SAR (Synthetic Aperture Radar) satellite structure suitable for multi-satellite launching and design method

Abstract

The invention provides an SAR satellite structure suitable for multi-satellite launching and a design method, and relates to the technical field of spacecraft design, the SAR satellite structure comprises a satellite main body, a solar wing, a radiation unit, an antenna substrate, a plate penetrating connector, a TR assembly and a semi-rigid connection assembly, the SAR satellite structure adopts a trapezoidal cross section configuration, the internal space of a rocket fairing is fully utilized, and the space of the rocket fairing is fully utilized; a heat conduction unit and a heating unit are arranged between the radiation unit and the antenna substrate and between the antenna substrate and the TR assembly, so that the radiation array plane flatness of the radiation unit and the installation flatness of the TR assembly are ensured, heat conduction between single machines is increased, and the temperature consistency of the antenna is improved; the semi-rigid connection assembly can reduce the response of the active section antenna, release the thermal deformation of the antenna, reduce the flatness change, improve the precision of a radiation array plane, and solve the problems that the space utilization rate of an existing SAR satellite is low, the flatness of the antenna is easily affected by thermal deformation, and the temperature of the antenna is difficult to control.

Description

Technical Field

[0001] The present invention relates to the technical field of spacecraft design, and in particular to a SAR satellite structure and a design method suitable for multi-satellite launch. Background Art

[0002] Conventional satellite structures must meet requirements such as single-machine layout, structural strength, thermal control and heat conduction, and heat dissipation during design. In addition, SAR satellites also have requirements for the shape accuracy and temperature consistency of the SAR antenna.

[0003] Currently, most SAR satellites adopt a cubic configuration design, which is difficult to adapt to the internal space of the rocket fairing to maximize space utilization. The launch antenna is folded on both sides of the satellite through a compression and release mechanism. After being in orbit, the antenna is unfolded by a deployment mechanism. Multiple antenna sub-arrays are spliced ​​into a complete antenna. The configuration structure of this type of satellite is complex. The introduction of the compression and release mechanism and the deployment mechanism greatly increases the development cost and failure risk of the satellite; and after unfolding, the antenna is in a cantilever state. The overall flatness of the antenna is easily affected by thermal deformation, and it takes more energy to control the temperature of the antenna. 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 launch.

[0005] A SAR satellite structure suitable for multi-satellite launch comprises: a satellite body and a solar wing, wherein the solar wing is arranged on the side of the satellite body, a SAR antenna is arranged above the satellite body, the width of the SAR antenna is greater than the width of the satellite body, the SAR antenna comprises a radiation unit, an antenna substrate and a TR component which are arranged in sequence longitudinally, the radiation unit and the TR component are arranged correspondingly, mounting bosses are arranged on both sides of the antenna substrate, the mounting boss on the antenna substrate close to the radiation unit is connected to the radiation unit, the mounting boss on the antenna substrate close to the TR component is connected to the TR component, a heat conduction unit and a heating unit are arranged between the radiation unit and the antenna substrate, and between the TR component and the antenna substrate, a through-board connector is also arranged on the antenna substrate, the through-board connector is simultaneously connected to the radiation unit and the TR component signals, and the satellite body and the antenna substrate are connected via a semi-rigid connection component.

[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 in 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 simultaneously cooperated and connected with the rubber pad stop nut and the rubber pad, and the long bolt is cooperated and connected with the inner ring of the rubber pad bushing.

[0007] Furthermore, the satellite body comprises a +X plate, a +Y plate, a -X plate and a -Y plate which are connected in sequence end to end, and the -Y plate is provided with a sailboard pressing seat and a hinge connection seat which are connected to the solar wing correspondingly.

[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 the satellite-rocket connection bottom plate is simultaneously connected to the +X plate, +Y plate, -X plate and -Y plate, and the antenna mounting top plate is located at the top of the satellite body, and the antenna mounting top plate is simultaneously connected to the +X plate, +Y plate, -X plate and -Y plate.

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

[0010] Furthermore, a mounting hole is provided on the semi-rigid connection seat, an antenna mounting seat corresponding to the semi-rigid connection seat is provided on the antenna mounting top plate, and the semi-rigid connection seat and the antenna mounting seat are connected in a matching manner through the mounting hole.

