A spaceborne integrated SAR satellite platform

Abstract

An integrated spaceborne SAR satellite platform, belonging to the field of spacecraft technology, solves the problems of poor temperature uniformity of existing satellite platform mounting plates, large SAR antenna envelope, inability to meet high-precision single-unit installation requirements, and low structural strength. The platform comprises: a SAR antenna, a feed assembly, a single-unit mounting plate, an external single-unit device, an internal single-unit device, a platform main frame, and a solar sail; the platform main frame, single-unit mounting plate, and solar sail constitute the cabin; the solar sail is located below the platform main frame; the SAR antenna, feed assembly, and external single-unit device are mounted on the outer surface of the single-unit mounting plate; the internal single-unit device is mounted on the inner surface of the single-unit mounting plate; the single-unit mounting plate includes a honeycomb panel, metal gaskets, and pre-embedded heat pipes; the honeycomb panel includes a honeycomb core and a honeycomb panel skin; the metal gaskets are connected to the pre-embedded heat pipes. This invention is applicable to satellite platform spacecraft platforms, spacecraft configuration and layout design, spacecraft structural thermal control design, spacecraft on-orbit monitoring, and SAR satellite on-orbit active compensation.

Description

Technical Field

[0001] This application relates to the field of spacecraft technology, and in particular to SAR satellite platforms. Background Technology

[0002] Currently, SAR satellites consume a significant amount of power, with most of it concentrated in the feed assembly. Existing satellite platforms mostly employ a honeycomb panel structure, resulting in poor temperature uniformity of the mounting plate and deficiencies in thermal equalization and thermal deformation control. Furthermore, the thermal deformation of the feed mounting surface cannot be measured during satellite operation in orbit. Additionally, the SAR antenna's outer envelope is relatively large, leading to structural strength limitations.

[0003] Furthermore, SAR satellite feed assemblies require high flatness of the mounting surface. Since the honeycomb panels commonly used in spacecraft cannot meet the high-precision installation requirements of individual units, a 2-3mm metal shim is typically placed on the honeycomb panel. The shim is then glued to the honeycomb panel before assembly to meet the installation requirements. Figure 1 and Figure 2 As shown.

[0004] The above installation method results in a large thermal resistance between the electronic unit and the heat pipes embedded in the honeycomb panel. The temperature difference between the unit and the heat pipes is large, which affects the heat dissipation of the electronic unit and leads to poor temperature uniformity on the mounting surface of the unit and between the units.

[0005] At this point, the expression for the thermal resistance along the heat transfer path from the electronic unit to the heat pipe is:

[0006] R = R1 + R2 + R3 + R4 + R5

[0007] In the formula, R1 is the contact thermal resistance between the electronic unit casing and the metal pad, R2 is the thermal resistance of the metal pad itself, R3 is the contact thermal resistance between the metal pad and the honeycomb panel skin, R4 is the thermal resistance of the honeycomb panel skin itself, and R5 is the contact thermal resistance between the honeycomb panel skin and the embedded heat pipe. Summary of the Invention

[0008] The purpose of this invention is to solve the problems of poor temperature uniformity of existing satellite platform mounting plates, large SAR antenna envelope, inability to meet the installation requirements of high-precision single units, and low structural strength, and to provide a spaceborne integrated SAR satellite platform.

[0009] The present invention is achieved through the following technical solution. In one aspect, the present invention provides a spaceborne integrated SAR satellite platform, the platform comprising a SAR antenna, a feed assembly, a single-unit mounting plate, an external single unit, an internal single unit, a platform main frame, and a solar sail installed sequentially.

[0010] The platform's main frame, the single-unit mounting plate, and the solar sail constitute the cabin.

[0011] The solar sail is positioned below the main frame of the platform;

[0012] The SAR antenna, the feed assembly, and the external unit are mounted on the outer surface of the unit mounting plate on the outside of the cabin.

[0013] The in-cabin unit is installed on the inner surface of the unit mounting plate on the inner side of the cabin.

[0014] The single-unit mounting plate includes a honeycomb panel, metal gaskets, and pre-embedded heat pipes;

[0015] The honeycomb panel includes a honeycomb core and a honeycomb panel skin;

[0016] A honeycomb panel skin is provided between the honeycomb core and the metal gasket;

[0017] The metal gasket is connected to the pre-embedded heat pipe.

[0018] Furthermore, the pre-embedded heat pipe includes a phase change heat pipe and several ordinary heat pipes;

[0019] The vertically arranged conventional heat pipes are parallel to the vertically arranged phase change heat pipes;

[0020] The horizontally arranged conventional heat pipes intersect perpendicularly with the vertically arranged phase change heat pipes.

