Satellite side plate structure and integrated method for in-orbit fine temperature control single machine heat pipe lead-out

Abstract

The application relates to a satellite side plate structure and an integrated method for leading out a heat pipe of an in-orbit precise temperature control single machine, which comprises a filling plate and a main bearing frame, the main bearing frame is filled and installed in an installation groove of the filling plate; the main bearing frame forms a plurality of assembly windows corresponding to the installation positions of precise temperature control single machine equipment, and the assembly windows correspond to the positions of L-shaped heat pipe leading-out cabin bodies when the precise temperature control single machine equipment is installed in a satellite cabin; the main bearing frame is provided with a plurality of heat insulation columns for supporting radiation cold plates corresponding to the outer side of the cabin body; during final assembly, the filling plate is assembled outside the satellite cabin body to form a cabin body side plate, the main bearing frame is installed after the precise temperature control single machine equipment is installed in the satellite cabin body; the L-shaped heat pipe is installed from the assembly window, then the radiation cold plate is installed, and finally the radiation cold plate is connected and fixed with the heat insulation columns. The application solves the system-level engineering problems of the complicated heat pipe of the precise temperature control single machine equipment, such as difficult leading-out, difficult installation and difficult support at the satellite side plate.

Description

Technical Field

[0001] This invention relates to the field of spacecraft structural design and assembly technology, specifically to a satellite side plate structure and integration method for heat pipe extraction from an in-satellite precision temperature control unit. Background Technology

[0002] In satellite design, traditional satellite structures use integral side panels, which have systemic defects in design, manufacturing, and assembly: Because the satellite's internal temperature control unit is equipped with heat pipes, the heat pipe path must be adapted to the predetermined side panel opening position, making it difficult to optimize the heat dissipation path. Any adjustment to the layout of the unit will lead to the redesign and manufacturing of the side panel, resulting in a long iteration cycle.

[0003] During the assembly stage, operators need to precisely pass the L-shaped heat pipe through the side plate holes and connect it with the external cooling plate in an extremely narrow visual and operational space. This can easily cause heat pipe breakage, excessive assembly stress, or poor contact, resulting in low assembly quality and efficiency.

[0004] Furthermore, due to the relatively independent and uncoordinated design of the structure, thermal control, and final assembly, the structural plate cannot proactively provide optimal support for the thermal management system. Summary of the Invention

[0005] To address the aforementioned technical problems, this invention provides a satellite side plate structure and integration method for extracting heat pipes from a single in-satellite precision temperature control unit, solving the system-level engineering problems of "difficult extraction, difficult installation, and difficult support" of multiple complex heat pipes in precision temperature control units at the satellite side plate.

[0006] The technical objective of this invention is achieved through the following technical solution: A satellite side plate structure for heat pipe extraction of a single precision temperature control unit within a satellite includes a filler plate and a main load-bearing frame. The filler plate has a pre-reserved mounting groove for the main load-bearing frame corresponding to the installation position of the precision temperature control unit. The main load-bearing frame is filled and installed in the mounting groove. The main load-bearing frame forms several assembly windows corresponding to the installation position of the precision temperature control unit. When the precision temperature control unit is installed inside the satellite cabin, there is an assembly window at the position where the L-shaped heat pipe exits the cabin. The four sides of the main load-bearing frame are provided with countersunk holes for assembly and connection with the filler plate and the cabin floor plate. The main load-bearing frame is provided with several heat insulation columns for supporting the radiant cooling plate on the outer side of the cabin.

[0007] Furthermore, the main load-bearing frame includes longitudinal load-bearing rods and transverse load-bearing rods, which are vertically connected to form a frame structure with several assembly windows; countersunk holes are pre-embedded in the longitudinal and transverse load-bearing rods around the perimeter of the frame structure; and thermal insulation columns are installed on the longitudinal and / or transverse load-bearing rods around the assembly windows.

[0008] Furthermore, the longitudinal and transverse load-bearing bars are connected by node components; the longitudinal load-bearing bars, transverse load-bearing bars, and node components are all made of carbon fiber reinforced composite material.

[0009] Furthermore, threaded holes are pre-embedded on the longitudinal and transverse support rods of the heat insulation column. The bottom of the heat insulation column is provided with a through hole corresponding to the threaded hole of the threaded hole pre-embedded part, and the top of the heat insulation column is provided with a threaded hole for fixing the cooling plate. Bolts that are threadedly connected to the threaded hole pre-embedded part are inserted into the through hole.

[0010] Furthermore, the insulation column is made of low thermal conductivity titanium alloy or polyimide.

[0011] Furthermore, the height of the insulation column is adjustable.

[0012] Furthermore, the infill panel includes a carbon fiber panel and an aluminum honeycomb panel, with the carbon fiber panel sandwiched between the two sides of the aluminum honeycomb panel.