[0011] Furthermore, a satellite connection seat corresponding to the long bolt is provided on one side of the antenna substrate away from the radiation unit, and the satellite connection seat is connected to the long bolt.

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

[0013] Furthermore, the antenna mounting top plate, the satellite-rocket connection bottom plate, the +X plate, the -X plate, the +Y plate, the -Y plate, the middle cabin plate, the sailboard pressing seat, the hinge connection seat and the antenna mounting seat are all made of carbon fiber skinned aluminum honeycomb sandwich panels.

[0014] The present invention also includes a SAR satellite structure design method suitable for multi-satellite launch, which is implemented based on a SAR satellite structure suitable for multi-satellite launch as described in any of the above items, wherein the solar wing is arranged 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 arranged on both sides of the antenna substrate, and the mounting bosses are adjusted to meet the flatness of the radiation unit and the TR component after installation, the mounting boss on one side is connected to the radiation unit, and the mounting boss on the other side is connected to the TR component, so that the radiation unit and the TR component are arranged correspondingly, a through-board connector is arranged on the antenna substrate, so that the through-board connector is simultaneously connected to the radiation unit and the TR component signals, a heat conduction unit and a heating unit are arranged between the radiation unit and the antenna substrate and between the TR component and the antenna substrate, and the satellite body and the antenna substrate are connected by a semi-rigid connection component.

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

[0016] 1. The present invention provides a SAR satellite structure and design method suitable for multi-satellite launch. By designing the width of the SAR antenna to be larger than the width of the satellite body, the SAR satellite structure is made into a trapezoidal cross-section configuration, thereby making the satellite adapt to the launch mode of multiple satellites with one rocket, and facilitating the rapid networking of satellites. The internal space of the rocket fairing can be divided into several spaces with fan-shaped cross-sections. The trapezoidal cross-section configuration can adapt to the fan-shaped space inside the rocket fairing to the highest degree, thereby maximizing the space utilization of the rocket. By installing the boss, a thermal control interlayer space is reserved between the antenna substrate and the radiation unit, and between the TR component and the antenna substrate, so that a heat conduction unit and a heating unit are arranged between the antenna substrate and the radiation unit, and between the TR component and the antenna substrate. The mounting boss also provides a good installation reference for single-machine installation. After the radiation unit and the TR component are installed, they have good flatness, which is convenient for heat conduction and heat dissipation, and can also ensure the flatness of the antenna single-machine installation reference surface. , thereby improving the flatness of the antenna array surface, and also improving the temperature consistency of the antenna sub-array, and enhancing the heat dissipation of the antenna; the satellite body and the antenna substrate are connected by a semi-rigid connection component to realize a semi-rigid connection between the antenna and the satellite body, reduce the vibration shock transmitted to the antenna unit, reduce the antenna vibration response caused by the rocket vibration in the launch phase, and reduce the risk of antenna damage. At the same time, the semi-rigid connection can also absorb the thermal deformation of the antenna caused by the change of space environment temperature after the satellite enters orbit, and reduce the impact on the antenna surface accuracy and flatness. The antenna adopts a "sandwich" structure design, and the radiation unit and TR components are distributed on both sides of the antenna substrate, which greatly reduces the impact of the processing and forming accuracy of the composite material plate itself on the antenna array surface accuracy, and provides sufficient space for thermal control implementation and cable laying, reduces the difficulty of thermal control, and improves the temperature consistency of the antenna. The SAR satellite structure of the present application also has the characteristics of simple structure, stable performance and suitability for mass production, realizing the integrated design of structural thermal control.

[0017] 2. In the technical solution provided by the present invention, the carbon fiber skinned aluminum honeycomb sandwich panel has the advantages of high specific strength and specific stiffness, and is suitable for application in satellite structures. The intermediate cabin panel divides the internal cabin of the satellite into multiple parts, which increases the stiffness of the satellite body while also providing more installation surfaces for single-machine layout. The antenna substrate is made of an aluminum skinned honeycomb panel, and the materials of other single machines are the same as those of the antenna substrate, ensuring that the antenna structure has good overall thermal deformation consistency and avoiding the occurrence of 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 sailboard pressing seat and the hinge connecting seat are used to install the solar wing, so that the active section of the solar wing is in a folded state, reducing the envelope size, and unfolding after entering orbit to increase the sunlight absorption area. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0020] Figure 1 A layout diagram of a carrier rocket carrying multiple SAR satellite structures of the present invention;

