Integrated thermal control and space debris protection system for satellites

Abstract

The present invention relates to the field of spacecraft thermal control technology and provides an integrated satellite thermal control and space debris protection system, comprising a plurality of flexible protective layer plates arranged at the rear end and a buffer screen arranged at the front end. The buffer screen is configured as a matrix array of alloy boxes, each of which is sequentially arranged along the impact direction from front to back with an aluminum alloy plate, a polyurethane layer, a foam aluminum filling layer, a polyurethane layer, and an aluminum alloy plate. The heat source between the buffer screen and the satellite platform is connected by a flexible heat pipe. The present invention achieves an organic principle-based integration of the space debris protection system and the steam chamber device in the spacecraft thermal control system by sharing multiple key materials and structural layouts. This not only maximizes the functional characteristics of both systems, but also ensures that both systems operate at high technical standards. It also saves weight and space for the satellite platform and has strong redundancy capabilities, meeting the lightweight debris protection and thermal control requirements of future high-value satellites.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft thermal control technology, specifically, to an integrated thermal control and space debris protection system for satellites, and more particularly to a lightweight structural device that can simultaneously perform the heat dissipation function of a thermal control radiator and the space debris protection function. Background Art

[0002] The continuous expansion of human space activities has led to a rapid increase in the amount of debris in low-Earth orbit from decommissioned or inoperable spacecraft and various accidents. These uncontrolled space objects range in size from submillimeter to 10 meters and remain in orbit for long periods of time. For low-orbit spacecraft, these objects can travel at relative speeds of 3 to 15 km / s. A collision with one another poses a significant threat to active spacecraft, causing structural damage, functional failure, and even explosion and disintegration. While spacecraft protection against space debris has a long history and accumulation, existing debris protection systems are generally only installed on high-value manned spacecraft due to their large mass and limited functionality. Conventional spacecraft, such as artificial satellites and deep space probes, are currently almost completely unprotected against the threat of space debris due to weight and size constraints. Therefore, research is needed on space debris protection systems for unmanned spacecraft, such as satellites, to reduce the weight and volume burden of these systems through lightweight and multifunctional integrated designs.

[0003] Existing hybrid thermal control / space debris protection designs, such as patent document CN105109709A, disclose an integrated heat-insulating / protective space debris shielding structure. This design utilizes the low thermal conductivity of multi-layer space debris shielding structural materials to create a heat-insulating function with a relatively high operating temperature. However, heat transfer in space is primarily through radiation rather than solid conduction. The multi-layer and high-temperature multi-layer technologies used in existing spacecraft heat-insulating designs are already relatively well-developed and very lightweight, so the practical significance of this design is limited. For another example, patent document CN102941926A discloses a space debris protection thermal radiator. This design leverages the metal protection capabilities of the radiator panel, which is coupled with a fluid circuit and heat pipe, to provide a certain degree of debris protection for the spacecraft. Due to the high weight per unit area of ​​large metal panels, this type of thermal radiator can only be used on large manned spacecraft, such as space stations and manned spacecraft. For example, patent document CN108426694A discloses a simulation device and method for high-speed impact of space debris on a thermal protection structure. In addition to being used for space debris protection, the structure of this design is mainly used to resist aerodynamic heating of the spacecraft during re-entry into the atmosphere. Its function is completely different from the radiation heat dissipation effect of the present invention in a space vacuum environment.

[0004] In summary, the above hybrid or integrated designs only utilize the thermophysical properties of mechanical materials or the mechanical properties of thermal conductive materials to obtain two functions at the same time, and do not achieve an organic combination based on the basic principles. The secondary functions taken into account are not outstanding in performance, and it is difficult to meet the lightweight debris protection and thermal control requirements of future high-value satellites. Summary of the Invention

[0005] In view of the defects in the prior art, the purpose of the present invention is to provide an integrated thermal control and space debris protection system for satellites.

[0006] According to the present invention, a satellite thermal control and space debris protection integrated system includes a plurality of flexible protective layer plates arranged at the rear end and a buffer screen arranged at the front end, wherein the buffer screen is configured as a plurality of alloy boxes arranged in a matrix;

[0007] The alloy box is sequentially arranged with an aluminum alloy plate, a polyurethane layer, a foam aluminum filling layer, a polyurethane layer, and an aluminum alloy plate in the direction from front to back;

[0008] The heat source between the buffer screen and the satellite platform is connected via a flexible heat pipe.

