Modularized splicable flexible radiation array and on-orbit assembly system thereof

Abstract

The invention relates to the technical field of radiation arrays, in particular to a modular splicable flexible radiation array and an on-orbit assembly system thereof, and the radiation array comprises a radiation plate, a fixed frame is arranged on the outer side wall of the radiation plate, a plurality of positioning blocks are arranged on the side wall of the fixed frame, first convex blocks for splicing and fixing are arranged on the side wall of the fixed frame, and a plurality of limiting grooves are formed in the side wall of the fixed frame. And second convex blocks for limiting the first convex blocks are symmetrically arranged in the limiting grooves. According to the invention, through the arrangement of the modular splicable flexible radiation array and the cooperation of the fixing frame and the positioning block, the butt joint between the radiation plates is realized, and through the limiting design of the first convex block and the second convex block, the structural stability after splicing is ensured, the expandability of the radiator is improved, the radiation area is flexibly adjusted according to the actual demand, and the radiation efficiency is improved. The on-orbit assembly process is simplified, the launching and deploying difficulty is lowered, and on-orbit maintenance and replacement are further facilitated through the modular design.

Description

Technical Field

[0001] This invention relates to the field of radiation array technology, and in particular to a modular, splicable flexible radiation array and its on-orbit assembly system. Background Technology

[0002] The heat dissipation requirements of GW-level space data centers place extremely high demands on the radiation area. According to the Stefan-Boltzmann law, 1GW of power requires an effective radiation area of ​​approximately 2.32 square kilometers in an environment of 30°C. Such a large radiator scale poses a severe challenge to satellite launch and on-orbit deployment.

[0003] Currently, there is no mature large-scale on-orbit assembly solution. Traditional monolithic radiators are limited by the space size of the rocket fairing and cannot be launched directly. Even with a folding design, the complexity and risk of the unfolding process increase dramatically with the increase in area, making them prone to entanglement, deformation, and other failures. In addition, if a monolithic radiator suffers partial damage, it will lead to a significant decrease in the performance of the entire heat dissipation system, and it cannot be repaired on-orbit, seriously affecting the long-term operation of space data centers. With the advancement of space computing infrastructure with a scale of thousands of stars, such as the "Three-Body Computing Constellation," higher requirements are placed on the scalability, maintainability, and deployment flexibility of radiators. Traditional designs can no longer meet these needs, and there is an urgent need to develop modular and splicable radiator technology. Summary of the Invention

[0004] The purpose of this invention is to solve the problems of difficulty in replacing locally damaged parts and low efficiency of on-orbit assembly in the prior art, and to propose a modular, splicable flexible radiation array and its on-orbit assembly system.

[0005] To achieve the above objectives, the present invention adopts the following technical solution: A modular, splicable flexible radiation array includes a radiation plate, a fixing frame on the outer side wall of the radiation plate, a plurality of positioning blocks on the side wall of the fixing frame, a first protrusion for splicing and fixing on the side wall of the fixing frame, a plurality of limiting grooves on the side wall of the fixing frame, and a second protrusion symmetrically arranged in the limiting grooves to limit the first protrusion.

[0006] Preferably, the side wall of the fixed frame is provided with a plurality of fixed blocks, and the fixed blocks are provided with positioning grooves, the positioning grooves and the positioning blocks being mutually compatible.

[0007] Preferably, the inner wall of the positioning groove is provided with a first rubber anti-slip pad, and the outer wall of the positioning block is provided with a second rubber anti-slip pad, the first rubber anti-slip pad and the second rubber anti-slip pad fitting together.

[0008] Preferably, the first protrusion has an inclined surface on its sidewall, the inner sidewall of the movable cavity is provided with an electric push rod, the output end of the electric push rod is provided with a connecting rod, the end of the connecting rod is provided with a second protrusion, and the sidewall of the second protrusion is symmetrically provided with inclined surfaces.