[0021] Figure 2 This is a schematic diagram of the overall structure of the SAR satellite of the present 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 installation of the TR component of the present invention;

[0027] Figure 8 It is a partial enlarged view of the installation of the radiation unit and the through-board connector of the present invention;

[0028] Fig. 9 It is a schematic diagram of the overall structure of the semi-rigid connection assembly of the present invention;

[0029] Fig.10 It is a cross-sectional view of the overall structure of the semi-rigid connection assembly of the present invention;

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

[0031] Description of reference numerals:

[0032] 1-satellite body; 101-antenna mounting top plate; 102-satellite-rocket connection bottom plate; 103-+X plate; 104-﹣X plate; 105-+Y plate; 106-﹣Y plate; 107-middle cabin plate; 108-sailboard clamping seat; 109-hinge connection seat; 110-antenna mounting seat; 2-SAR antenna; 201-antenna substrate; 2011-mounting boss; 202-radiation unit; 203-TR assembly; 204-through-board connector; 205-satellite connection seat; 3-semi-rigid connection assembly; 301-semi-rigid connection seat; 302-rubber pad bushing; 303-rubber pad stop nut; 304-long bolt; 305-rubber pad; 4-solar wing; 5-rocket fairing; 6-rocket carrying section. DETAILED DESCRIPTION

[0033] The technical solution of the present invention will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0034] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the 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 cannot be understood as limiting the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance.

[0035] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0036] In addition, 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 A SAR satellite structure suitable for multi-satellite launch is shown, comprising: a satellite body 1 and a solar wing 4, wherein the solar wing 4 is arranged on the side of the satellite body 1, a SAR antenna 2 is arranged 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 comprises a radiation unit 202, an antenna substrate 201 and a TR component 203 which are arranged in sequence longitudinally, the radiation unit 202 and the TR component 203 are arranged correspondingly, both sides of the antenna substrate 201 are provided with mounting bosses 2011, and the antenna substrate 201 is close to the radiation unit 202. The mounting boss 2011 on one side is connected to the radiation unit 202, the mounting boss 2011 on the antenna substrate 201 close to the TR component 203 is connected to the TR component 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 component 203 and the antenna substrate 201, and a through-board connector 204 is also arranged on the antenna substrate 201, and the through-board connector 204 is simultaneously connected to the radiation unit 202 and the TR component 203 by signal, and the satellite body 1 and the antenna substrate 201 are connected by a semi-rigid connection component 3; The through-board connector 204 is connected to the radiation unit 202 and the TR component 203 by signal at the same time, so the through-board connector 204 is in the form of penetrating the antenna substrate 201, and the radiation unit 202 and the TR component 203 are electrically connected through the through-board connector 204 to transmit the signal. The entire SAR satellite structure is installed on the rocket carrying section 6 and is located in the annular carrying space between the rocket fairing 5 and the rocket carrying section 6; the SAR antenna 2 is composed of three antenna sub-arrays with similar structures, each of which includes the radiation unit 202, the TR component 203, and the antenna substrate 201. The line substrate 201 and other single machines, wherein the radiation unit 202 and the TR component 203 are used in pairs, and other single machines include wave control units, power supplies and power dividers, etc. Since other single machines have no special layout requirements, they are not specially distinguished here. The mounting boss 2011 is set at the mounting angle position of each radiation unit 202 and each TR component 203. The mounting boss 2011 is assembled and processed after the antenna substrate 201 is solidified, which ensures good flatness, provides a good installation reference for the single machine installation, and reduces the antenna flatness change caused by the uneven mounting surface.

