A double fluid circuit system for a common platform

Abstract

The present invention relates to a public platform double fluid circuit system, belonging to the technical field of composite material main load-bearing structure forming process; it comprises a first fluid circuit system and a second fluid circuit system; wherein the first fluid circuit system comprises a first pump valve assembly, a first fluid circuit heat pipe, a first deployable heat radiator, a first upper horizontal plate pre-buried heat pipe and a first lower horizontal plate pre-buried heat pipe; the second fluid circuit system comprises a second pump valve assembly, a second fluid circuit heat pipe, a second deployable heat radiator, a second upper horizontal plate pre-buried heat pipe and a second lower horizontal plate pre-buried heat pipe; the layout position of the double fluid circuit system of the present invention in a satellite payload cabin is symmetrical along the horizontal direction of the satellite, and the satellite internal weight changes and torque changes caused by the unidirectional flow of the working fluid in the pipeline are offset each other.

Description

Technical Field

[0001] The invention belongs to the technical field of composite material main load-bearing structure forming process, and relates to a public platform double fluid circuit system. Background Art

[0002] As space missions gradually increase the performance requirements of launch vehicles, the satellite platform under development is a cross-generational satellite platform with many technological innovations, high integration, and multiple key technologies. The heat inside the satellite is mainly dissipated to space through the heat dissipation surface. The heat dissipation surface of the satellite is selected on the outer surface of the north and south plates where the sunlight exposure changes little.

[0003] However, the actual situation is that the heat consumption of existing satellite platforms has increased significantly, and there is no corresponding isothermal design inside the satellite, which makes it impossible to collect the heat generated by the internal structural plates of the satellite and dissipate the generated heat outside the satellite. Summary of the invention

[0004] The technical problem solved by the present invention is: to overcome the shortcomings of the prior art and propose a double fluid circuit system for a public platform. The layout position of the double fluid circuit system in the satellite payload cabin is symmetrical along the horizontal center direction of the satellite, realizing the isothermal design of the satellite body, collecting the heat consumption generated by the internal structural plates of the satellite body, and dissipating it to the outside of the satellite body through the fluid circuit heat pipe and the heat dissipation surface.

[0005] The solution of the present invention is:

[0006] A double fluid circuit system for a common platform, comprising a first fluid circuit system and a second fluid circuit system; wherein the first fluid circuit system comprises a first pump valve assembly, a first fluid circuit heat pipe, a first deployable heat radiator, a first upper horizontal plate pre-buried heat pipe and a first lower horizontal plate pre-buried heat pipe; the second fluid circuit system comprises a second pump valve assembly, a second fluid circuit heat pipe, a second deployable heat radiator, a second upper horizontal plate pre-buried heat pipe and a second lower horizontal plate pre-buried heat pipe;

[0007] The first pump-valve assembly is installed at the bottom of the lower horizontal plate of the satellite payload cabin; the first deployable heat radiator is arranged on the south plate of the satellite payload cabin; the first upper horizontal plate pre-buried heat pipe is horizontally installed on the upper horizontal plate of the satellite payload cabin; the first lower horizontal plate pre-buried heat pipe is horizontally installed on the lower horizontal plate of the satellite payload cabin; the first pump-valve assembly, the first lower horizontal plate pre-buried heat pipe, the first upper horizontal plate pre-buried heat pipe, and the first deployable heat radiator are all connected through the first fluid circuit heat pipe;

[0008] The second pump-valve assembly is installed at the bottom of the lower horizontal plate of the satellite payload cabin; the second deployable heat radiator is arranged on the north plate of the satellite payload cabin; the second upper horizontal plate pre-buried heat pipe is horizontally installed on the upper horizontal plate of the satellite payload cabin; the second lower horizontal plate pre-buried heat pipe is horizontally installed on the lower horizontal plate of the satellite payload cabin; the second pump-valve assembly, the second lower horizontal plate pre-buried heat pipe, the second upper horizontal plate pre-buried heat pipe and the second deployable heat radiator are all connected through the second fluid circuit heat pipe.

[0009] In the above-mentioned common platform double fluid circuit system, the first fluid circuit system and the second fluid circuit system have the same system composition, and the first fluid circuit system and the second fluid circuit system are symmetrical relative to the center of the satellite payload compartment.

