radiant cooling plate is provided with a liquid inlet and a liquid return port. The liquid inlet main pipeline is connected to the liquid inlet for introducing the working fluid, and the liquid return main pipeline is connected to the liquid return port for discharging the working fluid. The main return pipeline is arranged on one side edge of the corresponding frame, including two parallel sections and a second parallel section arranged in parallel and spaced apart in the same direction, a bend section and a vertical section. The bent section is coaxially connected to the top end of the first parallel section and the top end of the second parallel section, and the vertical section is perpendicularly connected to the bottom end of the second parallel section and to the return liquid interface. The ends of the multiple branch pipes away from the main inlet pipe are all vertically connected to the first parallel section of the main return pipe near the branch pipe. The first parallel section is used to collect the working fluid flowing through the branch pipe, guide it through the bend section to the second parallel section, and then guide it from the second parallel section to the vertical section, finally forming a working fluid return channel through the return interface.

3. The radiant cooling plate assembly according to claim 1, characterized in that, The flexible radiation film is a graphene-based composite film, which is formed by combining graphene and polyimide.

4. The radiant cooling plate assembly according to claim 1, characterized in that, The flexible radiative film has a functional coating sprayed on its sun-facing side to reduce solar heat absorption.

5. The radiant cooling plate assembly according to claim 1, characterized in that, The flexible radiation film is bonded to the surface of the rigid fluid pipeline using a low thermal resistance adhesive.

6. The radiant cooling plate assembly according to claim 1, characterized in that, A thermally conductive enhancement layer is disposed between the flexible radiation film and the rigid fluid pipeline, and the thermally conductive enhancement layer has a micro-nano trench structure.

7. The radiant cooling plate assembly according to claim 1, characterized in that, The clamping release mechanism adopts a release nut, which includes a shape memory alloy puller, a release nut body and an electrical connector, wherein the shape memory alloy puller has two parallel bridge wires. During the launch phase, the pin of the shape memory alloy puller is in the extended state, locking the separation nut body in the locked state, and pressing and locking the stacked and gathered radiant cooling plate assembly to the spacecraft body; Once in orbit, the electrical connector receives an electrical command that drives the shape memory alloy pin puller to retract its pin, releasing the release nut body and relieving the clamping constraint on the radiant cooling plate assembly.

8. The radiant cooling plate assembly according to claim 1, characterized in that, The on-orbit deployment mechanism includes a motor assembly, a constraint release pin, and a deployment hinge; The motor assembly is installed between the spacecraft body and the central radiant cooling plate, and is used to drive the central radiant cooling plate and the two side plates to perform an initial flip. The constraint release pin is used to release the connection constraint between adjacent radiant cooling plates after the initial flipping is completed; The unfolding hinge connects adjacent radiant cooling plates. After the constraint release pin releases the connection constraint, it drives the adjacent radiant cooling plates to unfold into the working configuration and lock them.

9. The radiant cooling plate assembly according to claim 8, characterized in that, The motor assembly includes a dual-winding stepper motor, a harmonic reducer, an encoder angle measurement assembly, a platform mounting flange, and a radiator plate mounting flange. The dual-winding stepper motor is used to provide power; The harmonic reducer is connected to the output shaft of the dual-winding stepper motor to reduce the speed and increase the torque. The encoder angle measuring component is connected to the output end of the harmonic reducer and is used to detect the rotation angle of the output shaft of the harmonic reducer. The platform mounting flange is used to fix the motor assembly to the spacecraft body; The radiant cooling plate mounting flange is used for fixed connection with the radiant cooling plate single plate located in the center; The platform mounting flange, dual-winding stepper motor, harmonic reducer, encoder angle measuring assembly, and radiant cooling plate mounting flange are stacked and integrated sequentially along the same axis.

10. The radiant cooling plate assembly according to claim 8, characterized in that, The unfolding hinge includes a hinge body, a locking mechanism, and a limit switch, which are mechanically integrated into one unit. The hinge body has a built-in elastic torsion spring. The elastic torsion spring stores elastic potential energy through pre-deformation, which is used to provide the unfolding driving force when the single plate of the radiated cold plate is unfolded. The locking mechanism is used to achieve rigid locking through the mechanical cooperation of the locking tongue and the locking buckle when the hinge body drives the cooling plate to unfold to the working angle. The limit switch is a mechanical contact switch, used to generate a locking status confirmation signal by closing the contact after the locking tongue of the locking mechanism is fully engaged with the latch.

11. The radiant cooling plate assembly according to claim 1, characterized in that, The main inlet pipe between adjacent radiant cooling plates is connected by a rotating water-passing joint, and a metal hose is connected to each end of the rotating water-passing joint; the main return pipe between adjacent radiant cooling plates is connected by another rotating water-passing joint, and a metal hose is also connected to each end of the rotating water-passing joint. The combination of the rotating water-passing joint and the metal hose is used to adapt to the relative movement of adjacent radiated cooling plates when they are folded or unfolded, ensuring the continuity of the working fluid flow.

12. The radiant cooling plate assembly according to claim 11, characterized in that, The rotating water-passing joint includes an outer tube, an inner tube, a seal, a first bearing, a second bearing, a bushing, a shaft retaining circlip, a hole retaining circlip, a first pipe connector, a sheath, and a second pipe connector; wherein... The outer tube is provided with a flow guiding channel inside, the axis of the flow guiding channel coincides with the axis of the outer tube itself, and a first pipe joint is fixed on the outer tube and communicates with the flow guiding channel. The first pipe joint is used to connect the main pipeline of the single plate of the side cooling plate. The inner tube is rotatably disposed inside the outer tube. Its first end is provided with an insert tube, which is inserted into the flow channel. The second end of the inner tube is fitted with a protective sleeve, and a second pipe joint is fixed on the protective sleeve. The second pipe joint is used to connect the main pipeline of the single plate of the other side of the radiant cooling plate, and the flow channel and the inner wall of the inner tube together form a fluid passage. The sealing element is disposed in the first annular groove on the outer wall of the insertion tube and sandwiched between the outer wall of the insertion tube and the inner wall of the flow channel to achieve radial dynamic sealing; The first bearing and the second bearing are sequentially fitted onto the outer wall of the inner tube. The bushing is fitted onto the outer wall of the inner tube and sandwiched between the inner rings of the first bearing and the second bearing. The shoulder of the first end of the inner tube is positioned against the inner ring of the first bearing. The shaft retaining ring is located in the second annular groove on the outer wall of the inner tube and abuts against the inner ring of the second bearing; the hole retaining ring is located in the third annular groove on the inner wall of the outer tube and abuts against the outer ring of the second bearing; together they constitute a locking device to prevent the inner tube from separating from the flow channel of the outer tube, and without affecting the relative rotation of the inner and outer tubes.

13. The radiant cooling plate assembly according to claim 11, characterized in that, The end of the metal hose is connected to the inlet or return main pipeline interface within the radiant cooling plate via a plunger-type connector with double O-ring seals. The plunger-type connector includes a plunger adapted to the main pipeline interface and a hole-shaped connector. The plunger is fixed to the end of the metal hose and inserted into the hole-shaped connector of the main pipeline interface. Two O-rings are axially spaced between the plunger and the hole-shaped connector to form a double radial sealing interface.

14. The radiant cooling plate assembly according to claim 1, characterized in that, It also includes a heating component, which is in the form of a thin-film heating element and is distributed on the outer surface of the rigid fluid pipeline.

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