[0038] The above-mentioned SAR satellite structure suitable for multi-satellite launch is designed so that the width of the SAR antenna 2 is larger than the width of the satellite body 1, so that the SAR satellite structure has a trapezoidal cross-section configuration, thereby making the satellite adapt to the launch mode of multiple satellites with one rocket, and facilitating the rapid networking of satellites. The internal space of the rocket fairing 5 can be divided into several spaces with fan-shaped cross-sections. The trapezoidal cross-section configuration can adapt to the fan-shaped space inside the rocket fairing 5 to the highest degree, thereby maximizing the utilization rate of the rocket space. The mounting boss 2011 is used to leave a thermal control interlayer space between the antenna substrate 201 and the radiation unit 202 and between the TR component 203 and the antenna substrate 201, so that a heat conduction unit and a heating unit are arranged between the antenna substrate 201 and the radiation unit 202 and between the TR component 203 and the antenna substrate 201. The mounting boss 2011 also provides a good installation reference for single-machine installation. After the radiation unit 202 and the TR component 203 are installed, they have good flatness, which is convenient for heat conduction and heat dissipation while also ensuring the single-machine installation of the antenna. The flatness of the mounting reference surface is improved, thereby improving the flatness of the antenna array surface, and also improving the temperature consistency of the antenna sub-array, and enhancing the heat dissipation of the antenna; the satellite body 1 and the antenna substrate 201 are connected through a semi-rigid connection component 3 to realize a semi-rigid connection between the antenna and the satellite body, reduce the vibration shock transmitted to the antenna unit, reduce the antenna vibration response caused by the rocket vibration in the launch phase, and reduce the risk of antenna damage. At the same time, the semi-rigid connection can also absorb the thermal deformation of the antenna caused by the change of space environment temperature after the satellite enters orbit, and reduce the impact on the antenna surface accuracy and flatness. The antenna adopts a "sandwich" structure design, and the radiation unit 202 and the TR component 203 are distributed on both sides of the antenna substrate 201, which greatly reduces the impact of the processing and forming accuracy of the composite material plate itself on the antenna array surface accuracy, and provides sufficient space for thermal control implementation and cable laying, reduces the difficulty of thermal control, and improves the temperature consistency of the antenna. The SAR satellite structure of the present application also has the characteristics of simple structure, stable performance and suitability for mass production, realizing the integrated design of structural thermal control.

[0039] like Fig. 9 and Fig.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 in the semi-rigid connection seat 301, 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 simultaneously connected with the rubber pad stop nut 303 and the rubber pad 305, and the long bolt 304 is connected with the axial hole of the inner ring of the rubber pad bushing 302; the rubber pad 305 is clamped and the rubber pad 305 is in a pre-compressed state. The semi-rigid connection assembly 3 realizes a semi-rigid connection between the antenna and the satellite, reduces the transmission of vibration shock to the antenna unit, reduces the antenna vibration response caused by the vibration of the rocket in the launch phase, and reduces the risk of antenna damage. At the same time, the semi-rigid connection can also absorb the thermal deformation of the antenna caused by the change of space environment temperature after the satellite enters orbit, and reduces the influence 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 which are connected in sequence end to end. The -Y plate 106 is provided with a sailboard clamping seat 108 and a hinge connecting seat 109 which are correspondingly connected to the solar wing 4; the sailboard clamping seat 108 and the hinge connecting seat 109 are used to install the solar wing 4. The solar wing 4 is designed with two wings and two folds, and both wings are installed on the satellite body -Y plate 106. The active section of the solar wing 4 is in a retracted state to reduce the envelope size. After entering orbit, the solar wing 4 is unfolded to increase the sunlight absorption area.

[0041] like Figure 3 and Figure 4 As shown, in this embodiment, the satellite body 1 also includes an antenna installation top plate 101 and a satellite-rocket connection bottom plate 102. The satellite-rocket connection bottom plate 102 is located at the bottom of the satellite body 1, and the satellite-rocket connection bottom plate 102 is simultaneously connected to the +X plate 103, the +Y plate 105, the -X plate 104 and the -Y plate 106. The antenna installation top plate 101 is located at the top of the satellite body 1, and the antenna installation top plate 101 is simultaneously connected to the +X plate 103, the +Y plate 105, the -X plate 104 and the -Y plate 106; the antenna installation top plate 101, the satellite-rocket connection bottom plate 102, the +X plate 103, the +Y plate 105, the -X plate 104 and the -Y plate 106 are jointly spliced ​​into a hexahedral satellite body 1 with a rectangular cross-section.

[0042] like Figure 4 As shown, in this embodiment, the satellite body 1 also includes an intermediate cabin panel 107. The intermediate cabin panels 107 arranged in pairs are located inside the satellite body 1. The intermediate cabin panels 107 divide the internal cabin of the satellite into multiple parts, which increases the rigidity of the satellite body 1 while also providing more installation surfaces for single-machine layout.