[0010] In the above-mentioned common platform dual fluid circuit system, the first deployable heat radiator can be opened or closed by rotation relative to the south plate of the satellite payload cabin; the second deployable heat radiator can be opened or closed by rotation relative to the north plate of the satellite payload cabin; and the first deployable heat radiator and the second deployable heat radiator are symmetrical relative to the center of the satellite payload cabin.

[0011] In the above-mentioned common platform double fluid circuit system, the first pump-valve assembly provides power for the first fluid circuit system, driving the working fluid to flow in the heat pipe of the first fluid circuit system to transfer heat; the second pump-valve assembly provides power for the second fluid circuit system, driving the working fluid to flow in the heat pipe of the second fluid circuit system to transfer heat.

[0012] In the above-mentioned common platform double fluid circuit system, the path of the working fluid circulation circuit in the first fluid circuit system is:

[0013] The working medium flows out under the drive of the first pump-valve assembly, and enters the first deployable thermal radiator through the first fluid loop heat pipe, the first lower horizontal plate pre-buried heat pipe, the first fluid loop heat pipe, the first upper horizontal plate pre-buried heat pipe, and the first fluid loop heat pipe in sequence; the first deployable thermal radiator is deployed in orbit to increase the heat dissipation surface and dissipate heat to the external space; the first fluid loop system is lowered, and the low-temperature working medium flows back to the inlet of the first pump-valve assembly to form a circulation loop.

[0014] In the above-mentioned common platform double fluid circuit system, the path of the working fluid circulation circuit in the second fluid circuit system is:

[0015] The working medium flows out under the drive of the second pump-valve assembly, and enters the second deployable thermal radiator through the second fluid loop heat pipe, the second lower horizontal plate pre-buried heat pipe, the second fluid loop heat pipe, the second upper horizontal plate pre-buried heat pipe, and the second fluid loop heat pipe in sequence; the second deployable thermal radiator is deployed in orbit to increase the heat dissipation surface and dissipate the heat to the external space; the first fluid loop system is lowered, and the low-temperature working medium flows back to the inlet of the second pump-valve assembly to form a circulation loop.

[0016] In the above-mentioned public platform double fluid circuit system, the first upper horizontal plate pre-buried heat pipe and the second upper horizontal plate pre-buried heat pipe are both single-row wave tube structures; and the first upper horizontal plate pre-buried heat pipe and the second upper horizontal plate pre-buried heat pipe are symmetrically arranged.

[0017] In the above-mentioned common platform double fluid circuit system, the first lower horizontal plate pre-buried heat pipe and the second lower horizontal plate pre-buried heat pipe are both double-row wave tube structures, and the first lower horizontal plate pre-buried heat pipe and the second lower horizontal plate pre-buried heat pipe are symmetrically arranged.

[0018] In the above-mentioned common platform double fluid circuit system, the first fluid circuit heat pipe and the second fluid circuit heat pipe are both made of aluminum alloy 2A12 material, and the inner diameter of the pipe is 12 mm; the first fluid circuit heat pipe is threadedly connected to the first pump valve assembly, the first expandable heat radiator, the first upper horizontal plate pre-buried heat pipe and the first lower horizontal plate pre-buried heat pipe; the second fluid circuit heat pipe is threadedly connected to the second pump valve assembly, the second expandable heat radiator, the second upper horizontal plate pre-buried heat pipe and the second lower horizontal plate pre-buried heat pipe.

[0019] In the above-mentioned common platform double fluid circuit system, the first deployable heat radiator and the second deployable heat radiator both adopt an aluminum skin aluminum honeycomb core structure; heat pipes are embedded inside the first deployable heat radiator and the second deployable heat radiator, which are in a folded state when the satellite is launched and are pressed against the south plate and the north plate of the satellite payload cabin respectively, and are deployed in orbit through unlocking, unfolding and reliable locking of mechanical joint hinges, thereby increasing the illuminated heat dissipation surface of the outer surface of the south plate and the north plate of the satellite payload cabin.