[0009] Preferably, the two polyurethane layers arranged one behind the other are tensioned and connected by a polyurethane column.

[0010] Preferably, the alloy box is a sealed structure, and the inner side wall of each alloy box is bonded with the polyurethane layer having a porous structure, and the polyurethane layer is filled with a phase change medium.

[0011] Preferably, the flexible protective layer plate is arranged in parallel with the buffer screen and the sizes of the two are matched.

[0012] Preferably, the surfaces of the alloy boxes in each row are connected by a channel heat pipe.

[0013] Preferably, a plurality of the flexible protective layer plates are stacked and arranged, and the plurality of the flexible protective layer plates and the buffer screen are connected together by four connecting rods arranged at four corners and a rotating fixing frame.

[0014] Preferably, the multiple flexible protective layer panels have two states: expanded and folded. When the satellite is in orbit, the multiple flexible protective layer panels are adjusted to the expanded state; when the satellite is not in orbit, the multiple flexible protective layer panels are adjusted to the folded state.

[0015] Preferably, two sets of protection units are included, and both sets of protection units are installed on the windward surface to form a sharp-angle structure.

[0016] Preferably, adjacent alloy boxes are treated with thermal grease and mechanical compression.

[0017] Preferably, the flexible protective layer plate is made of one or more of carbon fiber, glass fiber, Kevlar, silicon dioxide, silicon carbide fiber, basalt fiber, or is made of any one of Betelon cloth, silicon carbide blanket, and PBO fiber.

[0018] Compared with the prior art, the present invention has the following beneficial effects:

[0019] 1. The present invention combines a front-end buffer screen with multiple flexible laminates at the rear end. The buffer screen consists of a steam chamber array and a matching heat pipe. The steam chamber uses aluminum alloy plates as a load-bearing and sealing structure, with a porous polyurethane layer as a capillary wick inside. The space outside the capillary wick is filled with foamed aluminum. The single protective screen and multiple flexible laminates form a unit. The two units are combined at a certain angle to form a wedge angle, pointing toward the windward side of the satellite's flight. A folding and unfolding mechanism can be retracted to reduce the space occupied by the rocket fairing during launch. The system is connected to the heat source on the satellite through loop heat pipes and other means, and the heat pipe array diffuses heat flow to each steam chamber. The present invention achieves an organic principle of integration by sharing multiple key materials and structural layouts for the steam chamber devices in the spacecraft thermal control system and the space debris protection system. This not only maximizes the functional characteristics of both, but also ensures that both operate at a high level of technical performance. It also saves weight and space for the satellite platform and provides strong redundancy, effectively meeting the requirements of lightweight debris protection and thermal control for future high-value satellites.

[0020] 2. The present invention has a sheet structure, and a filling-type buffer screen and multiple flexible protective layer plates are sequentially arranged along the incident impact direction of space debris. The buffer screen adopts a filling-type composite structure to enhance the protection capability, wherein the basic material of the buffer screen is 6 series aluminum alloy, which mainly plays the role of forming a debris cloud when impacted by high-speed debris. The aluminum alloy is made into a thin-walled sealed square box, and one of the filling materials on the inside of the box is a thin layer of polyurethane foam, and the other material is foam aluminum, both of which are lightweight impact protection materials. The former is closely attached to the wall of the box. In addition to generating impact protection function, it also serves as a capillary wick material and forms a steam chamber structure together with the saturated phase change working medium filled in the aluminum alloy box, thereby realizing efficient heat conduction and heat expansion functions of the aluminum alloy square box.

[0021] 3. A complete buffer screen in the present invention is composed of an array of multiple rectangular aluminum alloy boxes, which are fixedly arranged by components. A multi-layer flexible layer plate is provided at the rear end of the buffer screen, which continuously blocks and protects against space debris that breaks through the protective screen. The buffer screen and the flexible layer plate form a protective unit. In order to transfer the heat on the satellite platform to the buffer screen for dissipation, two measures are taken. First, multiple heat pipes are used to connect the aluminum alloy box array, wherein a single heat pipe connects multiple aluminum alloy boxes on each row of the array. The heat pipe and the aluminum alloy box array are pressed and filled with thermal conductive fillers to form a good thermal coupling between them. Second, flexible heat conductive pipes are used for connection, such as the condensation section or fluid loop of a loop heat pipe, to transfer the heat of the satellite platform to the heat pipe, effectively achieving the effect of thermal control and protection.