[0021] Furthermore, the phase change heat pipe is embedded below the feed assembly.

[0022] Furthermore, the main frame of the platform is made of carbon fiber material.

[0023] Furthermore, the embedded heat pipe and the metal gasket are bonded and fixed together using an adhesive film.

[0024] Furthermore, the solar sail includes a body-mounted solar sail and a deployable solar sail. The body-mounted solar sail is located below the main frame of the platform, and the deployable solar sail is located on both sides of the body-mounted solar sail, with a deployable heat dissipation surface on its back.

[0025] Furthermore, a high-emissivity thermal control coating is sprayed onto the unfoldable heat dissipation surface;

[0026] A heat insulation component is provided between the deployable heat dissipation surface and the solar sail.

[0027] Furthermore, the unfoldable heat dissipation surface is provided with a flexible heat pipe, which is an extension of the pre-embedded heat pipe and is an integral structure with the pre-embedded heat pipe.

[0028] Furthermore, a highly thermally conductive flexible film is provided on the unfoldable heat dissipation surface, and the highly thermally conductive flexible film is bonded to the honeycomb panel skin.

[0029] Furthermore, the platform also includes a fiber optic demodulator, a strain sensor, and a temperature sensor.

[0030] The beneficial effects of this invention are:

[0031] 1. Integrated Spaceborne Design: It integrates the load mounting plate and the platform unit mounting plate, which has a high space utilization rate and reduces the number of honeycomb panels, thus helping to reduce weight.

[0032] 2. The design of using honeycomb panels as mounting plates and carbon fiber as the main frame not only meets the installation requirements of each individual unit, but also improves the overall structural strength and rigidity. It can effectively control the amount of thermal deformation and better ensure pointing accuracy and structural stability.

[0033] 3. The deformation of the main structure is measured using strain sensors, and attitude pointing compensation is performed using satellite management software. Simultaneously, the SAR antenna can also actively adjust its beam pointing based on the feedback deformation data.

[0034] 4. Integrated Structural and Thermal Control Design: A pre-embedded heat pipe network is integrated into the single-unit mounting plate, combining the heat storage capacity of phase change heat pipes with the temperature equalization capacity of ordinary heat pipes. While meeting the design requirements for structural installation, rigidity, and strength, it also achieves the goals of temperature equalization, heat preservation, and reduced energy consumption.

[0035] 5. The unfoldable heat dissipation surface is integrated with the solar sail, which has a stronger heat dissipation capacity while saving space and weight.

[0036] 6. A layer of honeycomb skin was removed between the metal gasket used to install the unit and the pre-embedded heat pipe, reducing the contact heat transfer resistance and conduction resistance, enhancing the heat transfer between the unit and the heat pipe, and improving the temperature uniformity between the units.

[0037] This invention optimizes the shortcomings of traditional honeycomb plate satellite platforms in terms of thermal balance and thermal deformation control, while improving the overall structural strength, reducing the thermal resistance between electronic units and pre-embedded heat pipes in spacecraft that have high requirements for installation flatness, enhancing heat dissipation of individual units, and improving the temperature uniformity between individual units.

[0038] This invention is applicable to spacecraft platform, spacecraft configuration and layout design, spacecraft structural thermal control design, spacecraft on-orbit monitoring, and SAR satellite on-orbit active compensation. Attached Figure Description

[0039] To more clearly illustrate the technical solution of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, for those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0040] Figure 1 Schematic diagram of the traditional heat pipe pre-embedded principle Figure 1 ;

[0041] Figure 2 Schematic diagram of the traditional heat pipe pre-embedded principle Figure 2 ;

[0042] Figure 3 This is a schematic diagram of the integrated spaceborne SAR satellite platform structure of the present invention;

[0043] Figure 4 This is an exploded view of the spaceborne integrated SAR satellite platform of the present invention;

[0044] Figure 5 This is a schematic diagram of the strain sensor arrangement according to the present invention;

[0045] Figure 6 This is a schematic diagram showing the arrangement of the pre-embedded heat pipes on the single-unit mounting plate of the present invention;

[0046] Figure 7 This is a schematic diagram of the unfoldable heat dissipation surface of the present invention. Figure 1 ;

[0047] Figure 8 This is a schematic diagram of the unfoldable heat dissipation surface of the present invention. Figure 2 ;

[0048] Figure 9 This is a schematic diagram of the assembly of a single-unit mounting plate;

[0049] Figure 10 Detailed diagram of the single-unit mounting plate structure. Detailed Implementation

[0050] Embodiments of the present invention are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, and should not be construed as limiting the present invention.