[0020] The beneficial effects of the present invention compared with the prior art are:

[0021] (1) The present invention installs a double fluid circuit system on the payload cabin structural plate of the existing platform satellite to achieve isothermal design inside the satellite body, collect the heat loss generated by the internal structural plate of the satellite body, and dissipate it to the outside of the satellite body through the fluid circuit heat pipe and heat dissipation surface. A deployable radiator is configured in the fluid circuit system. The heat radiator can be mechanically deployed according to demand during the in-orbit stage to increase the heat dissipation surface of the entire satellite and dissipate heat;

[0022] (2) The present invention combines the actual design of the satellite and its on-orbit status. During the on-orbit phase, the north and south panels of the satellite are alternately irradiated with seasonal changes. Therefore, the deployable radiator is symmetrically arranged in the north and south directions of the payload cabin, thereby reducing the impact of external heat flux changes on the heat dissipation of the system. At the same time, the thermal coupling of the north and south panels of the satellite can be achieved, and the temperature in the satellite payload cabin can be uniformed.

[0023] (3) The fluid circuit system of the present invention is a thermal control system that integrates heat collection, transfer, and dissipation. The two sets of fluid circuit system products are exactly the same in structure. The difference is that the fluid circuit heat pipes pass through different areas, resulting in different areas of the upper and lower horizontal plates when collecting heat, and different heat radiators used when dissipating heat, which increases the heat dissipation performance of the structural plate in the load compartment.

[0024] (4) Under the premise of meeting the overall heat dissipation requirements of the satellite, the present invention sets up a double fluid circuit system for different heat dissipation areas in the satellite payload cabin. The layout position of the double fluid circuit system in the satellite payload cabin is symmetrical along the horizontal direction of the satellite. The changes in the weight and torque inside the satellite caused by the unidirectional flow of the working fluid in the pipeline can offset each other. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is an overall schematic diagram of the double fluid circuit system of the present invention;

[0026] Figure 2 This is a schematic diagram of the installation position of the first fluid circuit system of the present invention;

[0027] Figure 3 This is a schematic diagram of the installation position of the second fluid circuit system of the present invention;

[0028] Figure 4 It is a schematic diagram of the path of the working medium circulation loop of the first / second fluid loop system of the present invention. DETAILED DESCRIPTION

[0029] The present invention will be further described below in conjunction with the embodiments.

[0030] The present invention proposes a dual fluid circuit system for a common platform, including various products required for the dual fluid circuit system of the common platform. The dual fluid circuit systems are both installed on the satellite payload cabin structural plate. According to the fluid circuit system composition diagram, the specific composition of the dual fluid circuit system is decomposed and explained. The layout position of the dual fluid circuit system (hereinafter referred to as the first fluid circuit system and the second fluid circuit system) in the satellite payload cabin is symmetrical along the horizontal direction of the satellite, and the internal weight change and torque change of the satellite caused by the unidirectional flow of the working fluid in the pipeline can offset each other.

[0031] The layout of the dual fluid circuit system in the satellite payload compartment is as follows: Figure 1As shown, the satellite payload cabin body coordinate system (O-XYZ) is established and defined as follows:

[0032] Coordinate origin O: Figure 1 As shown, the center point of the center partition on the lower side of the satellite payload compartment;

[0033] +Z axis: Figure 1 As shown in the figure, +Z direction is the direction from the lower horizontal plate of the load cabin to the upper horizontal plate of the load cabin;

[0034] +Y axis: Figure 1 As shown in the figure, the +Y direction is from the north plate of the load cabin to the south plate of the load cabin;

[0035] +X axis: Figure 1 As shown, the +Y axis and +Z axis conform to the right-hand rule.

[0036] The double fluid circuit system of the common platform specifically includes a first fluid circuit system and a second fluid circuit system; wherein, the first fluid circuit system includes a first pump valve assembly 1, a first fluid circuit heat pipe 3, a first expandable heat radiator 5, a first upper horizontal plate pre-buried heat pipe 71 and a first lower horizontal plate pre-buried heat pipe 81; the second fluid circuit system includes a second pump valve assembly 2, a second fluid circuit heat pipe 4, a second expandable heat radiator 6, a second upper horizontal plate pre-buried heat pipe 72 and a second lower horizontal plate pre-buried heat pipe 82.

[0037] like Figure 2 As shown, the first pump-valve assembly 1 is installed at the bottom of the lower horizontal plate 12 of the satellite payload cabin; the first deployable heat radiator 5 is arranged on the south plate 9 of the satellite payload cabin; the first upper horizontal plate pre-buried heat pipe 71 is horizontally installed on the upper horizontal plate 11 of the satellite payload cabin; the first lower horizontal plate pre-buried heat pipe 81 is horizontally installed on the lower horizontal plate 12 of the satellite payload cabin; the first pump-valve assembly 1, the first lower horizontal plate pre-buried heat pipe 81, the first upper horizontal plate pre-buried heat pipe 71, and the first deployable heat radiator 5 are all connected through the first fluid circuit heat pipe 3.