[0009] The on-orbit assembly system includes a base plate with multiple mounting bolts inserted at its end. Electromagnetic slide rails are symmetrically arranged at the end of the base plate. An electric slider is located on the outer wall of the electromagnetic slide rails. A first movable plate is located at the end of the electric slider. A rotating seat is located at the end of the first movable plate. A first rotating arm is located at the end of the rotating seat. A first drive motor is located on the side wall of the first rotating arm. A second rotating arm is located on the side wall of the first rotating arm. The output end of the first drive motor and the second rotating arm are coaxially connected. A support plate is located at the end of the second rotating arm. A support plate is located at the end of the support plate. Visual recognition sensors are symmetrically arranged at the end of the support plate. Multiple clamping plates are symmetrically arranged at the end of the support plate. A suction cup is located at the end of the support plate.

[0010] Preferably, the rotating seat has a movable cavity, the inner sidewall of the movable cavity has an L-shaped plate, the end of the L-shaped plate has a servo motor, the inner sidewall of the movable cavity has a rotating shaft, the end of the rotating shaft is connected to the bottom of the first rotating arm, the outer sidewall of the rotating shaft has a first gear, the inner sidewall of the movable cavity has a second gear, the end of the second gear is coaxially connected to the output end of the servo motor, and the first gear and the second gear mesh with each other.

[0011] Preferably, the support plate has a first groove, the inner sidewall of the first groove is provided with a second drive motor, the output end of the second drive motor is provided with a bidirectional lead screw, the outer sidewall of the bidirectional lead screw is provided with a second moving plate, and the bottom of the clamping plate and the end of the second moving plate are connected.

[0012] Preferably, the inner wall of the first groove is provided with a guide rod, and the second movable plate is provided with a movable hole, and the second movable plate is coaxially connected to the guide rod through the movable hole.

[0013] Preferably, a second groove is formed in the support plate, a third drive motor is provided on the inner sidewall of the second groove, the output end of the third drive motor is coaxially connected to the end of the support plate, an annular groove is formed at the end of the support plate, an annular slider is provided in the annular groove, and the annular slider is connected to the end of the support plate.

[0014] Preferably, the first drive motor, the second drive motor, the third drive motor, and the servo motor are all electrically connected to the visual recognition sensor.

[0015] Compared with the prior art, the present invention has the following advantages: 1. This invention, by setting up a modular, splicable flexible radiating array, utilizes the cooperation of a fixed frame and positioning blocks to achieve docking between radiating plates. At the same time, the limiting design of the first and second protrusions ensures the structural stability after splicing, improves the scalability of the radiator, allows for flexible adjustment of the radiating area according to actual needs, simplifies the on-orbit assembly process, reduces the difficulty of launch and deployment, and the modular design also facilitates on-orbit maintenance and replacement. Once a module is damaged, it can be quickly located and replaced, ensuring the continuous and efficient operation of the entire heat dissipation system.

[0016] 2. This invention enhances the stability of the radiating plate during splicing by incorporating rubber anti-slip pads, based on the mutual adaptation of the positioning groove and positioning block. The first and second rubber anti-slip pads fit together, reducing the possibility of loosening or displacement of the spliced ​​radiating plate in the complex space environment, thus improving the reliability of the radiating array in orbit. The inclined surface on the side wall of the first protrusion, along with the corresponding electric push rod, connecting rod, and second protrusion structure, makes the splicing process smoother and provides an automatic locking function. During the splicing operation, the electric push rod pushes the connecting rod, which in turn moves the second protrusion. Through the interaction of the inclined surfaces, the first protrusion is limited and fixed, improving the efficiency of the splicing process. Attached Figure Description

[0017] Figure 1 This is an isometric view of the on-orbit assembly system proposed in this invention; Figure 2 These are the left and right isometric views of the on-orbit assembly system proposed in this invention; Figure 3 This is a top-section view of the support plate of the on-orbit assembly system proposed in this invention; Figure 4 This is a sectional side view of the base plate of the on-orbit assembly system proposed in this invention; Figure 5 A partial schematic diagram A shows the on-orbit assembly system proposed in this invention; Figure 6 This is a top-section view of the base plate of the on-orbit assembly system proposed in this invention; Figure 7 This is a partial schematic diagram (B) of the on-orbit assembly system proposed in this invention; Figure 8 This is an isometric view of a modular, splicable flexible radiating array proposed in this invention; Figure 9 This is a partial schematic diagram (C) of a modular, splicable flexible radiating array proposed in this invention; Figure 10 This is a top-section view of the fixed frame of a modular, splicable flexible radiation array proposed in this invention; Figure 11This is a partial schematic diagram (D) of a modular, splicable flexible radiation array proposed in this invention.

