A multi-antenna sar satellite configuration and rocket

Abstract

The present application relates to a kind of multi-antenna SAR satellite configuration and rocket, and the multi-antenna SAR satellite configuration includes satellite platform, first antenna, second antenna, first solar sail and second solar sail, satellite platform is columnar structure, the circumferential surface of satellite platform includes first mounting surface, second mounting surface, third mounting surface and fourth mounting surface sequentially arranged along its own circumferential direction respectively, first antenna is assembled on first mounting surface and can be unfolded in the direction parallel to satellite platform axis, second antenna is assembled on second mounting surface and can be unfolded in the direction away from first antenna, first solar sail and second solar sail are respectively installed on the end face of satellite platform axial both ends and can embrace stack on third mounting surface, fourth mounting surface is as rocket assembly surface.The overall configuration of the satellite of the present application is compact, suitable for multiple load antennas, high integration, small envelope size, strong rocket adaptability, can be side-hung and top layout, improve the rocket volume fraction, can realize one rocket multiple satellites.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, specifically to a multi-antenna SAR satellite configuration and rocket. Background Technology

[0002] Since launch vehicle space is limited, satellite launch costs are primarily determined by volumetric density, namely the satellite's size envelope and overall satellite weight. Rockets aim to launch multiple satellites at once, rather than a single satellite. Therefore, a smaller satellite envelope size makes it easier to find a suitable rocket.

[0003] A typical SAR satellite consists of three main parts: a SAR antenna, a satellite platform, and solar panels. The SAR antenna is the satellite's main payload and its core function; other equipment on the satellite platform serves the main payload. The solar panels provide power to the entire satellite and are its primary energy source. To meet the satellite's power needs in space, typical satellite solar panels are relatively large and usually have two solar panels, each composed of multiple panels. Due to their inherent design characteristics, SAR antennas also have a relatively large size envelope and are generally composed of multiple panels, commonly three or five panels.

[0004] For SAR satellites, the overall satellite layout is often limited by the size of the SAR antenna and solar panels. Since the envelope size of both SAR antennas and solar panels is relatively large, the envelope size of common SAR satellites is also relatively large. With the development of satellite technology and the increasing demands on satellite functionality, a single SAR antenna is no longer sufficient for design requirements. Therefore, some satellites require two SAR antennas, placing higher demands on satellite configuration and layout to achieve the need for a single satellite with multiple payloads.

[0005] Common SAR satellites are mainly equipped with one SAR antenna, which uses a π-type configuration, such as... Figure 8 As shown, this type of SAR antenna configuration requires three sides of the satellite. Common satellite configurations are often hexahedral, with one side serving as the docking surface between the satellite and the rocket, and the remaining two sides as mounting surfaces for the satellite's solar panels. The overall satellite layout perfectly meets these requirements. However, if two SAR antennas are used, this configuration would not be sufficient.

[0006] Satellites exist in two states: ground-launched and in-orbit. For SAR satellites, these are completely different states. In ground-launched mode, the SAR antenna and solar panels are folded up. Once the satellite enters its orbit, the SAR antenna and solar panels are deployed, resulting in a different satellite configuration and a larger size envelope. The deployment of the SAR antenna and solar panels is accomplished through a specific mechanism, the technology of which is relatively mature.

[0007] With the development of satellite technology and the increasing demands, satellite functional indicators are becoming more and more demanding, and the ability to achieve the layout requirement of multiple payloads on a single satellite is becoming increasingly important. Summary of the Invention

[0008] In order to solve one or more technical problems existing in the prior art, the present invention provides a multi-antenna SAR satellite configuration and rocket.

[0009] The technical solution of the present invention to solve the above-mentioned technical problems is as follows: The present invention provides a multi-antenna SAR satellite configuration, including a satellite platform, a first antenna, a second antenna, a first solar panel, and a second solar panel. The satellite platform has a columnar structure. The peripheral side of the satellite platform includes a first mounting surface, a second mounting surface, a third mounting surface, and a fourth mounting surface arranged sequentially along its circumference. The first antenna is mounted on the first mounting surface and can be deployed in a direction parallel to the axis of the satellite platform. The second antenna is mounted on the second mounting surface and can be deployed in a direction away from the first antenna. The first solar panel and the second solar panel are respectively mounted on the two end faces of the satellite platform in the axial direction and can be stacked around the third mounting surface. The fourth mounting surface serves as a rocket mounting surface.

[0010] The beneficial effects of the present invention are as follows: The multi-antenna SAR satellite configuration of the present invention, by setting a first antenna, a second antenna, a first solar panel and a second solar panel, with the first antenna and the second antenna having different deployment directions, and the two solar panels being stacked in a ring around the third mounting surface, results in a compact overall satellite configuration layout, adaptability to multiple payload antennas, high integration, small envelope size, strong rocket adaptability, and the ability to be mounted on the side or top, thereby improving the rocket's volume ratio and enabling the launch of multiple satellites with a single rocket.

[0011] Based on the above technical solution, the present invention can be further improved as follows.

