SAR satellite structure and design method suitable for multi-satellite launch

Abstract

The application provides a SAR satellite structure and a design method suitable for multi-satellite launching, relates to the technical field of spacecraft design, and comprises a satellite main body, a solar wing, a radiation unit, an antenna substrate, a through-plate connector, a TR assembly and a semi-rigid connecting assembly. The SAR satellite structure adopts a trapezoidal cross-section configuration, fully utilizes the internal space of a rocket fairing, improves satellite networking speed, sets heat conduction units and heating units between the radiation unit and the antenna substrate and between the antenna substrate and the TR assembly, increases heat conduction between single machines while ensuring the radiation array plane flatness of the radiation unit and the installation flatness of the TR assembly, improves antenna temperature consistency, the semi-rigid connecting assembly can reduce the antenna response in the active stage, release the antenna thermal deformation, reduce the flatness change, improve the radiation array precision, and solves the problems of low space utilization rate of the existing SAR satellite, the antenna flatness being easily affected by thermal deformation and the difficulty in antenna temperature control.

Description

Technical Field

[0001] This invention relates to the field of spacecraft design technology, specifically to a SAR satellite structure and design method suitable for multi-satellite launches. Background Technology

[0002] Conventional satellite structures need to meet requirements such as single-unit layout, structural strength, thermal control and heat dissipation during design; in addition, SAR satellites also have requirements for the surface accuracy and temperature consistency of SAR antennas.

[0003] Currently, most SAR satellites adopt a cubic configuration design, which makes it difficult to adapt to the internal space of the rocket fairing to maximize space utilization. The antennas in the launch phase are folded up to the sides of the satellite through a compression and release mechanism, and then deployed in orbit through a deployment mechanism. Multiple antenna subarrays are spliced ​​together to form a complete antenna. This type of satellite configuration has a complex structure, and the introduction of compression and release mechanisms and deployment mechanisms greatly increases the satellite's development cost and failure risk. Moreover, after deployment, the antenna is in a cantilever state, and the overall flatness of the antenna is easily affected by thermal deformation, requiring a lot of energy to control the antenna temperature. Summary of the Invention

[0004] Therefore, the technical problem to be solved by the present invention is to overcome the defects in the prior art, thereby providing a SAR satellite structure and design method suitable for multi-satellite launches.

[0005] A SAR satellite structure suitable for multi-satellite launches includes: a satellite body and a solar array. The solar array is disposed on the side of the satellite body. A SAR antenna is disposed on the top of the satellite body. The width of the SAR antenna is greater than the width of the satellite body. The SAR antenna includes a radiating element, an antenna substrate, and a TR assembly arranged longitudinally. The radiating element and the TR assembly are correspondingly arranged. Mounting bosses are provided on both sides of the antenna substrate. The mounting boss on the side of the antenna substrate near the radiating element is connected to the radiating element. The mounting boss on the side of the antenna substrate near the TR assembly is connected to the TR assembly. Heat-conducting units and heating units are provided between the radiating element and the antenna substrate, and between the TR assembly and the antenna substrate. A through-plate connector is also provided on the antenna substrate. The through-plate connector is simultaneously connected to the radiating element and the TR assembly for signal transmission. The satellite body and the antenna substrate are connected by a semi-rigid connection assembly.

[0006] Furthermore, the semi-rigid connection assembly includes a semi-rigid connection seat, a rubber pad bushing, a rubber pad stop nut, a long bolt, and a rubber pad. The rubber pads are arranged in pairs inside the semi-rigid connection seat, the rubber pad stop nut is located below the semi-rigid connection seat, the outer ring of the rubber pad bushing is connected to both the rubber pad stop nut and the rubber pad, and the long bolt is connected to the inner ring of the rubber pad bushing.

[0007] Furthermore, the satellite body includes a +X plate, a +Y plate, a -X plate, and a -Y plate connected end to end. The -Y plate is provided with a solar panel clamping seat and a hinge connecting seat that are connected to the solar panels.

[0008] Furthermore, the satellite body also includes an antenna mounting top plate and a satellite-rocket connection bottom plate. The satellite-rocket connection bottom plate is located at the bottom of the satellite body and is connected to the +X plate, +Y plate, -X plate, and -Y plate. The antenna mounting top plate is located at the top of the satellite body and is connected to the +X plate, +Y plate, -X plate, and -Y plate.