[0018] In the diagram: 1. Base plate; 2. First moving plate; 3. Rotating seat; 4. Electric slider; 5. Electromagnetic slide rail; 6. First rotating arm; 7. Mounting bolt; 8. Second rotating arm; 9. Support plate; 10. Clamping plate; 11. Visual recognition sensor; 12. Suction cup; 13. First drive motor; 14. Second drive motor; 15. Second moving plate; 16. Guide rod; 17. Bidirectional lead screw; 18. Third drive motor; 19. Annular slider; 20. Annular groove; 21. Support plate; 22. Rotating shaft; 23. First gear; 24. Second gear; 25. Servo motor; 26. L-shaped plate; 27. Radial plate; 28. Fixed frame; 29. ​​Positioning block; 30. Fixed block; 31. First protrusion; 32. Second protrusion; 33. Connecting rod; 34. Electric push rod. Detailed Implementation

[0019] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments.

[0020] Reference Figures 1-11 A modular, splicable flexible radiating array includes a radiating plate 27, a fixing frame 28 fixedly disposed on the outer wall of the radiating plate 27, multiple positioning blocks 29 fixedly disposed on the side wall of the fixing frame 28, and multiple fixing blocks 30 fixedly disposed on the side wall of the fixing frame 28. The fixing blocks 30 have positioning grooves, and the positioning grooves and positioning blocks 29 are mutually adapted. Through the mutual cooperation of the fixing blocks 30 and the positioning grooves, the initial positioning of the radiating plate 27 is achieved during splicing, thereby improving the accuracy and efficiency of splicing.

[0021] like Figure 9 As shown, the first rubber anti-slip pad is fixedly installed on the inner wall of the positioning groove, and the second rubber anti-slip pad is fixedly installed on the outer wall of the positioning block 29. The first rubber anti-slip pad and the second rubber anti-slip pad are arranged in a sawtooth shape. The first rubber anti-slip pad and the second rubber anti-slip pad fit together. Through the cooperation of the first rubber anti-slip pad and the second rubber anti-slip pad, the friction between the positioning block 29 and the positioning groove is increased, preventing loosening or displacement during splicing or use, and improving the stability and reliability of the entire flexible radial array splicing.

[0022] like Figure 11As shown, the first protrusion 31 is fixedly mounted on the side wall of the fixed frame 28. The side wall of the fixed frame 28 has multiple limiting grooves. The second protrusion 32, which limits the first protrusion 31, is symmetrically arranged in the limiting grooves. The side wall of the first protrusion 31 has an inclined surface. The electric push rod 34 is fixedly mounted on the inner side wall of the movable cavity. The connecting rod 33 is fixedly mounted on the output end of the electric push rod 34. The second protrusion 32 is fixedly mounted on the end of the connecting rod 33. The side wall of the second protrusion 32 has an inclined surface. Through the mutual cooperation of the first protrusion 31 and the second protrusion 32, during splicing, the electric push rod 34 pushes the connecting rod 33. The electric push rod 34 drives the second protrusion 32 to move closer to the first protrusion 31. The inclined surface of the second protrusion 32 interacts with the inclined surface of the first protrusion 31, so that the second protrusion 32 can smoothly slide into the limiting groove to limit the first protrusion 31, realizing a firm splicing between the radiating plates 27 and facilitating on-orbit assembly.

[0023] The on-orbit assembly system includes a base plate 1, multiple mounting bolts 7 inserted at the end of the base plate 1, electromagnetic slide rails 5 symmetrically fixed at the end of the base plate 1, electric sliders 4 slidably disposed on the outer side wall of the electromagnetic slide rails 5, and a first moving plate 2 fixedly disposed at the end of the electric sliders 4. Through the cooperation of the electric sliders 4 and the electromagnetic slide rails 5, the first moving plate 2 can move in the horizontal direction to meet the assembly requirements of different positions.