[0012] Furthermore, the angle between the first mounting surface and the second mounting surface is greater than 90°.

[0013] Furthermore, the peripheral side of the satellite platform also includes a fifth mounting surface, which is connected between the first mounting surface and the fourth mounting surface, and the included angle between the fifth mounting surface and the fourth mounting surface is greater than 90°.

[0014] Furthermore, the second mounting surface is arranged perpendicularly to the third mounting surface, and the third mounting surface is arranged perpendicularly to the fourth mounting surface.

[0015] Furthermore, the first solar panel and the second solar panel are respectively mounted on the two end faces of the satellite platform along the axial direction via the first mounting bracket and the second mounting bracket; when the first solar panel and the second solar panel are stacked around the third mounting surface, the first solar panel and the second solar panel are connected to the third mounting surface via the first locking and releasing mechanism, and the first mounting bracket and the second mounting bracket are respectively folded on the two end faces of the satellite platform along the axial direction; when the first solar panel and the second solar panel are in the deployed state, the first solar panel and the first mounting bracket are respectively deployed and located on the same plane at one end of the satellite platform along the axial direction, and the second solar panel and the second mounting bracket are respectively deployed and located on the same plane at the other end of the satellite platform along the axial direction.

[0016] Furthermore, the length of the first mounting bracket is greater than the length of the second mounting bracket, and the first solar panel, after being folded, wraps around the outside of the second solar panel.

[0017] The beneficial effect of adopting the above-mentioned further solution is that by setting the first mounting bracket and the second mounting bracket, it is convenient to stack the two solar panels around the side of the satellite platform.

[0018] Furthermore, the first antenna adopts a planar configuration, comprising a central antenna plate and two side antenna plates. The two side antenna plates are respectively hinged to both sides of the central antenna plate along the axial direction of the satellite platform. The two side antenna plates can be folded onto the central antenna plate and connected to the first mounting surface through a second locking and releasing mechanism. The central antenna plate is fixed on the first mounting surface.

[0019] The advantages of adopting the above-mentioned further scheme are: the first antenna adopts a planar configuration, which makes it easy to expand to both sides.

[0020] Furthermore, the second antenna adopts a stacked configuration. The second antenna includes an mounting antenna plate, a first connecting antenna plate, and a second connecting antenna plate. The first connecting antenna plate is hinged to the side of the mounting antenna plate away from the first antenna and can be stacked on the mounting antenna plate. The second connecting antenna plate is hinged to the side of the first connecting antenna plate away from the mounting antenna plate and can be stacked on the first connecting antenna plate. The second connecting antenna plate is connected to the second mounting surface through a third locking and releasing mechanism, and the mounting antenna plate is fixed on the second mounting surface.

[0021] The advantages of adopting the above-mentioned further scheme are: the second antenna adopts a stacked configuration, which facilitates sequential deployment in a direction away from the first antenna. The second antenna and the first antenna do not interfere with each other in the deployed and stacked states.

[0022] The present invention provides a rocket comprising multiple multi-antenna SAR satellite configurations as described above, and a rocket body, wherein the fourth mounting surface of the satellite platform is connected to the peripheral sidewall of the rocket body via a fourth locking and releasing mechanism.

[0023] The beneficial effects of the present invention are: the rocket of the present invention can realize multiple satellites with one rocket, can meet the requirements of multiple antenna layout within the limited envelope space of the rocket body, improve the integration and storage ratio of small satellites, and can simultaneously meet the needs of both the satellite provider and the launch vehicle provider.

[0024] Furthermore, the rocket body is provided with multiple layers of the aforementioned multi-antenna SAR satellite configuration along its own axis, each layer including multiple of the aforementioned multi-antenna SAR satellite configurations, and the axis of the satellite platform is arranged parallel to the axis of the rocket body; in two circumferentially adjacent satellite platforms, the first antenna on one satellite platform is arranged adjacent to the stacked solar panels on the other satellite platform. Attached Figure Description

[0025] Figure 1 This is an axonometric view of the multi-antenna SAR satellite configuration of the present invention;

[0026] Figure 2 This is a three-dimensional structural diagram of the multi-antenna SAR satellite configuration of the present invention;

[0027] Figure 3 This is a three-dimensional structural diagram of the first antenna of the present invention;

[0028] Figure 4 This is a three-dimensional structural diagram of the second antenna of the present invention;

[0029] Figure 5 This is a three-dimensional structural diagram of the first solar panel and the second solar panel of the present invention, which are stacked and assembled in a ring.

[0030] Figure 6 This is a three-dimensional structural diagram of the deployed state of the multi-antenna SAR satellite configuration of the present invention;

[0031] Figure 7 This is a three-dimensional structural schematic diagram of the rocket of the present invention;

[0032] Figure 8 This is a schematic diagram of an existing π-type SAR antenna structure.