[0013] This invention also provides a satellite side plate structure, heat pipe path, and radiant cooling plate integration method for heat pipe extraction from a single in-satellite precision temperature control unit. The method includes: During the final assembly stage, after the filler plates of the satellite side panel structure are assembled on the outside of the satellite cabin, the main load-bearing frame is not installed yet. After the precision temperature control unit is installed into the satellite cabin and fixed to the cabin floor during the final assembly stage, the main load-bearing frame is filled and installed in the mounting slot. The L-shaped heat pipe is connected to the precision temperature control unit from the outside of the cabin through the assembly window of the main load-bearing frame. A radiant cooling plate is installed on the outside of the cabin so that the radiant cooling plate and the L-shaped heat pipe can achieve thermal contact outside the cabin. Finally, the radiant cooling plate is connected and fixed to the heat insulation column of the main load-bearing frame.

[0014] Furthermore, the radiant cooling plate and the L-shaped heat pipe are bolted together outside the cabin, and a heat-conducting layer is installed at the connection point between the radiant cooling plate and the L-shaped heat pipe.

[0015] Compared with the prior art, the beneficial effects of the present invention are as follows: 1. Through the design of the satellite side plate structure of the present invention, the frame structure of the main load-bearing frame can flexibly adapt to almost any irregular heat pipe arrangement. As a result, the heat pipes are no longer limited by the traditional side plate holes when passing through, and the heat pipes can be arranged in the ideal path with the shortest and least bending, thereby reducing the heat transfer resistance.

[0016] 2. This invention uses the main load-bearing frame as a unified, high-rigidity foundation, which simultaneously serves the force transmission (mechanical interface) of the satellite's main structure and the support (thermal interface) of the cooling plate, making the load transmission path clear and the risk of thermal short circuit controllable.

[0017] 3. The method of this invention can serve as a standard design pattern and be applied to different side panels of a satellite. By determining the plane position through which the heat pipe needs to pass and the installation support point position of the radiant cooling plate, the design position of the main load-bearing frame can be determined, thereby quickly generating side panel schemes that adapt to different single-unit layouts, which is conducive to the modular development of satellite platforms.

[0018] 4. The method of this invention transforms the highly difficult precision tube threading operation into a simple operation of threading through the assembly window, significantly reducing the skill requirements for operators and the assembly error rate, which is conducive to improving the final assembly efficiency. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the satellite side plate structure for the heat pipe leading out of the single unit of the in-satellite precision temperature control system according to the present invention.

[0020] Figure 2 This is a schematic diagram of the main load-bearing frame structure in this invention.

[0021] Figure 3 This is a schematic diagram of the countersunk hole pre-embedded component structure in this invention.

[0022] Figure 4 This is a cross-sectional view of the countersunk hole pre-embedded component structure in this invention.

[0023] Figure 5 This is a schematic diagram of the threaded hole embedded part structure in this invention.

[0024] Figure 6 This is a schematic diagram of the heat insulation column structure in this invention.

[0025] Figure 7 This is a schematic diagram of the filling plate being assembled on the outside of the satellite cabin during the final assembly stage of this invention.

[0026] Figure 8 This is a schematic diagram of the precision temperature control unit in this invention being installed into the satellite cabin during the final assembly stage.

[0027] Figure 9 This is a schematic diagram of the installation of the main load-bearing frame in this invention.

[0028] Figure 10 This is a schematic diagram of the L-shaped heat pipe passing through the assembly window in this invention.

[0029] Figure 11 This is a schematic diagram showing the connection between the L-shaped heat pipe and the radiant cooling plate in the precision temperature control unit of this invention.

[0030] Figure 12 This is a schematic diagram of the installation of the cooling plate in this invention.

[0031] In the picture: 1. Main load-bearing frame; 2. Filler plate; 3. Thermal insulation column; 4. Precision temperature control unit; 5. L-shaped heat pipe; 6. Bottom plate of the cabin; 7. Cooling plate; 101. Longitudinal load-bearing bar; 102. Transverse load-bearing bar; 103. Joint component; 104. Post-processed precision shim; 105. Countersunk hole embedded part; 106. Threaded hole embedded part; 301. Mounting through hole; 302. Threaded hole. Detailed Implementation

[0032] The technical solution of the present invention will be further described below with reference to specific embodiments: A satellite sideplate structure for heat pipe extraction from a single unit in a satellite's precise temperature control system, such as... Figures 1-6 As shown, it includes a filling plate 2 and a main load-bearing frame 1. The filling plate 2 has a reserved mounting groove for the main load-bearing frame at the installation position of the precision temperature control unit 4. The main load-bearing frame 1 is filled and installed in the mounting groove. The main load-bearing frame 1 forms several assembly windows at the installation position of the precision temperature control unit 4. When the precision temperature control unit 4 is installed in the spacecraft cabin, there is an assembly window at the position where the L-shaped heat pipe 5 leads out of the cabin. The four sides of the main load-bearing frame 1 are provided with countersunk hole embedded parts 105 for assembly and connection with the filling plate 2 and the cabin bottom plate 6. The main load-bearing frame 1 is provided with several heat insulation columns 3 for supporting the radiant cooling plate 7 on the outer side of the cabin.