[0009] Furthermore, the satellite body also includes intermediate panels, which are arranged in pairs and located inside the satellite body, dividing the satellite body into multiple parts.

[0010] Furthermore, the semi-rigid connector has mounting holes, and the antenna mounting top plate is provided with an antenna mounting base corresponding to the semi-rigid connector. The semi-rigid connector and the antenna mounting base are connected through the mounting holes.

[0011] Furthermore, a satellite connector corresponding to a long bolt is provided on the side of the antenna substrate away from the radiating element, and the satellite connector is connected to the long bolt.

[0012] Furthermore, the antenna substrate is made of an aluminum-skinned honeycomb panel.

[0013] Furthermore, the antenna mounting top plate, the star-rocket connection bottom plate, the +X plate, the -X plate, the +Y plate, the -Y plate, the intermediate cabin plate, the sail clamping seat, the hinge connecting seat, and the antenna mounting seat are all made of carbon fiber skin aluminum honeycomb sandwich panels.

[0014] The present invention also includes a SAR satellite structure design method suitable for multi-satellite launches. This method is based on a SAR satellite structure suitable for multi-satellite launches as described above. The solar array is set on the side of the satellite body. The width of the SAR antenna is designed to be greater than the width of the satellite body, so that the SAR satellite structure has a trapezoidal cross-section configuration. Mounting bosses are provided on both sides of the antenna substrate. The mounting bosses are adjusted to meet the flatness after the radiating element and TR component are installed. The mounting boss on one side is connected to the radiating element, and the mounting boss on the other side is connected to the TR component, so that the radiating element and TR component are set accordingly. Through-plate connectors are provided on the antenna substrate, so that the through-plate connectors are simultaneously connected to the radiating element and the TR component for signal connection. Heat conduction units and heating units are provided between the radiating element and the antenna substrate, and between the TR component and the antenna substrate. The satellite body and the antenna substrate are connected by a semi-rigid connection component.

[0015] The technical solution of this invention has the following advantages:

[0016] 1. This invention provides a SAR satellite structure and design method suitable for multi-satellite launches. By designing the SAR antenna width to be greater than the width of the satellite body, the SAR satellite structure adopts a trapezoidal cross-section configuration, thereby enabling the satellite to adapt to a multi-satellite launch mode and facilitating rapid satellite networking. The internal space of the rocket fairing can be divided into several fan-shaped spaces. The trapezoidal cross-section configuration can best fit the fan-shaped spaces inside the rocket fairing, maximizing the utilization of rocket space. The mounting boss provides thermal control interlayer space between the antenna substrate and the radiating element, as well as between the TR assembly and the antenna substrate. This allows for the placement of heat conduction and heating units between the antenna substrate and the radiating element, and between the TR assembly and the antenna substrate. The mounting boss also provides a good installation reference for single-unit installation, ensuring good flatness after the radiating element and TR assembly are installed. This facilitates heat conduction and dissipation while maintaining the flatness of the antenna single-unit installation reference surface. This improves the flatness of the antenna array and the temperature uniformity of the antenna subarrays, enhancing antenna heat dissipation. The satellite body and antenna substrate are connected by a semi-rigid connection component, achieving a semi-rigid connection between the antenna and the satellite. This reduces the transmission of vibration and shock to the antenna unit, lowers the antenna vibration response caused by rocket vibration during launch, and reduces the risk of antenna damage. At the same time, the semi-rigid connection can also absorb the antenna thermal deformation caused by changes in space environment temperature after the satellite enters orbit, reducing the impact on the antenna surface accuracy and flatness. The antenna adopts a "sandwich" structure design, with the radiating element and TR component distributed on both sides of the antenna substrate. This greatly reduces the impact of the processing and molding accuracy of the composite material plate itself on the surface accuracy of the antenna array, and provides sufficient space for thermal control implementation and cable laying, reducing the difficulty of thermal control and improving antenna temperature uniformity. The SAR satellite structure of this application also has the characteristics of simple structure, stable performance, and suitability for mass production, realizing an integrated design of structure and thermal control.