[0051] Implementation Method 1: A spaceborne integrated SAR satellite platform, the platform comprising a SAR antenna, a feed assembly, a single-unit mounting plate, an external single unit, an internal single unit, a platform main frame, and a solar sail installed sequentially.

[0052] The platform's main frame, the single-unit mounting plate, and the solar sail constitute the cabin.

[0053] The solar sail is positioned below the main frame of the platform;

[0054] The SAR antenna, the feed assembly, and the external unit are mounted on the outer surface of the unit mounting plate on the outside of the cabin.

[0055] The in-cabin unit is installed on the inner surface of the unit mounting plate on the inner side of the cabin.

[0056] The single-unit mounting plate includes a honeycomb panel, metal gaskets, and pre-embedded heat pipes;

[0057] The honeycomb panel includes a honeycomb core and a honeycomb panel skin;

[0058] A honeycomb panel skin is provided between the honeycomb core and the metal gasket;

[0059] The metal gasket is connected to the pre-embedded heat pipe.

[0060] In this embodiment, the single-unit mounting plate serves as both the SAR payload mounting plate and the satellite platform mounting plate. This integrated spaceborne design combines the payload single-unit mounting plate and the platform single-unit mounting plate, making more efficient use of the overall satellite installation space and reducing the overall satellite weight. The integrated spaceborne design results in high space utilization and low weight.

[0061] The platform in this embodiment reduces the thermal resistance between the unit and the heat pipe, thus enhancing the heat dissipation of the unit. The low thermal resistance heat pipe pre-embedding method requires minimal changes to existing production processes, is easy to implement, enhances heat transfer at minimal cost, and has little impact on structural strength.

[0062] Implementation Method Two: This implementation method further defines the spaceborne integrated SAR satellite platform described in Implementation Method One. In this implementation method, the pre-embedded heat pipe is further defined, specifically including:

[0063] The pre-embedded heat pipes include phase change heat pipes and several ordinary heat pipes;

[0064] The vertically arranged conventional heat pipes are parallel to the vertically arranged phase change heat pipes;

[0065] The horizontally arranged conventional heat pipes intersect perpendicularly with the vertically arranged phase change heat pipes.

[0066] This implementation method features an integrated structural and thermal control design, which ensures good temperature uniformity of the single-unit mounting plate. The phase change heat pipe provides insulation for the mounting plate, thereby reducing the overall energy consumption of the satellite.

[0067] Implementation Method 3 is a further definition of the spaceborne integrated SAR satellite platform described in Implementation Method 2. In this implementation method, the phase change heat pipe is further defined, specifically including:

[0068] The phase change heat pipe is embedded below the feed assembly.

[0069] In this embodiment, when the feed assembly is operating, the phase change heat pipes absorb the heat generated by the feed assembly during high-power operation using their phase change heat storage capacity and then slowly release it. This heat is then transferred to the entire mounting plate through a crisscrossing network of heat pipes. This integrated mechanical and thermal design balances the temperature of the entire mounting plate while simultaneously insulating it, thereby reducing the overall energy consumption of the satellite. Figure 6 As shown.

[0070] Implementation Method Four: This implementation method further defines the spaceborne integrated SAR satellite platform described in Implementation Method One. In this implementation method, the main framework of the platform is further defined, specifically including:

[0071] The main frame of the platform is made of carbon fiber.

[0072] In this embodiment, the main frame of the platform is made of carbon fiber, and the single-unit mounting plate is a honeycomb structure. It is connected to the main frame through multiple connecting embedded parts. Utilizing the high thermal stability and high strength of carbon fiber, the carbon fiber main frame can effectively control the amount of thermal deformation, thereby better ensuring pointing accuracy and structural stability.

[0073] Implementation method five is a further definition of the spaceborne integrated SAR satellite platform described in implementation method one. In this implementation method, the connection method between the pre-embedded heat pipe and the metal gasket is further defined, specifically including:

[0074] The embedded heat pipe is bonded and fixed to the metal gasket using adhesive film.

[0075] In this embodiment, the honeycomb panel covering between the metal gasket and the upper surface of the embedded heat pipe is removed, and the metal gasket and the embedded heat pipe are directly glued together, reducing one layer of contact heat transfer resistance and conduction resistance. Simultaneously, the metal gasket, as a mounting surface, can be precision machined to ensure the flatness of the mounting surface and the positional accuracy of the mounting holes, which is more conducive to ensuring the focal length accuracy of the SAR payload. For example... Figure 6 and 7 As shown.