[0033] More specifically, such as Figure 2 As shown, the main load-bearing frame 1 includes longitudinal load-bearing members 101 and transverse load-bearing members 102. The longitudinal load-bearing members 101 and transverse load-bearing members 102 are vertically connected to form a frame structure with several assembly windows. Countersunk hole embedded parts 105 are pre-embedded and installed in the longitudinal load-bearing members 101 and transverse load-bearing members 102 on the periphery of the frame structure. The countersunk hole embedded parts 105 are as follows: Figure 3 and Figure 4 As shown; heat insulation columns 3 are installed on the longitudinal support rods 101 and / or transverse support rods 102 around the assembly window.

[0034] Preferably, the longitudinal support bar 101 and the transverse support bar 102 are made of carbon fiber reinforced composite material, and the connection between the longitudinal support bar 101 and the transverse support bar 102 is connected by a node 103, which is also made of carbon fiber reinforced composite material.

[0035] To facilitate the installation of the heat insulation column 3, threaded hole embedded parts 106 are pre-embedded on the longitudinal support rod 101 and the transverse support rod 102 of the heat insulation column 3. The threaded hole embedded parts 106 are as follows: Figure 5 As shown, it is equipped with internal threads; the heat insulation column 3 is as follows. Figure 6As shown, the bottom of the heat insulation column 3 is provided with a mounting through hole 301 corresponding to the threaded hole of the threaded hole pre-embedded part 106, and the top of the heat insulation column 3 is provided with a threaded hole 302 for fixing the radiant cooling plate 7. When fixing the radiant cooling plate 7 later, it is fixed to the threaded hole 302 by bolts. The mounting through hole 301 and the threaded hole 302 are staggered. A bolt that is threaded and connected to the threaded hole pre-embedded part 106 is inserted in the mounting through hole 301. Preferably, the heat insulation column 3 is made of low thermal conductivity titanium alloy or polyimide material to achieve thermal conduction barrier between the radiant cooling plate 7 and the main load-bearing frame 1.

[0036] Preferably, the height of the heat insulation column 3 is adjustable. In one implementation, the heat insulation column 3 is detachably installed on the main load-bearing frame 1, and heat insulation columns 3 of different heights can be manufactured and replaced with heat insulation columns 3 of different heights as needed.

[0037] More specifically, the filling plate 2 includes a carbon fiber panel and an aluminum honeycomb panel, with the carbon fiber panel sandwiched between the two sides of the aluminum honeycomb panel. The shape of the mounting groove on the filling plate 2 can be adapted to the shape and size of the main load-bearing frame 1.

[0038] This embodiment also provides a satellite side plate structure, heat pipe path, and radiant cooling plate integration method for heat pipe extraction from an in-satellite precision temperature control unit. The method includes: During the final assembly stage, the infill plate 2 of the satellite side panel structure is assembled onto the outside of the satellite cabin to form part of the cabin side panel. The main load-bearing frame 1 is not installed at this time. Figure 7 As shown; The precise temperature control unit 4 is installed into the satellite cabin during the final assembly stage and fixed to the cabin floor plate 6, such as Figure 8 As shown: After the precision temperature control unit 4 is installed, the main load-bearing frame 1 is filled and installed in the mounting groove, such as... Figure 9 As shown; the upper end and left and right sides of the main load-bearing frame 1 are connected to the threaded hole embedded part 106 by bolts passing through the filler plate; the lower end of the main load-bearing frame 1 is connected to the threaded hole embedded part 106 by bolts passing through the bottom plate 6 of the cabin; a post-processing precision shim 104 is also provided at the position where the bolts of the main load-bearing frame pass through. After the bolts pass through the post-processing shim 104, they are threadedly connected to the threaded hole embedded part 106. The post-processing shim 104 is made of aluminum alloy to ensure the installation accuracy of the main load-bearing frame 1; After the main load-bearing frame 1 is installed, the L-shaped heat pipe 5 is connected to the precision temperature control unit 4 from the outside of the cabin through the assembly window of the main load-bearing frame 1, such as... Figure 10 As shown; A cooling plate 7 is installed on the outside of the cabin, allowing the cooling plate 7 and the L-shaped heat pipe 5 to make thermally conductive contact outside the cabin. Specifically, the cooling plate 7 and the L-shaped heat pipe 5 are connected by bolts outside the cabin. Preferably, a thermally conductive layer is provided at the connection point between the cooling plate 7 and the L-shaped heat pipe 5. Finally, the cooling plate 7 is fixed to the heat-insulating column 3 of the main load-bearing frame 1. Figure 11 and Figure 12 As shown. After the radiant cooling plate 7 is installed, the gaps in the remaining frame are sealed by a thermal control multilayer insulation assembly. For example, an aluminized reflective film and a low thermal conductivity spacer are alternately stacked to form an extra-spacer thermal control multilayer insulation assembly to seal the gaps in the remaining frame, relying on the vacuum radiation insulation effect of the multilayer insulation assembly to isolate the orbital heat exchange.