[0024] like Figure 7 As shown, the rotating seat 3 is fixedly mounted at the end of the first movable plate 2. A movable cavity is opened inside the rotating seat 3. An L-shaped plate 26 is fixedly mounted on the inner side wall of the movable cavity. A servo motor 25 is fixedly mounted at the end of the L-shaped plate 26. A rotating shaft 22 is rotatably mounted on the inner side wall of the movable cavity. The end of the rotating shaft 22 is fixedly connected to the bottom of the first rotating arm 6. A first gear 23 is fixedly mounted on the outer side wall of the rotating shaft 22. A second gear 24 is rotatably mounted on the inner side wall of the movable cavity. The end of the second gear 24 is coaxially fixedly connected to the output end of the servo motor 25. The first gear 23 and the second gear 24 mesh with each other. Through the mutual cooperation of the first gear 23 and the second gear 24, the output end of the servo motor 25 drives the second gear 24 to rotate. The second gear 24 drives the first gear 23 to rotate. The first gear 23 drives the rotating shaft 22 to rotate, thereby realizing the rotation of the first rotating arm 6 in the vertical direction to meet the assembly requirements of different angles.

[0025] like Figure 2As shown, the first rotating arm 6 is rotatably mounted at the end of the rotating seat 3, the first drive motor 13 is fixedly mounted on the side wall of the first rotating arm 6, and the second rotating arm 8 is rotatably mounted on the side wall of the first rotating arm 6. The output end of the first drive motor 13 and the second rotating arm 8 are coaxially connected. Through the mutual cooperation of the first drive motor 13 and the second rotating arm 8, the output end of the first drive motor 13 drives the second rotating arm 8 to rotate, thereby realizing the rotation of the second rotating arm 8 relative to the first rotating arm 6, adjusting the assembly angle, and meeting the multi-angle operation requirements in the on-orbit assembly environment.

[0026] A support plate 21 is fixedly mounted at the end of the second rotating arm 8. A support plate 9 is provided at the end of the support plate 21. Multiple clamping plates 10 are symmetrically provided at the end of the support plate 9. A first groove is provided in the support plate 9. A second drive motor 14 is fixedly mounted on the inner side wall of the first groove. A bidirectional lead screw 17 is fixedly mounted at the output end of the second drive motor 14, and the end of the bidirectional lead screw 17 is rotatably connected to the inner side wall of the first groove. A threaded hole adapted to the outer side wall of the bidirectional lead screw 17 is provided in the second moving plate 15. The second moving plate 15 moves on the outer side wall of the bidirectional lead screw 17 through the internal thread. The bottom of the clamping plate 10 and the end of the second moving plate 15 are fixedly connected. Through the mutual cooperation of the clamping plate 10 and the second moving plate 15, the output end of the second drive motor 14 drives the bidirectional lead screw 17 to rotate. The bidirectional lead screw 17 drives the second moving plate 15 to move in opposite directions in the first groove. The second moving plate 15 drives the clamping plate 10 to clamp and fix the radiating plates 27 of different sizes, which improves the versatility and flexibility of the on-orbit assembly system.

[0027] The guide rod 16 is fixedly installed on the inner side wall of the first groove. The second movable plate 15 has a movable hole. The second movable plate 15 is coaxially connected to the guide rod 16 through the movable hole. Through the mutual cooperation of the guide rod 16 and the second movable plate 15, the guide rod 16 guides and limits the movement of the second movable plate 15, reducing the possibility of the second movable plate 15 deviating during movement, ensuring that the clamping plate 10 stably clamps the radiation plate 27, and improving the stability of clamping the radiation plate 27 during on-orbit assembly.