[0038] like Figure 3 As shown, the second pump-valve assembly 2 is installed at the bottom of the lower horizontal plate 12 of the satellite payload cabin; the second deployable heat radiator 6 is arranged on the north plate 10 of the satellite payload cabin; the second upper horizontal plate pre-buried heat pipe 72 is horizontally installed on the upper horizontal plate 11 of the satellite payload cabin; the second lower horizontal plate pre-buried heat pipe 82 is horizontally installed on the lower horizontal plate 12 of the satellite payload cabin; the second pump-valve assembly 2, the second lower horizontal plate pre-buried heat pipe 82, the second upper horizontal plate pre-buried heat pipe 72, and the second deployable heat radiator 6 are all connected through the second fluid circuit heat pipe 4.

[0039] Double fluid circuit system, each component product forms a series system, the connection relationship is as follows Figure 4As shown, the pump-valve assembly 1 / 2 is the core equipment of the fluid circuit system. Driven by the pump, it provides power for the circuit system. The working fluid flows in the heat pipe to transfer heat. It flows from the outlet of the pump-valve assembly through the fluid circuit heat pipe 3 / 4 through the pre-buried heat pipe 81 / 82 on the lower horizontal plate of the load cabin and the pre-buried heat pipe 71 / 72 on the upper horizontal plate. The heat of the equipment is collected in the heat pipe and then enters the deployable radiator 5 / 6. The deployable heat radiator is deployed in orbit to increase the heat dissipation surface and dissipate the heat to the external space. The temperature of the fluid circuit system is reduced, and the low-temperature working fluid returns to the inlet of the pump-valve assembly, and this cycle is repeated to form a circulation loop to complete the heat dissipation of the system.

[0040] The first fluid circuit system and the second fluid circuit system have the same system composition, and the first fluid circuit system and the second fluid circuit system are symmetrical relative to the center of the satellite payload cabin. The first pump-valve assembly 1 provides power for the first fluid circuit system, driving the working fluid to flow in the heat pipe of the first fluid circuit system to transfer heat; the second pump-valve assembly 2 provides power for the second fluid circuit system, driving the working fluid to flow in the heat pipe of the second fluid circuit system to transfer heat.

[0041] The first deployable thermal radiator 5 can be opened or closed by rotation relative to the south plate 9 of the satellite payload bay; the second deployable thermal radiator 6 can be opened or closed by rotation relative to the north plate 10 of the satellite payload bay; and the first deployable thermal radiator 5 and the second deployable thermal radiator 6 are symmetrical relative to the center of the satellite payload bay.

[0042] like Figure 4 As shown, the path of the working medium circulation loop in the first fluid circuit system is:

[0043] The working medium flows out under the drive of the first pump-valve assembly 1, and enters the first deployable thermal radiator 5 through the first fluid loop heat pipe 3, the first lower horizontal plate pre-buried heat pipe 81, the first fluid loop heat pipe 3, the first upper horizontal plate pre-buried heat pipe 71, and the first fluid loop heat pipe 3 in sequence; the first deployable thermal radiator 5 is deployed on track to increase the heat dissipation surface and dissipate heat to the external space; the first fluid loop system is lowered, and the low-temperature working medium flows back to the inlet of the first pump-valve assembly 1 to form a circulation loop.

[0044] Similarly, the path of the working medium circulation loop in the second fluid circuit system is:

[0045] The working medium flows out under the drive of the second pump-valve assembly 2, and enters the second deployable thermal radiator 6 through the second fluid loop heat pipe 4, the second lower horizontal plate pre-buried heat pipe 82, the second fluid loop heat pipe 4, the second upper horizontal plate pre-buried heat pipe 72, and the second fluid loop heat pipe 4 in sequence; the second deployable thermal radiator 6 is deployed on track to increase the heat dissipation surface and dissipate heat to the external space; the first fluid loop system is lowered, and the low-temperature working medium flows back to the inlet of the second pump-valve assembly 2 to form a circulation loop.