[0043] like Figure 3 , Fig. 9 and Fig.11 As shown, in this embodiment, a mounting hole is provided on the semi-rigid connecting seat 301, and an antenna mounting seat 110 corresponding to the semi-rigid connecting seat 301 is provided on the antenna mounting top plate 101, and the semi-rigid connecting seat 301 and the antenna mounting seat 110 are connected through the mounting hole; the antenna mounting seat 110 is used to install the semi-rigid connecting component 3, and a connecting hole corresponding to the mounting hole is provided on the antenna mounting seat 110, and the connection between the semi-rigid connecting seat 301 and the antenna mounting seat 110 is realized by connecting the mounting hole and the connecting hole through a connecting piece. In addition, in order to ensure that the antenna has an installation reference with good flatness, after the satellite body 1 is assembled, the antenna mounting seat 110 needs to be processed to ensure that the antenna mounting surface formed by the antenna mounting seat 110 has good initial flatness.

[0044] like Figure 6 , Figure 7 and Fig.11 As shown, in this embodiment, a satellite connection seat 205 corresponding to the long bolt 304 is also provided on the side of the antenna substrate 201 away from the radiation unit 202, and the satellite connection seat 205 is connected to the long bolt 304; a total of twelve satellite connection seats 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, and the satellite connection seats 205 correspond to the antenna mounting seats 110 one by one, and the satellite connection seat 205 is connected to the long bolt 304, so that a semi-rigid connection is achieved 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 an aluminum-skinned honeycomb panel; the materials of other single units are the same as the antenna substrate 201, ensuring that the antenna structure has good overall thermal deformation consistency and avoiding the occurrence of local thermal deformation and large thermal stress problems 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 middle cabin plate 107, the sailboard clamping seat 108, the hinge connection seat 109 and the antenna mounting seat 110 are all made of carbon fiber skinned aluminum honeycomb sandwich panels; the carbon fiber skinned aluminum honeycomb sandwich panels have the advantages of high specific strength and specific stiffness, and are suitable for application 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 launch, which is implemented based on a SAR satellite structure suitable for multi-satellite launch described in any one of the above items, wherein the solar wing 4 is arranged on the side of the satellite body 1, and the width of the SAR antenna 2 is designed to be greater than the width of the satellite body 1, so that the SAR satellite structure has a trapezoidal cross-section configuration, and mounting bosses 2011 are arranged on both sides of the antenna substrate 201, and the mounting bosses 2011 are adjusted to meet the flatness of the radiation unit 202 and the TR component 203 after installation, and the mounting bosses on one side are arranged on the other side. 2011 is connected to the radiation unit 202, and the mounting boss 2011 on the other side is connected to the TR component 203, so that the radiation unit 202 and the TR component 203 are arranged correspondingly, and a through-board connector 204 is arranged on the antenna substrate 201, so that the through-board connector 204 is simultaneously connected to the radiation unit 202 and the TR component 203 signals, and a heat conduction unit and a heating unit are arranged between the radiation unit 202 and the antenna substrate 201 and between the TR component 203 and the antenna substrate 201, and the satellite body 1 and the antenna substrate 201 are connected through a semi-rigid connection component 3.

[0048] Obviously, the above embodiments are merely examples for the purpose of clear explanation, and are not intended to limit the implementation methods. For those skilled in the art, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all the implementation methods here. The obvious changes or modifications derived therefrom are still within the scope of protection of the invention.

Claims

1. A SAR satellite structure suitable for multi-satellite launch, comprising: A satellite body (1) and a solar wing (4), characterized in that the solar wing (4) is arranged on the side of the satellite body (1), a SAR antenna (2) is arranged 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) comprises a radiation unit (202), an antenna substrate (201) and a TR component (203) arranged in sequence in the longitudinal direction, the radiation unit (202) and the TR component (203) are arranged correspondingly, both sides of the antenna substrate (201) are provided with mounting bosses (2011), and the mounting bosses (2011) on the antenna substrate (201) close to the radiation unit (202) are arranged on the side of the antenna substrate (201) The antenna substrate (2011) is connected to the radiation unit (202); the mounting boss (2011) on the antenna substrate (201) close to the TR component (203) is connected to the TR component (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 component (203) and the antenna substrate (201); a through-board connector (204) is also arranged on the antenna substrate (201); the through-board connector (204) is signal-connected to the radiation unit (202) and the TR component (203); the satellite body (1) and the antenna substrate (201) are connected via a semi-rigid connection component (3).