[0017] 2. In the technical solution provided by this invention, the carbon fiber skin aluminum honeycomb sandwich panel has the advantages of high specific strength and specific stiffness, making it suitable for application in satellite structures. The intermediate panel divides the internal structure of the satellite into multiple parts, increasing the rigidity of the satellite body while providing more mounting surfaces for individual units. The antenna substrate is made of aluminum skin honeycomb panel, and the materials of other individual units are the same as those of the antenna substrate, ensuring that the antenna structure has good overall thermal deformation consistency and avoiding problems such as local thermal deformation and large thermal stress caused by inconsistent material thermal expansion systems.

[0018] 3. In the technical solution provided by the present invention, the solar panel clamping seat and the hinge connecting seat are used to install the solar fin, so that the active section of the solar fin is in a retracted state, reducing the envelope size, and unfolding after entering the orbit to increase the solar absorption area. Attached Figure Description

[0019] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0020] Figure 1 Layout diagram of a launch vehicle carrying multiple SAR satellites of this invention;

[0021] Figure 2 This is a schematic diagram of the overall structure of the SAR satellite of this invention;

[0022] Figure 3 This is a schematic diagram of the overall structure of the satellite body of the present invention;

[0023] Figure 4 This is a schematic diagram of the internal structure of the satellite body of the present invention;

[0024] Figure 5 This is a schematic diagram of the upper surface structure of the SAR antenna of the present invention;

[0025] Figure 6 This is a schematic diagram of the lower surface structure of the SAR antenna of the present invention;

[0026] Figure 7 This is a partial enlarged view of the TR component installation of the present invention;

[0027] Figure 8 This is a partially enlarged view of the installation of the radiating unit and the through-plate connector of the present invention;

[0028] Figure 9 This is a schematic diagram of the overall structure of the semi-rigid connection component of the present invention;

[0029] Figure 10 This is a cross-sectional view of the overall structure of the semi-rigid connection component of the present invention;

[0030] Figure 11 This is an enlarged view of the antenna mounting base structure of the present invention.

[0031] Explanation of reference numerals in the attached figures:

[0032] 1-Satellite body; 101-Antenna mounting top plate; 102-Satellite-rocket connection base plate; 103-+X plate; 104--X plate; 105-+Y plate; 106--Y plate; 107-Intermediate compartment plate; 108-Sail plate clamping seat; 109-Hinge connecting seat; 110-Antenna mounting seat; 2-SAR antenna; 201-Antenna substrate; 2011-Mounting boss; 202-Radiating element; 203-TR assembly; 204-Through plate connector; 205-Satellite connector; 3-Semi-rigid connection assembly; 301-Semi-rigid connector; 302-Rubber pad bushing; 303-Rubber pad stop nut; 304-Long bolt; 305-Rubber pad; 4-Solar fin; 5-Rocket fairing; 6-Rocket mounting section. Detailed Implementation

[0033] The technical solution of the present invention will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0034] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0035] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0036] Furthermore, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0037] like Figure 1 , Figure 2 , Figure 5 , Figure 6 , Figure 7 and Figure 8 The diagram illustrates a SAR satellite structure suitable for multi-satellite launches, comprising: a satellite body 1 and a solar array 4. The solar array 4 is disposed on the side of the satellite body 1. A SAR antenna 2 is disposed above the satellite body 1. The width of the SAR antenna 2 is greater than the width of the satellite body 1. The SAR antenna 2 includes a radiating element 202, an antenna substrate 201, and a TR assembly 203 arranged longitudinally. The radiating element 202 and the TR assembly 203 are correspondingly arranged. Mounting bosses 2011 are provided on both sides of the antenna substrate 201, near the radiating element 202. A mounting boss 2011 on one side is connected to the radiating element 202. A mounting boss 2011 on the antenna substrate 201 near the TR assembly 203 is connected to the TR assembly 203. Heat-conducting units and heating units are provided between the radiating element 202 and the antenna substrate 201, and between the TR assembly 203 and the antenna substrate 201. A through-plate connector 204 is also provided on the antenna substrate 201, which is simultaneously connected to both the radiating element 202 and the TR assembly 203. The satellite body 1 and the antenna substrate 201 are connected via a semi-rigid connection component 3. The through-plate connector 204 is simultaneously connected to both the radiating element 202 and the TR component 203. Therefore, the through-plate connector 204 penetrates the antenna substrate 201, forming an electrical connection between the radiating element 202 and the TR component 203 to transmit signals. The entire SAR satellite structure is mounted on the rocket mounting section 6, located within the annular mounting space between the rocket fairing 5 and the rocket mounting section 6. The SAR antenna 2 consists of three structurally similar antenna subarrays, each containing a radiating element 202, a TR component 203, and a... The antenna substrate 201 and other individual units, including the radiating element 202 and the TR component 203 used in pairs, and the other individual units including the beam control unit, power supply and power divider, etc. Since the other individual units do not have special layout requirements, they are not specially distinguished here. The mounting boss 2011 is set at the mounting corner position of each radiating element 202 and each TR component 203. The mounting boss 2011 is assembled and processed after the antenna substrate 201 is cured, which ensures good flatness and provides a good mounting reference for the installation of individual units, reducing the change in antenna flatness caused by uneven mounting surface.