[0022] 4. The entire space debris shielding system of this invention consists of two laminated shielding units, one on the left and one on the right, positioned directly in front of the satellite's flight path. Together, these two units form a sharp angle, effectively blocking oncoming space debris with the highest relative speed and a certain yaw angle.

[0023] 5. In order to reduce the space occupied by the system during storage, transportation and launch and to avoid possible collision damage during storage and transportation, the buffer screen and flexible layer are both installed on a foldable and unfoldable mechanism and are in a folded state before the satellite enters space.

[0024] 6. In the present invention, polyurethane and foam aluminum serve as capillary wicks and heat conductors, achieving efficient heat conduction of the steam chamber and high isothermal performance of the radiator. On the other hand, they act as a buffer screen together with the aluminum alloy shell to form a composite Whipple filling structure, which, combined with the flexible layer at the rear, can play an important role in efficient debris protection. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Other features, objects and advantages of the present invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following drawings:

[0026] Figure 1 This is a schematic diagram of the unfolded form of a protective unit in the present invention.

[0027] Figure 2 This is a schematic diagram of the folded form of a protective unit in the present invention.

[0028] Figure 3 Schematic diagram of the overall structure of the buffer screen.

[0029] Figure 4 Schematic diagram of the internal structure of the aluminum alloy box and the combination of the heat pipe in the present invention.

[0030] Figure 5Schematic diagram of the distribution of the layer structure corresponding to the debris protection in the present invention along the incident direction.

[0031] Figure 6 This is a schematic diagram of a sharp-angle layout formed by combining left and right unit assemblies when the present invention is applied on a satellite platform.

[0032] Figure 7 This is a schematic diagram of the configuration of the present invention arranged on a satellite platform.

[0033] In the figure: 1-aluminum alloy plate; 2-polyurethane layer; 3-polyurethane column; 4-foam aluminum filling layer; 5-channel heat pipe; 6-alloy box; 7-buffer screen; 8-flexible protective layer plate; 9-left and right unit combination; 10-connecting rod; 11-satellite platform; 12-satellite solar sail panel. DETAILED DESCRIPTION

[0034] The present invention will be described in detail below with reference to specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those skilled in the art, several changes and improvements can be made without departing from the scope of the present invention. These all fall within the scope of protection of the present invention.

[0035] Example 1:

[0036] The present invention provides an integrated thermal control and space debris protection system for satellites, including multiple flexible protective layer plates 8 arranged at the rear end and a buffer screen 7 arranged at the front end. The buffer screen 7 is configured as a plurality of alloy boxes 6 arranged in a matrix. Adjacent alloy boxes 6 are treated with thermal grease and mechanical compression. The alloy boxes 6 are made of aluminum alloy boxes, and the surfaces of each row of aluminum alloy boxes are connected by grooved heat pipes 5.

[0037] Furthermore, the structure of the alloy box 6 is arranged in the order from front to back as an aluminum alloy plate 1, a polyurethane layer 2, a foam aluminum filling layer 4, a polyurethane layer 2, and an aluminum alloy plate 1. The two polyurethane layers 2 arranged in front and back are connected by a polyurethane column 3. The polyurethane layer 2 is filled with a phase change working medium, which is alcohol or electronic fluoride liquid.

[0038] Multiple flexible protective layer plates 8 are stacked and arranged. The flexible protective layer plates 8 are made of one or more of carbon fiber, glass fiber, Kevlar, silicon dioxide, silicon carbide fiber, basalt fiber, or any one or more of Betelon cloth, silicon carbide blanket, and PBO fiber.

[0039] In the present invention, multiple flexible protective layer panels 8 and the buffer screen 7 are connected together by rotating a fixing frame and four connecting rods 10 arranged at the four corners. The multiple flexible protective layer panels 8 have two states: expanded and folded. When the satellite is in orbit, the multiple flexible protective layer panels 8 are adjusted to the expanded state. When the satellite is not in orbit, the multiple flexible protective layer panels 8 are adjusted to the folded state.

[0040] Specifically, the integrated satellite thermal control and space debris protection system of the present invention preferably includes two sets of protection units, and both sets of protection units are installed on the windward side and form a sharp-angle structure.