[0076] The "precision machining" employed can refer to traditional machining methods such as turning, milling, and drilling. Adhering metal sheets can compensate for the limitations of honeycomb panels in terms of machining capabilities.

[0077] Implementation method six is ​​a further definition of the spaceborne integrated SAR satellite platform described in implementation method one. In this implementation method, the solar sail is further defined, specifically including:

[0078] The solar sail includes a body-mounted solar sail and a deployable solar sail. The body-mounted solar sail is located below the main frame of the platform, and the deployable solar sail is located on both sides of the body-mounted solar sail, with a deployable heat dissipation surface on the back.

[0079] In this embodiment, to accommodate higher power SAR payloads, a deployable heat dissipation surface is provided on the back of the deployed solar sail to conduct heat from the cellular mounting plate to the heat dissipation surface.

[0080] The integrated design of the deployable heat dissipation surface and the deployable solar sail provides enhanced heat dissipation while saving space and weight.

[0081] Implementation method seven is a further definition of the spaceborne integrated SAR satellite platform described in implementation method six. In this implementation method, the deployable heat dissipation surface is further defined, specifically including:

[0082] A high-emissivity thermal control coating is sprayed onto the unfoldable heat dissipation surface;

[0083] A heat insulation component is provided between the deployable heat dissipation surface and the solar sail.

[0084] In this embodiment, a high emissivity thermal control coating is sprayed onto the deployable heat dissipation surface to ensure efficient heat dissipation. Due to solar radiation, the solar sail has a high temperature level. To avoid affecting the temperature of the heat dissipation surface, the heat dissipation surface and the solar sail are thermally insulated. The heat dissipation surface can be made of a high thermal conductivity material, such as, but not limited to, aluminum alloy, copper, high thermal conductivity carbon nanotube film, high thermal conductivity graphene film, etc.

[0085] Implementation method eight is a further definition of the spaceborne integrated SAR satellite platform described in any one of implementation methods six or seven. In this implementation method, the deployable heat dissipation surface is further defined, specifically including:

[0086] The unfoldable heat dissipation surface is provided with a flexible heat pipe, which is an extension of the pre-embedded heat pipe and is an integral structure with the pre-embedded heat pipe.

[0087] In this embodiment, the heat on the honeycomb mounting plate is transferred using a flexible heat pipe (such as...). Figure 7 (As shown) is directed to the heat dissipation surface.

[0088] Implementation method nine is a further definition of the spaceborne integrated SAR satellite platform described in any one of implementation methods six or seven. In this implementation method, the deployable heat dissipation surface is further defined, specifically including:

[0089] A highly thermally conductive flexible film is provided on the unfoldable heat dissipation surface, and the highly thermally conductive flexible film is bonded to the honeycomb panel skin.

[0090] In this embodiment, the heat on the honeycomb mounting plate is dissipated using a highly thermally conductive flexible thin film material (e.g., but not limited to: highly thermally conductive carbon nanotube film, highly thermally conductive graphene film, etc.). Figure 8 (As shown) is directed to the heat dissipation surface.

[0091] Implementation method ten is a further definition of the spaceborne integrated SAR satellite platform described in implementation method one. In this implementation method, the platform is further defined, specifically including:

[0092] The platform also includes a fiber optic demodulator, a strain sensor, and a temperature sensor.

[0093] In this embodiment, addressing the issue that traditional SAR satellites cannot measure feed thermal deformation on-orbit, this design uses a fiber optic grating demodulator and strain and temperature sensors to measure the deformation of the main structure. Attitude and pointing compensation can then be performed via satellite management software, and the SAR antenna can also adjust its beam pointing based on the feedback deformation data. This design possesses the capability to detect structural accuracy, monitor overall satellite health, and enhance active adaptive capabilities while the satellite is in orbit. The sensor arrangement is as follows... Figure 5 As shown.

[0094] This implementation method can autonomously adjust attitude and actively adjust beam pointing based on on-orbit strain data.

[0095] Implementation method eleven, this implementation method is an embodiment of a spaceborne integrated SAR satellite platform as described above, specifically including:

[0096] This embodiment designs a spaceborne integrated SAR satellite platform, the specific structural form of which is as follows: Figure 3 and Figure 4 As shown.