[0038] The aforementioned SAR satellite structure suitable for multi-satellite launches, by designing the width of the SAR antenna 2 to be greater than the width of the satellite body 1, creates a trapezoidal cross-section configuration for the SAR satellite structure. This allows the satellite to adapt to a multi-satellite launch mode, facilitating rapid satellite networking. The internal space of the rocket fairing 5 can be divided into several fan-shaped spaces. The trapezoidal cross-section configuration can best fit the fan-shaped spaces inside the rocket fairing 5, maximizing the utilization of rocket space. The mounting boss 2011 provides thermal control interlayer space between the antenna substrate 201 and the radiating element 202, and between the TR assembly 203 and the antenna substrate 201. This allows for the placement of heat conduction and heating units between the antenna substrate 201 and the radiating element 202, and between the TR assembly 203 and the antenna substrate 201. The mounting boss 2011 also provides a good installation reference for single-unit installation, ensuring good flatness after the radiating element 202 and the TR assembly 203 are installed. This facilitates heat conduction and dissipation while ensuring the safety of the single antenna unit. The flatness of the mounting reference surface is improved, thereby enhancing the flatness of the antenna array and the temperature uniformity of the antenna subarray, and improving antenna heat dissipation. The satellite body 1 and the antenna substrate 201 are connected by a semi-rigid connection component 3 to achieve a semi-rigid connection between the antenna and the satellite body, reducing the transmission of vibration and shock to the antenna unit, reducing the antenna vibration response caused by rocket vibration during launch, and reducing the risk of antenna damage. At the same time, the semi-rigid connection can also absorb the antenna thermal deformation caused by changes in space environment temperature after the satellite enters orbit, reducing the impact on the antenna surface accuracy and flatness. The antenna adopts a "sandwich" structure design, with the radiating element 202 and the TR component 203 distributed on both sides of the antenna substrate 201, which greatly reduces the impact of the processing and molding accuracy of the composite material plate itself on the surface accuracy of the antenna array, and provides sufficient space for thermal control implementation and cable laying, reducing the difficulty of thermal control and improving the antenna temperature uniformity. The SAR satellite structure of this application also has the characteristics of simple structure, stable performance and suitability for mass production, realizing the integrated design of structure and thermal control.

[0039] like Figure 9 and Figure 10As shown, in this embodiment, the semi-rigid connection assembly 3 includes a semi-rigid connection seat 301, a rubber pad bushing 302, a rubber pad stop nut 303, a long bolt 304, and a rubber pad 305. The rubber pads 305 are arranged in pairs inside the semi-rigid connection seat 301, and the rubber pad stop nut 303 is located below the semi-rigid connection seat 301. The outer ring of the rubber pad bushing 302 is connected to both the rubber pad stop nut 303 and the rubber pad 305. The long bolt 304 is connected to the axial hole of the inner ring of the rubber pad bushing 302. This clamps the rubber pad 305, putting it in a pre-compressed state. The semi-rigid connection assembly 3 enables a semi-rigid connection between the antenna and the satellite, reducing the transmission of vibration and impact to the antenna unit, reducing the antenna vibration response caused by rocket vibration during launch, and reducing the risk of antenna damage. At the same time, the semi-rigid connection can also absorb the antenna thermal deformation caused by changes in space environment temperature after the satellite enters orbit, reducing the impact on the antenna surface accuracy and flatness.