[0041] The present invention's high-speed fragment impact protection is primarily based on Whipple's fragment protection principle. An aluminum alloy plate serves as a buffer screen 7 at the very front end of the protection unit. When an incident projectile strikes the buffer screen 7 at ultrahigh velocity, a strong shock wave forms between the screen and the projectile. This shock wave causes the projectile and the aluminum alloy plate to shatter, melt, vaporize, and even plasmatize, forming a debris cloud composed of both projectile and panel materials. The particle size and velocity of the debris cloud are significantly smaller than those of the original projectile, and the particles further diffuse between the buffer screen 7 and the flexible protective layer 8 at the rear end.

[0042] The rear end of the buffer screen 7 is provided with a plurality of flexible protective layer plates 8. When the debris cloud reaches the rear flexible protective layer plates 8, a large area will be formed on the rear flexible protective layer plates 8. This process changes the impact of space debris from a point source with a high energy density to a surface source with a greatly expanded area, thereby greatly reducing the degree of damage caused by the impact. After penetrating several layers of the rear flexible protective layer plates 8, the space debris will completely stop, thus achieving the function of impact protection. The buffer screen 7 in the present invention further adds a composite structure on the basis of the aluminum alloy plate, and a polyurethane layer and a foam aluminum layer are provided close to the rear side of the aluminum alloy plate to achieve a better buffering effect.

[0043] Example 2:

[0044] This embodiment is a preferred example of Embodiment 1.

[0045] In terms of heat dissipation function of the heat control and exhaust, this embodiment makes full use of the basic materials used in the debris protection function, forms a steam chamber array through the assembly design of the structure, and realizes efficient heat conduction of the entire buffer screen 7. Among them, the aluminum alloy plate 1 in the buffer screen 7 adopts a rectangular array composed of multiple sealed thin-walled aluminum alloy boxes 6, such as Figure 3 As shown, the inner wall of each aluminum alloy box 6 is tightly attached to a thin small-pore polyurethane layer 2 using an adhesive. The polyurethane layer 2 is a porous structure. The polyurethane layers 2 on the inner sides of the top and bottom aluminum alloy boxes are also tightly connected at the middle position using a polyurethane column 3. Figure 4 shown.

[0046] The industrially produced small-pore polyurethane layer 2 has good chemical compatibility with most phase change fluids, strong hydrophilicity and capillary suction force, high porosity, and good consistency of pore size distribution, making it an excellent porous medium. When the aluminum alloy box 6 is sealed and filled with saturated phase change fluid, the saturated phase change fluid combines with the polyurethane layer 2 to form a steam chamber with high thermal conductivity. The phase change fluid can be selected from substances with low vapor pressure that are compatible with polyurethane and aluminum alloy, such as alcohol, electronic fluoride liquid, etc., to reduce the structural stress requirements of the aluminum alloy box. The thinner thickness of the polyurethane layer 2 minimizes the adverse characteristics of the low thermal conductivity of polyurethane. With the help of the polyurethane column 3 in the middle position, the distance the liquid phase fluid is transported in the porous medium can be reduced, thereby reducing the overall flow resistance.

[0047] The space inside alloy box 6, excluding polyurethane layer 2, is filled with aluminum foam filling layer 4. Aluminum foam is also a structural material with excellent cushioning properties. Due to its extremely high porosity and large, interconnected pores, it does not affect the operation of the steam chamber. Both polyurethane and aluminum foam are excellent materials for impact protection. Together with the aluminum alloy, they form the protective shield and steam chamber structure.

[0048] In order to achieve good thermal coupling between the aluminum alloy boxes 6, the buffer screen 7 uses groove heat pipes 5 on the aluminum alloy box array to connect the surfaces of each box. A good thermal conductivity relationship is formed between the groove heat pipes 5 and the surface of the alloy box 6 through thermal grease and mechanical compression. Figure 4 shown.

[0049] In practice, when tiny pieces of space debris strike the aluminum alloy box's vapor chamber, only that single chamber will fail, while the other chambers in the array will continue to function normally. This redundant design ensures a long service life for both the device's space debris protection and its radiative heat dissipation thermal control functions.