[0097] The platform's main frame is the primary load-bearing structure. Individual unit mounting plates are installed on top of the main frame, and body-mounted solar sails are installed below. Deployed solar sails are connected to both sides of the body-mounted solar sails. The individual unit mounting plates are made of honeycomb panels with pre-embedded heat pipes inside. The space enclosed by the platform's main frame, individual unit mounting plates, and body-mounted solar sails is called the internal space. All individual units are located within this internal space.

[0098] The SAR antenna and feed assembly are mounted separately as discrete components on a single-unit mounting plate. This single-unit mounting plate serves as both a SAR payload mounting plate and a satellite platform mounting plate. The inner side of the single-unit mounting plate primarily houses the platform unit, while the outer side primarily houses the feed assembly and other payload units, as well as the SAR payload antenna. This integrated spaceborne design combines the payload and platform single-unit mounting plates, making more efficient use of the overall satellite installation space and reducing the overall satellite weight. The platform's main frame is made of carbon fiber, and the single-unit mounting plate has a honeycomb structure, connected to the main frame via multiple embedded connectors. Utilizing the high thermal stability and strength of carbon fiber, the amount of thermal deformation can be effectively controlled, better ensuring pointing accuracy and structural stability. Figure 3 and Figure 4 As shown.

[0099] To address the limitation of traditional SAR satellites in measuring feed thermal deformation in orbit, this design utilizes a fiber Bragg grating demodulator and strain and temperature sensors to measure the deformation of the main structure. Attitude and pointing compensation can then be performed via satellite management software, and the SAR antenna can adjust its beam pointing based on the feedback deformation data. This design provides capabilities for structural accuracy monitoring, overall satellite health monitoring, and enhanced active adaptive capabilities while the satellite is in orbit. The sensor arrangement is as follows: Figure 5 As shown, arrange them in a row.

[0100] A crisscrossing heat pipe network is pre-embedded inside the single-unit mounting plate. The upper and lower surfaces of the heat pipes are attached to the honeycomb panel skin or metal gaskets, and there are honeycomb cores on both sides of the heat pipes. The heat pipe network includes both high-capacity phase-change heat pipes and ordinary heat pipes. The phase-change heat pipes are pre-embedded under the high-power feed assembly, and the pre-embedding direction is consistent with the arrangement direction of the feed assembly. Due to the limitation of heat pipe profile length, there may not be a single phase-change heat pipe, but the total pre-embedded length is not less than the arrangement length of the feed assembly. This arrangement uses the fewest phase-change heat pipes, effectively reducing costs. Vertically, ordinary heat pipes and phase-change heat pipes are arranged parallel to each other. Horizontally, ordinary heat pipes and phase-change heat pipes are arranged perpendicularly and intersectingly. Heat pipes are fixed to metal gaskets, honeycomb panel skins, and heat pipes themselves using adhesive film.

[0101] When the feed assembly is operating, the phase change heat pipes absorb the heat generated by the feed assembly during high-power operation through their phase change heat storage capacity and then slowly release it. This heat is then transferred to the entire mounting plate through a crisscrossing network of heat pipes. This integrated mechanical and thermal design evens out the temperature of the entire mounting plate while simultaneously insulating it, thus reducing the overall energy consumption of the satellite. Figure 6 As shown.

[0102] To accommodate higher-power SAR payloads, a deployable heat dissipation surface is installed on the back of the deployed solar sail, and heat from the honeycomb mounting plate is dissipated using flexible heat pipes (such as...). Figure 7(as shown) or highly thermally conductive flexible thin film materials (e.g., but not limited to: highly thermally conductive carbon nanotube films, highly thermally conductive graphene films, such as...) Figure 8 (As shown) The heat is directed to the heat dissipation surface. The flexible heat pipe is an extension of the pre-embedded heat pipe and is an integral structure with the pre-embedded heat pipe. A high thermal conductivity film is pasted onto the honeycomb panel skin.

[0103] It should be noted that the solar sail is in a retracted state before the satellite is launched into orbit, and then unfolds again after entering orbit. The heat dissipation surface and the unfolded solar sail are an integrated structure, hence the name "deployable heat dissipation surface".

[0104] To ensure efficient heat dissipation, a high-emissivity thermal control coating is sprayed onto the heat dissipation surface. Due to solar radiation, the solar sail reaches a high temperature. To prevent this from affecting the temperature of the heat dissipation surface, the surface is thermally insulated from the solar sail, and multiple layers of thermal insulation components separate the solar sail and the heat dissipation surface. The heat dissipation surface is made of highly thermally conductive materials, such as, but not limited to, aluminum alloys, copper, highly thermally conductive carbon nanotube films, and highly thermally conductive graphene films.