[0040] like Figure 3 and Figure 4 As shown, in this embodiment, the satellite body 1 includes a +X plate 103, a +Y plate 105, a -X plate 104, and a -Y plate 106 connected end to end. The -Y plate 106 is provided with a solar panel clamping seat 108 and a hinge connecting seat 109 that are connected to the solar panel 4. The solar panel 4 is designed with two wings and two folds. Both wings are installed on the satellite's -Y plate 106. The active section of the solar panel 4 is in a retracted state to reduce the envelope size. After entering orbit, the solar panel 4 unfolds to increase the solar absorption area.

[0041] like Figure 3 and Figure 4 As shown, in this embodiment, the satellite body 1 also includes an antenna mounting top plate 101 and a satellite-rocket connection base plate 102. The satellite-rocket connection base plate 102 is located at the bottom of the satellite body 1 and is connected to the +X plate 103, +Y plate 105, -X plate 104, and -Y plate 106. The antenna mounting top plate 101 is located at the top of the satellite body 1 and is connected to the +X plate 103, +Y plate 105, -X plate 104, and -Y plate 106. The antenna mounting top plate 101, the satellite-rocket connection base plate 102, the +X plate 103, the +Y plate 105, the -X plate 104, and the -Y plate 106 are assembled together to form a rectangular cross-section hexahedral satellite body 1.

[0042] like Figure 4 As shown, in this embodiment, the satellite body 1 also includes an intermediate panel 107. The paired intermediate panels 107 are located inside the satellite body 1. The intermediate panels 107 divide the internal cabin of the satellite into multiple parts, which increases the rigidity of the satellite body 1 and provides more mounting surfaces for single-unit arrangement.

[0043] like Figure 3 , Figure 9 and Figure 11 As shown, in this embodiment, the semi-rigid connector 301 has mounting holes, and the antenna mounting top plate 101 has an antenna mounting base 110 corresponding to the semi-rigid connector 301. The semi-rigid connector 301 and the antenna mounting base 110 are connected by mounting holes. The antenna mounting base 110 is used to install the semi-rigid connector assembly 3. The antenna mounting base 110 has connecting holes corresponding to the mounting holes. The semi-rigid connector 301 and the antenna mounting base 110 are connected by connecting parts to the mounting holes. In addition, in order to ensure that the antenna has a good flatness mounting reference, after the satellite body 1 is assembled, the antenna mounting base 110 needs to be processed to ensure that the antenna mounting surface composed of the antenna mounting base 110 has good initial flatness.

[0044] like Figure 6 , Figure 7 and Figure 11 As shown, in this embodiment, a satellite connector 205 corresponding to the long bolt 304 is also provided on the side of the antenna substrate 201 away from the radiation unit 202. The satellite connector 205 and the long bolt 304 are connected. A total of twelve satellite connectors 205 are arranged on the antenna substrate 201, and a total of twelve antenna mounting seats 110 are arranged on the antenna mounting top plate 101 of the satellite body 1. The satellite connectors 205 and the antenna mounting seats 110 correspond one-to-one. The satellite connectors 205 and the long bolt 304 are connected, thereby achieving a semi-rigid connection between the antenna and the satellite body through the semi-rigid connection component 3.

[0045] like Figure 8 As shown, in this embodiment, the antenna substrate 201 is made of aluminum-skinned honeycomb plate; the materials of other individual units are the same as those of the antenna substrate 201, ensuring that the antenna structure has good overall thermal deformation consistency and avoiding problems such as local thermal deformation and large thermal stress caused by inconsistent material thermal expansion systems.

[0046] like Figure 4 As shown, in this embodiment, the antenna mounting top plate 101, the satellite-rocket connection bottom plate 102, the +X plate 103, the -X plate 104, the +Y plate 105, the -Y plate 106, the intermediate cabin plate 107, the sail clamping seat 108, the hinge connecting seat 109, and the antenna mounting seat 110 are all made of carbon fiber skin aluminum honeycomb sandwich panels. Carbon fiber skin aluminum honeycomb sandwich panels have the advantages of high specific strength and specific stiffness, making them suitable for use in satellite structures.