[0050] In this embodiment, the present invention is along the direction of the incident debris, such as Figure 5As shown, an aluminum alloy plate 1, a polyurethane layer 2, aluminum foam 4, a polyurethane layer 2, an aluminum alloy plate 1, and multiple flexible protective layer plates 8 at the rear end are arranged in this order. The number of flexible protective layer plates 8 is no less than three, and their dimensions are approximately the same as or similar to those of the buffer screen 7. They are preferably arranged parallel to and in the same direction as the buffer screen 7. To ensure effective protection, the buffer screen 7 should be at least 5 cm thick, and the spacing between the buffer screen 7 and the adjacent flexible protective layer plate 8 should be no less than 7 cm. The spacing between two adjacent flexible protective layer plates 8 should also be no less than 7 cm. The flexible protective layer plates 8 should have a low surface density and ultra-high impact strength. To ensure that the temperature of the buffer screen 7 does not affect the satellite platform 11, the flexible protective layer plates 8 should also have low thermal conductivity and infrared absorption. Specifically, fabrics such as carbon fiber, glass fiber, Kevlar, silica, silicon carbide fiber, and basalt fiber can be considered. Other materials include Betelon cloth, silicon carbide blanket, and PBO fiber.

[0051] Regarding the application of the present invention on the satellite platform 11, two factors are mainly considered. On the one hand, the debris protection system needs to be installed on the windward side of the satellite to protect against space debris with the highest relative collision speed and the strongest destructive power. If the platform's carrying capacity allows, it is best to set up two left and right unit assemblies 9 on the windward side of the satellite to form two sets of protection units, and form a certain angle. This can not only protect against space debris that impacts head-on at a certain angle, but also increase the heat dissipation area and avoid a decrease in heat dissipation capacity when a buffer screen 7 is facing the sun. Figure 6 and Figure 7 As shown, Figure 7 The arrow in the figure indicates the flight direction of the satellite platform 11. The left and right unit assemblies 9 are arranged on the windward side of the satellite platform 11, forming a forward pointed angle, which will not interfere with the satellite's solar panels 12 and other protruding objects. The left and right unit assemblies 9 should be slightly protruding in the four directions of the upper, lower, left and right of the satellite's windward section to provide certain protection for the sides of the satellite platform 11. On the other hand, the space occupied by the protection unit needs to be considered. In each set of protection units, four connecting rods 10 are used to cooperate with the rotating fixing frame above to fix the buffer screen 7 and the flexible protective layer plate 8 to form a folding and unfolding layout in the form of a parallelogram. The rotating fixing frame can adopt the structure in the existing technology, such as using a motor to drive the rotating shaft to rotate and then drive the connecting rod 10 to move to achieve the switching between the unfolded and folded states, etc. The action process of the rotating fixing frame can also be achieved with the help of other structures in the existing technology, which will not be repeated here.

[0052] The protection unit can be deployed and locked by mechanical force after the satellite enters orbit. It can also be folded when necessary. The deployed and folded states of the protection unit are as follows: Figure 1 、 Figure 2As shown. When the protection unit is fully folded, its thickness is only slightly larger than the sum of the thickness of the buffer screen 7 and all the flexible protection layer plates 8, usually only about 0.1 meters; and the thickness of the protection unit can reach 0.4 to 0.5 meters after it is unfolded. In order to cooperate with the folding and unfolding function of the system, the satellite platform 11 needs to use a loop heat pipe or a flexible pipe of a fluid circuit to transfer the heat on the satellite platform 11 to the buffer screen 7. In addition to the space debris protection function, since the present invention assumes the important radiation heat dissipation function, the original radiation heat dissipation plate on the satellite platform 11 can be greatly reduced or even eliminated, so the replacement of the thermal control function can also improve the lightweight level of the device.