[0046] The first upper horizontal plate pre-buried heat pipe 71 and the second upper horizontal plate pre-buried heat pipe 72 are both single-row wave tube structures, and the first upper horizontal plate pre-buried heat pipe 71 and the second upper horizontal plate pre-buried heat pipe 72 are symmetrically arranged. The first lower horizontal plate pre-buried heat pipe 81 and the second lower horizontal plate pre-buried heat pipe 82 are both double-row wave tube structures, and the first lower horizontal plate pre-buried heat pipe 81 and the second lower horizontal plate pre-buried heat pipe 82 are symmetrically arranged.

[0047] The first fluid circuit heat pipe 3 and the second fluid circuit heat pipe 4 are both made of aluminum alloy 2A12, and the inner diameter of the pipe is 12 mm; the first fluid circuit heat pipe 3 is threadedly connected to the first pump valve assembly 1, the first expandable heat radiator 5, the first upper horizontal plate pre-buried heat pipe 71 and the first lower horizontal plate pre-buried heat pipe 81; the second fluid circuit heat pipe 4 is threadedly connected to the second pump valve assembly 2, the second expandable heat radiator 6, the second upper horizontal plate pre-buried heat pipe 72 and the second lower horizontal plate pre-buried heat pipe 82.

[0048] The first deployable thermal radiator 5 and the second deployable thermal radiator 6 both adopt an aluminum skinned aluminum honeycomb core structure; heat pipes are embedded inside the first deployable thermal radiator 5 and the second deployable thermal radiator 6, which are in a folded state when the satellite is launched and are respectively pressed against the south plate 9 and the north plate 10 of the satellite payload cabin, and are deployed in orbit through unlocking, unfolding and reliable locking of mechanical joint hinges, thereby increasing the illuminated heat dissipation surface of the outer surface of the south plate 9 and the north plate 10 of the satellite payload cabin.

[0049] The present invention proposes a public platform double fluid circuit system, in which each component product is connected by screw connection, specifically including: the outlet of the pump-valve assembly 1 / 2 and the fluid circuit heat pipe 3 / 4, the fluid circuit heat pipe 3 / 4 and the inlet of the lower horizontal plate pre-buried heat pipe 81 / 82, the outlet of the lower horizontal plate pre-buried heat pipe 81 / 82 and the fluid circuit heat pipe 3 / 4, the fluid circuit heat pipe 3 / 4 and the inlet of the upper horizontal plate pre-buried heat pipe 71 / 72, the outlet of the upper horizontal plate pre-buried heat pipe 71 / 72 and the fluid circuit heat pipe 3 / 4, the fluid circuit heat pipe 3 / 4 and the inlet of the deployable radiator 5 / 6, the outlet of the deployable radiator 5 / 6 and the fluid circuit heat pipe 3 / 4, and the fluid circuit heat pipe 3 / 4 and the inlet of the pump-valve assembly 1 / 2.

[0050] The detailed layout of the first fluid circuit system equipment is as follows Figure 2As shown, the first pump-valve assembly 1 is installed on the +X+Y small cabin structure plate of the lower cabin section of the payload cabin, the outlet is connected to the first fluid circuit heat pipe 3 and goes from the lower horizontal plate 12+X+Y area into the first lower horizontal plate pre-buried heat pipe 81, the first lower horizontal plate pre-buried heat pipe 81 goes to the lower horizontal plate 12-X+Y area, the outlet is connected to the first fluid circuit heat pipe 3 and goes from the upper horizontal plate 11-X+Y area into the first upper horizontal plate pre-buried heat pipe 71, the first upper horizontal plate pre-buried heat pipe 71 goes to the upper horizontal plate 11+X+Y area, the outlet is connected to the first fluid circuit heat pipe 3 and goes into the first deployable heat radiator 5, the first deployable heat radiator 5 is installed on the south plate 9 of the payload cabin, and is located on the +X+Y side of the satellite payload cabin. The outlet of the first deployable heat radiator A part 5 is connected to the first fluid circuit heat pipe 3 and goes back to the first pump-valve assembly 1 to form a circulation loop.