[0047] like Figure 1 , Figure 2 , Figure 5 , Figure 6 , Figure 7 and Figure 8As shown, the present invention also includes a SAR satellite structure design method suitable for multi-satellite launches. This method is based on a SAR satellite structure suitable for multi-satellite launches as described above. The solar array 4 is mounted on the side of the satellite body 1. The width of the SAR antenna 2 is designed to be greater than the width of the satellite body 1, making the SAR satellite structure a trapezoidal cross-section configuration. Mounting bosses 2011 are provided on both sides of the antenna substrate 201. The mounting bosses 2011 are adjusted to meet the flatness requirements after the radiating element 202 and TR assembly 203 are installed. The mounting boss on one side... The mounting boss 2011 is connected to the radiating unit 202, and the mounting boss 2011 on the other side is connected to the TR component 203, so that the radiating unit 202 and the TR component 203 are set accordingly. A through-plate connector 204 is set on the antenna substrate 201, so that the through-plate connector 204 is simultaneously connected to the radiating unit 202 and the TR component 203. A heat conduction unit and a heating unit are set between the radiating unit 202 and the antenna substrate 201 and between the TR component 203 and the antenna substrate 201. The satellite body 1 and the antenna substrate 201 are connected by a semi-rigid connection component 3.

[0048] Obviously, the above embodiments are merely illustrative examples for clear explanation and are not intended to limit the implementation. Those skilled in the art will recognize that other variations or modifications can be made based on the above description. It is neither necessary nor possible to exhaustively list all possible implementations here. However, obvious variations or modifications derived therefrom are still within the scope of protection of this invention.

Claims

1. A SAR satellite structure suitable for multiple satellite launch, comprising: The satellite main body (1) and the solar wing (4) are characterized in that the solar wing (4) is arranged on the side of the satellite main body (1), the upper side of the satellite main body (1) is provided with a SAR antenna (2), the width of the SAR antenna (2) is greater than the width of the satellite main body (1), the SAR antenna (2) comprises a radiation unit (202), an antenna substrate (201) and a TR assembly (203) arranged in sequence in the longitudinal direction, the radiation unit (202) and the TR assembly (203) are arranged correspondingly, the two sides of the antenna substrate (201) are provided with mounting bosses (2011), the mounting boss (2011) on the side of the antenna substrate (201) close to the radiation unit (202) is connected with the radiation unit (202), the mounting boss (2011) on the side of the antenna substrate (201) close to the TR assembly (203) is connected with the TR assembly (203), a heat conduction unit and a heating unit are arranged between the radiation unit (202) and the antenna substrate (201) and between the TR assembly (203) and the antenna substrate (201), a through-board connector (204) is further arranged on the antenna substrate (201), the through-board connector (204) is signal-connected with the radiation unit (202) and the TR assembly (203) at the same time, and the satellite main body (1) and the antenna substrate (201) are connected through a semi-rigid connecting assembly (3). The semi-rigid connecting assembly (3) comprises a semi-rigid connecting seat (301), a rubber pad bushing (302), a rubber pad stop nut (303), a long bolt (304) and rubber pads (305), the rubber pads (305) are arranged in pairs in the semi-rigid connecting seat (301), the rubber pad stop nut (303) is located below the semi-rigid connecting seat (301), the outer ring of the rubber pad bushing (302) is connected with the rubber pad stop nut (303) and the rubber pads (305) at the same time, and the long bolt (304) is connected with the inner ring of the rubber pad bushing (302). The satellite main body (1) further comprises an antenna mounting top plate (101). Mounting holes are formed in the semi-rigid connecting seat (301), the antenna mounting top plate (101) is provided with an antenna mounting seat (110) corresponding to the semi-rigid connecting seat (301), and the semi-rigid connecting seat (301) and the antenna mounting seat (110) are connected through the mounting holes. A satellite connecting seat (205) corresponding to the long bolt (304) is further arranged on the side of the antenna substrate (201) away from the radiation unit (202), and the satellite connecting seat (205) is connected with the long bolt (304).