[0028] A second groove is formed inside the support plate 21, and a third drive motor 18 is provided on the inner side wall of the second groove. The output end of the third drive motor 18 is coaxially connected to the end of the support plate 9. An annular groove 20 is formed at the end of the support plate 21. An annular slider 19 is rotatably disposed on the inner side wall of the annular groove 20. The annular slider 19 is fixedly connected to the end of the support plate 9. Through the mutual cooperation between the annular slider 19 and the annular groove 20, when the output end of the third drive motor 18 drives the support plate 9 to rotate, the annular slider 19 rotates synchronously in the annular groove 20, providing stable support for the rotation of the support plate 9, so that the support plate 9 can rotate smoothly around the radial plate 27, meeting the assembly requirements of different orientations during on-orbit assembly, and improving the flexibility and adaptability of the on-orbit assembly system.

[0029] A suction cup 12 is fixedly mounted at the end of the support plate 9, and a visual recognition sensor 11 is symmetrically fixedly mounted at the end of the support plate 9. The first drive motor 13, the second drive motor 14, the third drive motor 18, and the servo motor 25 are all electrically connected to the visual recognition sensor 11. With this configuration, the visual recognition sensor 11 can acquire environmental information and the position status of the radiating plate 27 in real time during the on-orbit assembly process, and feed this information back to the first drive motor 13, the second drive motor 14, the third drive motor 18, and the servo motor 25, so that they can accurately adjust their actions according to the actual situation, realize automated and intelligent on-orbit assembly operations, improve the efficiency and accuracy of on-orbit assembly, and reduce manual intervention and operational errors.

[0030] The functional principle of this invention can be explained through the following operational methods: The operator starts the electric slider 4 to slide on the electromagnetic slide rail 5. The electric slider 4 drives the first moving plate 2 to adjust its position. Then, the servo motor 25 is started. The servo motor 25 drives the second gear 24 to rotate. Since the second gear 24 meshes with the first gear 23, the second gear 24 drives the first gear 23 and the rotating shaft 22 to rotate. The rotating shaft 22 then drives the first rotating arm 6 to rotate, thereby realizing the angle adjustment of the first rotating arm 6 in the horizontal direction. The first drive motor 13 is started, which drives the second rotating arm 8 to rotate relative to the first rotating arm 6. The position and angle of the second rotating arm 8 are adjusted. When the second rotating arm 8 reaches the appropriate position, the support plate 9 on the support plate 21 identifies the position information of the target modular splicable flexible radiation array through the visual recognition sensor 11. Then the second drive motor 14 is started, which drives the bidirectional lead screw 17 to rotate. The bidirectional lead screw 17 drives the second moving plate 15 to move towards the center under the guidance of the guide rod 16. The second moving plate 15 drives the clamping plate 10 to clamp the target radiation array. At the same time, the suction cup 12 also assists in adsorbing and fixing the radiation array to ensure the stability of the gripping. When it is necessary to splice the radiation array, the radiation array is accurately moved to the splicing position. Through the cooperation of the first protrusion 31 and the second protrusion 32, as well as the adaptation of the positioning block 29 and the positioning groove, the precise splicing and fixing between the radiation arrays is achieved. If it is necessary to adjust the rotation angle of the support plate 9, the third drive motor 18 is started. The third drive motor 18 drives the support plate 9 to rotate under the cooperation of the annular slider 19 and the annular groove 20 to meet the splicing requirements of different angles.

[0031] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A modular, tileable flexible radiating array comprising a radiating panel (27) characterised in that, The outer side wall of the radiation plate (27) is provided with a fixed frame (28), the side wall of the fixed frame (28) is provided with a plurality of positioning blocks (29), the side wall of the fixed frame (28) is provided with a first protrusion (31) fixed by splicing, a plurality of limiting grooves are formed in the side wall of the fixed frame (28), and a second protrusion (32) for limiting the first protrusion (31) is arranged in the limiting grooves in a symmetrical manner.

2. A modular, tileable flexible radiating array according to claim 1, wherein, The side wall of the fixed frame (28) is provided with a plurality of fixed blocks (30), the fixed blocks (30) are provided with positioning grooves, and the positioning grooves and the positioning blocks (29) are matched with each other.