2. A SAR satellite structure suitable for multi-satellite launch according to claim 1, characterized in that: The semi-rigid connection assembly (3) comprises 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), wherein the rubber pads (305) are arranged in pairs in the semi-rigid connection seat (301), 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 cooperatively connected with the rubber pad stop nut (303) and the rubber pad (305), and the long bolt (304) is cooperatively connected with the inner ring of the rubber pad bushing (302).

3. A SAR satellite structure suitable for multi-satellite launch according to claim 2, characterized in that: The satellite body (1) comprises a +X plate (103), a +Y plate (105), a -X plate (104) and a -Y plate (106) which are connected in sequence end to end, and the -Y plate (106) is provided with a sailboard pressing seat (108) and a hinge connection seat (109) which are connected to the solar wing (4) in correspondence.

4. A SAR satellite structure suitable for multi-satellite launch according to claim 3, characterized in that: The satellite body (1) further comprises an antenna installation top plate (101) and a satellite-rocket connection bottom plate (102); the satellite-rocket connection bottom plate (102) is located at the bottom of the satellite body (1), and the satellite-rocket connection bottom plate (102) is simultaneously connected to a +X plate (103), a +Y plate (105), a -X plate (104), and a -Y plate (106); the antenna installation top plate (101) is located at the top of the satellite body (1), and the antenna installation top plate (101) is simultaneously connected to the +X plate (103), the +Y plate (105), the -X plate (104), and the -Y plate (106).

5. A SAR satellite structure suitable for multi-satellite launch according to claim 4, characterized in that: The satellite body (1) further comprises intermediate cabin panels (107), wherein the intermediate cabin panels (107) are arranged in pairs and are located inside the satellite body (1), and the intermediate cabin panels (107) divide the cabin of the satellite body (1) into a plurality of parts.

6. A SAR satellite structure suitable for multi-satellite launch according to claim 5, characterized in that: The semi-rigid connection seat (301) is provided with a mounting hole, and the antenna mounting top plate (101) is provided with an antenna mounting seat (110) corresponding to the semi-rigid connection seat (301), and the semi-rigid connection seat (301) and the antenna mounting seat (110) are matched and connected via the mounting hole.

7. The SAR satellite structure suitable for multi-satellite launch according to claim 2, characterized in that: A satellite connection seat (205) corresponding to the long bolt (304) is also provided on the side of the antenna substrate (201) away from the radiation unit (202), and the satellite connection seat (205) and the long bolt (304) are connected.

8. The SAR satellite structure suitable for multi-satellite launch according to claim 1, characterized in that: The antenna substrate (201) is made of an aluminum-skinned honeycomb panel.

9. The SAR satellite structure suitable for multi-satellite launch according to claim 6, characterized in that: The antenna installation top plate (101), the star-rocket connection 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 sailboard pressing seat (108), the hinge connection seat (109) and the antenna installation seat (110) are all made of carbon fiber skinned aluminum honeycomb sandwich panels.

10. A method for designing a SAR satellite structure suitable for multi-satellite launch, the method being implemented based on the SAR satellite structure suitable for multi-satellite launch as claimed in any one of claims 1 to 9, characterized in that: The solar wing (4) is arranged on the side of the satellite body (1), and the width of the SAR antenna (2) is designed to be greater than the width of the satellite body (1), so that the SAR satellite structure has a trapezoidal cross-section configuration. Mounting bosses (211) are arranged on both sides of the antenna substrate (201), and the mounting bosses (211) are adjusted to meet the flatness of the radiation unit (202) and the TR component (203) after installation. The mounting boss (211) on one side is connected to the radiation unit (202), and the mounting boss (211) on the other side is connected to the TR component (203). ) are connected so that the radiation unit (202) and the TR component (203) are arranged correspondingly, a through-board connector (204) is arranged on the antenna substrate (201), so that the through-board connector (204) is simultaneously connected to the radiation unit (202) and the TR component (203) by signal, a heat conduction unit and a heating unit are arranged between the radiation unit (202) and the antenna substrate (201) and between the TR component (203) and the antenna substrate (201), and the satellite body (1) and the antenna substrate (201) are connected via a semi-rigid connection component (3).

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