2. The SAR satellite structure suitable for multi-satellite launch according to claim 1, wherein, The satellite main body (1) comprises +X plates (103), +Y plates (105), -X plates (104) and -Y plates (106) connected in sequence from the head to the tail, and the -Y plate (106) is provided with a sail plate pressing seat (108) and a hinge connecting seat (109) corresponding to the solar wing (4).

3. The SAR satellite structure suitable for multi-satellite launch according to claim 2, characterized in that, The satellite main body (1) further comprises a satellite-rocket connecting bottom plate (102) located at the bottom of the satellite main body (1), which is connected with the +X plate (103), the +Y plate (105), the -X plate (104) and the -Y plate (106).

4. The SAR satellite structure suitable for multi-satellite launch according to claim 3, characterized in that, The satellite main body (1) further comprises a middle cabin plate (107) arranged in pairs in the satellite main body (1), which separates the cabin of the satellite main body (1) into multiple parts.

5. The SAR satellite structure suitable for multi-satellite launch according to claim 1, wherein, The antenna base plate (201) is made of aluminum skin honeycomb plate.

6. The SAR satellite structure suitable for multi-satellite launch according to claim 4, wherein, The antenna mounting top plate (101), the satellite-rocket connecting bottom plate (102), the +X plate (103), the -X plate (104), the +Y plate (105), the -Y plate (106), the middle cabin plate (107), the sail plate pressing seat (108), the hinge connecting seat (109) and the antenna mounting seat (110) are all made of carbon fiber skin aluminum honeycomb sandwich plate.

7. A method for designing a SAR satellite structure suitable for multiple launch, the method being implemented by the SAR satellite structure suitable for multiple launch according to any one of claims 1 to 6, characterized in that, The solar wing (4) is arranged on the side of the satellite main body (1), the width of the SAR antenna (2) is designed to be greater than the width of the satellite main body (1), the SAR satellite structure is in trapezoidal cross-section configuration, mounting bosses (2011) are arranged on both sides of the antenna base plate (201), the mounting bosses (2011) are adjusted to meet the flatness after the radiation unit (202) and the TR assembly (203) are installed, the mounting boss (2011) on one side is connected with the radiation unit (202), and the mounting boss (2011) on the other side is connected with the TR assembly (203), so that the radiation unit (202) and the TR assembly (203) are correspondingly arranged, a through-plate connector (204) is arranged on the antenna base plate (201), the through-plate connector (204) is connected with the radiation unit (202) and the TR assembly (203) in signal, heat conducting units and heating units are arranged between the radiation unit (202) and the antenna base plate (201) and between the TR assembly (203) and the antenna base plate (201), and the satellite main body (1) and the antenna base plate (201) are connected through the semi-rigid connecting assembly (3). The satellite main body (1) further comprises a middle cabin plate (107) arranged in pairs in the satellite main body (1), which separates the cabin of the satellite main body (1) into multiple parts. The antenna base plate (201) is made of aluminum skin honeycomb plate. The antenna mounting top plate (101), the satellite-rocket connecting bottom plate (102), the +X plate (103), the -X plate (104), the +Y plate (105), the -Y plate (106), the middle cabin plate (107), the sail plate pressing seat (108), the hinge connecting seat (109) and the antenna mounting seat (110) are all made of carbon fiber skin aluminum honeycomb sandwich plate. The solar wing (4) is arranged on the side of the satellite main body (1), the width of the SAR antenna (2) is designed to be greater than the width of the satellite main body (1), the SAR satellite structure is in trapezoidal cross-section configuration, mounting bosses (2011) are arranged on both sides of the antenna base plate (201), the mounting bosses (2011) are adjusted to meet the flatness after the radiation unit (202) and the TR assembly (203) are installed, the mounting boss (2011) on one side is connected with the radiation unit (202), and the mounting boss (2011) on the other side is connected with the TR assembly (203), so that the radiation unit (202) and the TR assembly (203) are correspondingly arranged, a through-plate connector (204) is arranged on the antenna base plate (201), the through-plate connector (204) is connected with the radiation unit (202) and the TR assembly (203) in signal, heat conducting units and heating units are arranged between the radiation unit (202) and the antenna base plate (201) and between the TR assembly (203) and the antenna base plate (201), and the satellite main body (1) and the antenna base plate (201) are connected through the semi-rigid connecting assembly (3).

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