[0105] like Figure 9 and Figure 10 As shown, this embodiment proposes removing the honeycomb panel covering between the metal gasket and the upper surface of the embedded heat pipe, and directly adhesive-bonding the metal gasket to the embedded heat pipe, reducing one layer of contact heat transfer resistance and conduction resistance. Simultaneously, the metal gasket, as a mounting surface, can be precision-machined to ensure the flatness of the mounting surface and the positional accuracy of the mounting holes, which is more conducive to ensuring the focal length accuracy of the SAR payload. Figure 6 and Figure 7 As shown.

[0106] After adopting the spaceborne integrated SAR satellite platform of the present invention, the expression for the thermal resistance between the unit and the heat pipe is:

[0107] R = R1 + R2 + R3

[0108] In the formula, R1 is the contact thermal resistance between the electronic unit casing and the metal pad, R2 is the thermal resistance of the metal pad itself, and R3 is the contact thermal resistance between the metal pad and the embedded heat pipe.

[0109] Compared with traditional satellite platforms, the thermal resistance of the spaceborne integrated SAR satellite platform of this invention does not include the thermal conductivity R4 of the honeycomb panel skin itself and the contact thermal transfer R5 between the honeycomb panel skin and the pre-embedded heat pipe. This reduces the overall thermal resistance, improves the temperature uniformity of the entire mounting surface, and enhances the heat dissipation of the unit.

Claims

1. A spaceborne integrated SAR satellite platform, characterized in that, The platform includes a SAR antenna, a feed assembly, a single-unit mounting plate, an external single unit, an internal single unit, a platform main frame, and a solar sail, which are installed sequentially. The platform's main frame, the single-unit mounting plate, and the solar sail constitute the cabin. The solar sail is positioned below the main frame of the platform; The SAR antenna, the feed assembly, and the external unit are mounted on the outer surface of the single-unit mounting plate on the outside of the cabin. The in-cabin unit is installed on the inner surface of the unit mounting plate on the inner side of the cabin. The single-unit mounting plate includes a honeycomb panel, metal gaskets, and pre-embedded heat pipes; The honeycomb panel includes a honeycomb core and a honeycomb panel skin; A honeycomb panel skin is provided between the honeycomb core and the metal gasket; A layer of honeycomb skin was removed between the metal gasket and the embedded heat pipe; The metal gasket is connected to the pre-embedded heat pipe; The pre-embedded heat pipes include phase change heat pipes and several ordinary heat pipes; The vertically arranged conventional heat pipes are parallel to the vertically arranged phase change heat pipes; Horizontally arranged conventional heat pipes intersect vertically with vertically arranged phase change heat pipes. The phase change heat pipe is embedded below the feed assembly; The platform also includes a fiber optic demodulator, a strain sensor, and a temperature sensor; The deformation of the main structure is measured by a fiber optic demodulator and strain and temperature sensors. Attitude pointing compensation can then be performed by satellite software. At the same time, the SAR antenna can also adjust the beam pointing based on the feedback deformation data.

2. The spaceborne integrated SAR satellite platform according to claim 1, characterized in that, The main frame of the platform is made of carbon fiber.

3. The spaceborne integrated SAR satellite platform according to claim 1, characterized in that, The embedded heat pipe is bonded and fixed to the metal gasket using adhesive film.

4. The spaceborne integrated SAR satellite platform according to claim 1, characterized in that, The solar sail includes a body-mounted solar sail and a deployable solar sail. The body-mounted solar sail is located below the main frame of the platform, and the deployable solar sail is located on both sides of the body-mounted solar sail, with a deployable heat dissipation surface on the back.

5. The spaceborne integrated SAR satellite platform according to claim 4, characterized in that, A high-emissivity thermal control coating is sprayed onto the unfoldable heat dissipation surface; A heat insulation component is provided between the deployable heat dissipation surface and the solar sail.

6. A spaceborne integrated SAR satellite platform according to any one of claims 4 or 5, characterized in that, The unfoldable heat dissipation surface is provided with a flexible heat pipe, which is an extension of the pre-embedded heat pipe and is an integral structure with the pre-embedded heat pipe.

7. A spaceborne integrated SAR satellite platform according to any one of claims 4 or 5, characterized in that, A highly thermally conductive flexible film is provided on the unfoldable heat dissipation surface, and the highly thermally conductive flexible film is bonded to the honeycomb panel skin.

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