[0051] The detailed layout of the second fluid circuit system equipment is as follows Figure 3 As shown, the second pump-valve assembly 2 is installed on the -XY cabin structure plate of the lower cabin section of the payload cabin, the outlet is connected to the second fluid circuit heat pipe 4, and the direction is from the lower horizontal plate 12-XY area to the lower horizontal plate pre-buried heat pipe 82, and the lower horizontal plate pre-buried heat pipe 82 is directed to the lower horizontal plate 12+XY area, the outlet is connected to the second fluid circuit heat pipe 4, and the direction is from the upper horizontal plate 11+XY area to the second upper horizontal plate pre-buried heat pipe 72, and the second upper horizontal plate pre-buried heat pipe 72 is directed to the upper horizontal plate 11-XY area, the outlet is connected to the second fluid circuit heat pipe 4 and the direction is directed to the second deployable heat radiator 6, and the second deployable heat radiator 6 is installed on the north plate 10 of the payload cabin, and is located on the -XY side of the satellite payload cabin. The outlet of the second deployable heat radiator 6 is connected to the second fluid circuit heat pipe 4 and the direction is returned to the second pump-valve assembly 2, forming a circulation loop.

[0052] The present invention proposes a public platform double fluid circuit system, and the various products constituting the system are described as follows: a pump valve assembly 1 / 2 is composed of a pump, a charging and discharging valve, a filter, a pressure sensor, a manual operation valve and other components, and the materials of each component are designed separately; the material of the fluid circuit heat pipe 3 / 4 is aluminum alloy 2A12, and the inner diameter of the pipe is 12 mm, and it is screwed to the pump valve assembly 1 / 2, the lower horizontal plate embedded heat pipe 81 / 82, the upper horizontal plate embedded heat pipe 71 / 72, and the deployable heat radiator 5 / 6 embedded heat pipe; the material of the deployable radiator 5 / 6 is an aluminum skin aluminum honeycomb core structure, with embedded heat pipes, which are in a folded state and pressed against the south plate 9 and the north plate 10 of the payload cabin when the satellite is launched, and are deployed in orbit by unlocking, unfolding and reliably locking the mechanical joint hinges, thereby increasing the illuminated heat dissipation surface of the outer surfaces of the south and north plates of the satellite payload cabin.

[0053] The present invention proposes a common platform double fluid circuit system. The layout position of the double fluid circuit system in the satellite payload cabin is symmetrical along the horizontal center of the satellite. The internal weight changes and torque changes of the satellite caused by the unidirectional flow of the working fluid in the pipeline can offset each other.

[0054] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. A common platform double fluid circuit system, characterized in that: The invention comprises a first fluid circuit system and a second fluid circuit system; wherein the first fluid circuit system comprises a first pump valve assembly (1), a first fluid circuit heat pipe (3), a first deployable heat radiator (5), a first upper horizontal plate pre-buried heat pipe (71) and a first lower horizontal plate pre-buried heat pipe (81); the second fluid circuit system comprises a second pump valve assembly (2), a second fluid circuit heat pipe (4), a second deployable heat radiator (6), a second upper horizontal plate pre-buried heat pipe (72) and a second lower horizontal plate pre-buried heat pipe (82); The first pump-valve assembly (1) is installed at the bottom of the lower horizontal plate (12) of the satellite payload cabin; the first deployable heat radiator (5) is arranged on the south plate (9) of the satellite payload cabin; the first upper horizontal plate pre-buried heat pipe (71) is horizontally installed on the upper horizontal plate (11) of the satellite payload cabin; the first lower horizontal plate pre-buried heat pipe (81) is horizontally installed on the lower horizontal plate (12) of the satellite payload cabin; the first pump-valve assembly (1), the first lower horizontal plate pre-buried heat pipe (81), the first upper horizontal plate pre-buried heat pipe (71), and the first deployable heat radiator (5) are all connected via the first fluid circuit heat pipe (3); The second pump-valve assembly (2) is installed at the bottom of the lower horizontal plate (12) of the satellite payload cabin; the second deployable heat radiator (6) is arranged on the north plate (10) of the satellite payload cabin; the second upper horizontal plate pre-buried heat pipe (72) is horizontally installed on the upper horizontal plate (11) of the satellite payload cabin; the second lower horizontal plate pre-buried heat pipe (82) is horizontally installed on the lower horizontal plate (12) of the satellite payload cabin; the second pump-valve assembly (2), the second lower horizontal plate pre-buried heat pipe (82), the second upper horizontal plate pre-buried heat pipe (72), and the second deployable heat radiator (6) are all connected via the second fluid circuit heat pipe (4); The first fluid circuit system and the second fluid circuit system have the same system composition, and the first fluid circuit system and the second fluid circuit system are symmetrical relative to the center of the satellite payload compartment.