[0039] This embodiment is merely a further explanation of the present invention and is not intended to limit the present invention. Those skilled in the art can make non-inventive modifications to this embodiment as needed after reading this specification, but such modifications are protected by patent law as long as they are within the scope of the claims of the present invention.

Claims

1. A satellite side plate structure for heat pipe extraction from a single unit of in-satellite precision temperature control, characterized in that, The system includes a filler plate and a main load-bearing frame. The filler plate has a pre-reserved mounting groove for the main load-bearing frame at the installation position of the precision temperature control unit. The main load-bearing frame is filled and installed in the mounting groove. The main load-bearing frame forms several assembly windows at the installation position of the precision temperature control unit. When the precision temperature control unit is installed in the spacecraft cabin, there is an assembly window at the position where the L-shaped heat pipe leads out of the cabin. The four sides of the main load-bearing frame are provided with countersunk holes for assembly and connection with the filler plate and the cabin floor plate. The main load-bearing frame is provided with several heat insulation columns for supporting the cooling plates on the outer side of the cabin.

2. The satellite side plate structure for the extraction of heat pipes from a single unit of in-satellite precision temperature control according to claim 1, characterized in that, The main load-bearing frame includes longitudinal load-bearing rods and transverse load-bearing rods, which are vertically connected to form a frame structure with several assembly windows; countersunk holes are pre-embedded in the longitudinal and transverse load-bearing rods around the periphery of the frame structure; and heat insulation columns are installed on the longitudinal and / or transverse load-bearing rods around the assembly windows.

3. A satellite side plate structure for heat pipe extraction from an intra-satellite precision temperature control unit according to claim 2, characterized in that, The longitudinal and transverse load-bearing bars are connected by node components; the longitudinal and transverse load-bearing bars and node components are all made of carbon fiber reinforced composite material.

4. A satellite side plate structure for heat pipe extraction from a single unit of in-satellite precision temperature control, as described in claim 2, characterized in that... The longitudinal and transverse support rods of the heat insulation column are pre-embedded with threaded holes. The bottom of the heat insulation column is provided with a through hole corresponding to the threaded hole of the pre-embedded threaded hole. The top of the heat insulation column is provided with a threaded hole for fixing the cooling plate. A bolt that is threadedly connected to the pre-embedded threaded hole is inserted into the through hole.

5. A satellite side plate structure for heat pipe extraction from a single unit of in-satellite precision temperature control, as described in claim 5, characterized in that... The heat insulation column is made of low thermal conductivity titanium alloy or polyimide.

6. A satellite side plate structure for heat pipe extraction from an intra-satellite precision temperature control unit according to claim 1, characterized in that, The height of the insulation column is adjustable.

7. A satellite side plate structure for heat pipe extraction from an intra-satellite precision temperature control unit according to claim 1, characterized in that, The filler plate includes a carbon fiber panel and an aluminum honeycomb panel, with the carbon fiber panel sandwiched between the two sides of the aluminum honeycomb panel.

8. A satellite side plate structure, heat pipe path, and radiant cooling plate integration method for heat pipe extraction from a single unit of in-satellite precision temperature control, characterized in that... The satellite side panel structure is as described in any one of claims 1 to 7, and the method includes: During the final assembly stage, after the filler plates of the satellite side panel structure are assembled on the outside of the satellite cabin, the main load-bearing frame is not installed yet. After the precision temperature control unit is installed into the satellite cabin and fixed to the cabin floor during the final assembly stage, the main load-bearing frame is filled and installed in the mounting slot. The L-shaped heat pipe is connected to the precision temperature control unit from the outside of the cabin through the assembly window of the main load-bearing frame. A radiant cooling plate is installed on the outside of the cabin so that the radiant cooling plate and the L-shaped heat pipe can achieve thermal contact outside the cabin. Finally, the radiant cooling plate is connected and fixed to the heat insulation column of the main load-bearing frame.

9. The satellite side plate structure, heat pipe path, and radiant cooling plate integration method using an in-satellite precision temperature control unit heat pipe as described in claim 8, characterized in that... The radiant cooling plate and the L-shaped heat pipe are connected to the outside of the cabin by bolts, and a heat-conducting layer is provided at the connection position between the radiant cooling plate and the L-shaped heat pipe.

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