[0053] The present invention has a rectangular layer structure as a whole. Two identical layer combination units are symmetrically distributed on the left and right sides at a certain angle through a stretching and supporting mechanism, with their rectangular edges as rotation axes, and the front of the sharp corner points to the direction of the satellite's flight. The layer structure can cover the entire cross-sectional area of ​​the satellite in the direction of the satellite's flight and slightly protrude in the four directions of up, down, left and right. Along the incident impact direction of space debris, a filling-type buffer screen 7 and a plurality of flexible protective layer plates 8 are arranged in sequence, and a flexible heat pipe is provided between the filling-type protective screen 7 and the heat source on the satellite platform 11. The protective screen 7 body is composed of a plurality of rectangular aluminum alloy boxes and a plurality of heat pipes, which are formed into a rectangular array by structural fixing and supporting components. A good thermal connection is formed between the heat pipe and the aluminum alloy box by means of compression and thermal conductive fillers. A single heat pipe connects multiple aluminum alloy boxes in each row of the array. The aluminum alloy box is made of 6 series aluminum alloy material with high thermal conductivity. It is a thin-walled sealed pressure-bearing structure with a thickness of not less than 5 cm between the top plate and the bottom plate. Inside the aluminum alloy box, a thin layer of small-pore polyurethane porous foam is tightly attached to the wall surface. The top and bottom polyurethane layers 2 are also compressed and connected in the middle by polyurethane columns 3. The internal space of the aluminum alloy box is filled with large-pore aluminum foam material except for the polyurethane foam. After the structure is assembled and sealed, it is evacuated through the filling pipe connected to the aluminum alloy box, and then a low-pressure phase change medium is injected and sealed. The phase change medium is chemically compatible with polyurethane and aluminum alloy, and the filling amount is slightly more than the volume of the polyurethane material in the box. The flexible protective layer plate 8 has a low surface density and ultra-high impact strength, as well as low thermal conductivity and infrared absorption rate. There are no less than 3 pieces of it. Its outline size is the same as that of the filling-type buffer screen 7, and it is parallel to it. It is arranged at equal distances behind the buffer screen along the direction of incidence of debris. The layered structural units installed on the satellite can be folded together by a folding and unfolding mechanism when necessary to reduce the overall thickness and occupied space.

[0054] In the description of the present invention, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0055] The above describes specific embodiments of the present invention. It should be understood that the present invention is not limited to the specific embodiments described above, and that persons skilled in the art may make various changes or modifications within the scope of the claims without affecting the essence of the present invention. The embodiments of the present invention and the features of the embodiments may be combined in any manner unless there is a conflict.

Claims

1. An integrated system for thermal control and space debris protection for satellites, characterized in that: It comprises a plurality of flexible protective layer plates (8) arranged at the rear end and a buffer screen (7) arranged at the front end, wherein the buffer screen (7) is configured as a plurality of alloy boxes (6) arranged in a matrix; The alloy box (6) is sequentially arranged with an aluminum alloy plate (1), a polyurethane layer (2), a foamed aluminum filling layer (4), a polyurethane layer (2), and an aluminum alloy plate (1) in the direction from front to back; The heat source between the buffer screen (7) and the satellite platform (11) is connected via a flexible heat pipe; The alloy box (6) is a sealed structure, and the inner side wall of each alloy box (6) is bonded with the polyurethane layer (2) having a porous structure, and the polyurethane layer (2) is filled with a phase change working medium; The surfaces of the alloy boxes in each row are connected via a channel heat pipe (5).

2. The integrated satellite thermal control and space debris protection system according to claim 1, characterized in that: The two polyurethane layers (2) arranged front and back are tensioned and connected via polyurethane columns (3).

3. The integrated satellite thermal control and space debris protection system according to claim 1, characterized in that: The flexible protective layer plate (8) and the buffer screen (7) are arranged in parallel, and the sizes of the two are matched.

4. The integrated satellite thermal control and space debris protection system according to claim 1, characterized in that: The plurality of flexible protective layer plates (8) are stacked and arranged, and the plurality of flexible protective layer plates (8) and the buffer screen (7) are connected together via four connecting rods (10) arranged at four corners and a rotating fixed frame.

5. The integrated satellite thermal control and space debris protection system according to claim 4, characterized in that: The plurality of flexible protective layer plates (8) have two states: an expanded state and a folded state. When the satellite is in orbit, the plurality of flexible protective layer plates (8) are adjusted to the expanded state. When the satellite is not in orbit, the plurality of flexible protective layer plates (8) are adjusted to the folded state.

6. The integrated satellite thermal control and space debris protection system according to claim 1, characterized in that: Adjacent alloy boxes (6) are treated with thermal conductive silicone grease and mechanically pressed.

7. The integrated satellite thermal control and space debris protection system according to claim 1, characterized in that: The flexible protective layer plate (8) is made of one or more of carbon fiber, glass fiber, Kevlar, silicon dioxide, silicon carbide fiber, basalt fiber, or is made of any one of Betlen cloth, silicon carbide blanket, and PBO fiber.

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