2. A common platform double fluid circuit system according to claim 1, characterized in that: The first deployable heat radiator (5) can be opened or closed by rotation relative to the south plate (9) of the satellite payload cabin; the second deployable heat radiator (6) can be opened or closed by rotation relative to the north plate (10) of the satellite payload cabin; and the first deployable heat radiator (5) and the second deployable heat radiator (6) are symmetrical relative to the center of the satellite payload cabin.

3. A common platform double fluid circuit system according to claim 1, characterized in that: The first pump-valve assembly (1) provides power for the first fluid circuit system, driving the working fluid to flow in the heat pipe of the first fluid circuit system to transfer heat; the second pump-valve assembly (2) provides power for the second fluid circuit system, driving the working fluid to flow in the heat pipe of the second fluid circuit system to transfer heat.

4. A common platform double fluid circuit system according to claim 1, characterized in that: The path of the working medium circulation loop in the first fluid circuit system is: The working fluid flows out under the drive of the first pump-valve assembly (1), and enters the first deployable heat radiator (5) in sequence through the first fluid loop heat pipe (3), the first lower horizontal plate pre-buried heat pipe (81), the first fluid loop heat pipe (3), the first upper horizontal plate pre-buried heat pipe (71), and the first fluid loop heat pipe (3); the first deployable heat radiator (5) is deployed on the track to increase the heat dissipation surface and dissipate heat to the external space; the first fluid loop system is lowered, and the low-temperature working fluid flows back to the inlet of the first pump-valve assembly (1), forming a circulation loop.

5. A common platform double fluid circuit system according to claim 1, characterized in that: The path of the working medium circulation loop in the second fluid circuit system is: The working fluid flows out under the drive of the second pump-valve assembly (2), and enters the second deployable heat radiator (6) in sequence through the second fluid loop heat pipe (4), the second lower horizontal plate pre-buried heat pipe (82), the second fluid loop heat pipe (4), the second upper horizontal plate pre-buried heat pipe (72), and the second fluid loop heat pipe (4); the second deployable heat radiator (6) is deployed on the track to increase the heat dissipation surface and dissipate heat to the external space; the first fluid loop system is lowered, and the low-temperature working fluid flows back to the inlet of the second pump-valve assembly (2), forming a circulation loop.

6. A common platform double fluid circuit system according to claim 1, characterized in that: The first upper horizontal plate pre-buried heat pipe (71) and the second upper horizontal plate pre-buried heat pipe (72) are both single-row wave tube structures; and the first upper horizontal plate pre-buried heat pipe (71) and the second upper horizontal plate pre-buried heat pipe (72) are symmetrically arranged.

7. A common platform double fluid circuit system according to claim 1, characterized in that: The first lower horizontal plate pre-buried heat pipe (81) and the second lower horizontal plate pre-buried heat pipe (82) are both double-row wave tube structures, and the first lower horizontal plate pre-buried heat pipe (81) and the second lower horizontal plate pre-buried heat pipe (82) are symmetrically arranged.

8. A common platform double fluid circuit system according to claim 1, characterized in that: The first fluid circuit heat pipe (3) and the second fluid circuit heat pipe (4) are both made of aluminum alloy 2A12, and the inner diameter of the pipe is 12 mm; the first fluid circuit heat pipe (3) is threadedly connected to the first pump valve assembly (1), the first deployable heat radiator (5), the first upper horizontal plate pre-buried heat pipe (71), and the first lower horizontal plate pre-buried heat pipe (81); the second fluid circuit heat pipe (4) is threadedly connected to the second pump valve assembly (2), the second deployable heat radiator (6), the second upper horizontal plate pre-buried heat pipe (72), and the second lower horizontal plate pre-buried heat pipe (82).

9. A common platform dual fluid circuit system according to claim 1, characterized in that: The first deployable heat radiator (5) and the second deployable heat radiator (6) both adopt an aluminum skin aluminum honeycomb core structure; heat pipes are embedded in the first deployable heat radiator (5) and the second deployable heat radiator (6), and when the satellite is launched, they are in a folded state and pressed against the satellite payload cabin south plate (9) and the satellite payload cabin north plate (10) respectively, and are deployed on-orbit by unlocking, unfolding and reliably locking the mechanical joint hinge, thereby increasing the illuminated heat dissipation surface of the outer surface of the satellite payload cabin south plate (9) and the satellite payload cabin north plate (10).

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