3. A modular, tileable flexible radiating array according to claim 2, wherein, The inner side wall of the positioning groove is provided with a first rubber anti-skid pad, the outer side wall of the positioning block (29) is provided with a second rubber anti-skid pad, and the first rubber anti-skid pad and the second rubber anti-skid pad are matched with each other.

4. A modular, tileable flexible radiating array according to claim 3, wherein, The side wall of the first protrusion (31) is provided with an inclined surface, the inner side wall of the movable cavity is provided with an electric push rod (34), the output end of the electric push rod (34) is provided with a connecting rod (33), the end of the connecting rod (33) is provided with a second protrusion (32), and the side wall of the second protrusion (32) is provided with an inclined surface in a symmetrical manner.

5. An on-orbit assembly system applied to a modular splicable flexible radiating array as claimed in claim 4, comprising a base plate (1), characterized in that, The end of the bottom plate (1) is provided with a plurality of mounting bolts (7), the end of the bottom plate (1) is provided with electromagnetic slide rails (5) in a symmetrical manner, the outer side wall of the electromagnetic slide rail (5) is provided with an electric sliding block (4), the end of the electric sliding block (4) is provided with a first moving plate (2), the end of the first moving plate (2) is provided with a rotating seat (3), the end of the rotating seat (3) is provided with a first rotating arm (6), the side wall of the first rotating arm (6) is provided with a first driving motor (13), the side wall of the first rotating arm (6) is provided with a second rotating arm (8), the output end of the first driving motor (13) is coaxially connected with the second rotating arm (8), the end of the second rotating arm (8) is provided with a supporting disc (21), the end of the supporting disc (21) is provided with a supporting plate (9), the end of the supporting plate (9) is provided with visual identification sensors (11) in a symmetrical manner, the end of the supporting plate (9) is provided with a plurality of clamping plates (10) in a symmetrical manner, and the end of the supporting plate (9) is provided with a suction disc (12).

6. A modular, splicable, flexible radiating array and its on-orbit assembly system according to claim 5, characterized in that, The inner side wall of the rotating seat (3) is provided with a movable cavity, the inner side wall of the movable cavity is provided with an L-shaped plate (26), the end of the L-shaped plate (26) is provided with a servo motor (25), the inner side wall of the movable cavity is provided with a rotating shaft (22), the end of the rotating shaft (22) is connected with the bottom of the first rotating arm (6), the outer side wall of the rotating shaft (22) is provided with a first gear (23), the inner side wall of the movable cavity is provided with a second gear (24), the end of the second gear (24) is coaxially connected with the output end of the servo motor (25), and the first gear (23) and the second gear (24) are meshed with each other.

7. A modular, splicable, flexible radiating array and its on-orbit assembly system according to claim 6, characterized in that, The inner side wall of the supporting plate (9) is provided with a first recess, the inner side wall of the first recess is provided with a second driving motor (14), the output end of the second driving motor (14) is provided with a bidirectional screw rod (17), the outer side wall of the bidirectional screw rod (17) is provided with a second moving plate (15), and the bottom of the clamping plate (10) is connected with the end of the second moving plate (15).

8. A modular, splicable, flexible radiating array and its on-orbit assembly system according to claim 7, characterized in that, The inner side wall of the first groove is provided with a guide rod (16), and the second moving plate (15) is coaxially connected with the guide rod (16) through an activity hole.

9. A modular, splicable, flexible radiating array and its on-orbit assembly system according to claim 8, characterized in that, The support disc (21) is provided with a second groove, and the inner side wall of the second groove is provided with a third driving motor (18). The output end of the third driving motor (18) is coaxially connected with the end of the support plate (9). The end of the support disc (21) is provided with an annular sliding groove (20), and the annular sliding groove (20) is provided with an annular sliding block (19). The annular sliding block (19) is connected with the end of the support plate (9).

10. A modular, splicable, flexible radiating array and system for on-orbit assembly thereof according to claim 9, wherein, The first driving motor (13), the second driving motor (14), the third driving motor (18) and the servo motor (25) are electrically connected with the visual identification sensor (11).

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