[0033] The attached diagram lists the components represented by each number as follows:

[0034] 1. Satellite platform; 11. First mounting surface; 12. Second mounting surface; 13. Third mounting surface; 14. Fourth mounting surface; 15. Fifth mounting surface;

[0035] 2. First antenna; 21. Middle antenna plate; 22. Side antenna plate; 23. Second locking and releasing mechanism;

[0036] 3. Second antenna; 31. Assembled antenna plate; 32. First connecting antenna plate; 33. Second connecting antenna plate; 34. Third locking and releasing mechanism;

[0037] 4. First solar panel; 41. First mounting bracket; 42. First locking and releasing mechanism;

[0038] 5. Second solar panel; 51. Second mounting bracket;

[0039] 6. Rocket body; 61. Fourth locking and releasing mechanism. Detailed Implementation

[0040] The principles and features of the present invention are described below. The examples given are only for explaining the present invention and are not intended to limit the scope of the present invention.

[0041] Example 1

[0042] like Figures 1-6 As shown, a multi-antenna SAR satellite configuration in this embodiment includes a satellite platform 1, a first antenna 2, a second antenna 3, a first solar panel 4, and a second solar panel 5. The satellite platform 1 has a columnar structure. The peripheral surfaces of the satellite platform 1 include a first mounting surface 11, a second mounting surface 12, a third mounting surface 13, and a fourth mounting surface 14 arranged sequentially along its circumference. The first antenna 2 is mounted on the first mounting surface 11 and can be deployed in a direction parallel to the axis of the satellite platform 1. The second antenna 3 is mounted on the second mounting surface 12 and can be deployed in a direction away from the first antenna 2. The first solar panel 4 and the second solar panel 5 are respectively mounted on the two end faces of the satellite platform 1 along its axial direction and can be stacked around the third mounting surface 13. The fourth mounting surface 14 serves as a rocket mounting surface.

[0043] The multi-antenna SAR satellite configuration in this embodiment sets up a first antenna, a second antenna, a first solar panel, and a second solar panel. The first antenna and the second antenna have different deployment directions, and the two solar panels are stacked around a third mounting surface. The overall satellite configuration is compact, adaptable to multiple payload antennas, highly integrated, with a small envelope size, strong rocket adaptability, and can be mounted on the side or top, improving the rocket's volume ratio and enabling multiple satellites to be launched with a single rocket.

[0044] Example 2

[0045] Based on Example 1, this example provides an optional mating method for each mounting surface. For example... Figure 1As shown, in this embodiment, the included angle between the first mounting surface 11 and the second mounting surface 12 is greater than 90°.

[0046] More specifically, such as Figure 1 As shown, the peripheral side of the satellite platform 1 in this embodiment also includes a fifth mounting surface 15, which is connected between the first mounting surface 11 and the fourth mounting surface 14, and the included angle between the fifth mounting surface 15 and the fourth mounting surface 14 is greater than 90°.

[0047] Preferred, such as Figure 1 As shown, the second mounting surface 12 is arranged perpendicularly to the third mounting surface 13, and the third mounting surface 13 is arranged perpendicularly to the fourth mounting surface 14.

[0048] In this embodiment, the first mounting surface 11, the second mounting surface 12, the third mounting surface 13, the fourth mounting surface 14, and the fifth mounting surface 15 are all arranged parallel to the axis of the satellite platform 1.

[0049] Example 3

[0050] Based on Embodiment 1 or Embodiment 2, this embodiment provides a preferred structure for a solar panel. For example... Figure 1 , Figure 2 and 5 As shown, in this embodiment, the first solar panel 4 and the second solar panel 5 are respectively mounted on the two end faces of the satellite platform 1 along the axial direction via the first mounting bracket 41 and the second mounting bracket 51. When the first solar panel 4 and the second solar panel 5 are stacked around the third mounting surface 13, the first solar panel 4 and the second solar panel 5 are connected to the third mounting surface 13 via the first locking and releasing mechanism 42, and the first mounting bracket 41 and the second mounting bracket 51 are respectively folded on the two end faces of the satellite platform 1 along the axial direction. When the first solar panel 4 and the second solar panel 5 are in the deployed state, the first solar panel 4 and the first mounting bracket 41 are respectively deployed and located on the same plane at one end of the axial direction of the satellite platform 1, and the second solar panel 5 and the second mounting bracket 51 are respectively deployed and located on the same plane at the other end of the axial direction of the satellite platform 1.

[0051] In this embodiment, the first locking and releasing mechanism 42 can be a locking and releasing mechanism commonly used in aerospace. In the locked state, it can fold and press the solar panel against the outer surface of the satellite platform 1. In the released state, it can release the lock on the solar panel, and the solar panel will automatically unfold without being locked by the first locking and releasing mechanism 42. The unfolding and closing mechanism of the solar panel also adopts the common structure of satellite solar panels, and the mounting bracket used for the solar panel also adopts the common folding and unfolding mechanism of satellites.

[0052] like Figure 1 , Figure 2and Figure 5 As shown, specifically, the length of the first mounting bracket 41 is greater than the length of the second mounting bracket 51, and the first solar panel 4 is folded and wraps around the outside of the second solar panel 5. By setting the first and second mounting brackets, it is convenient to stack the two solar panels around the side of the satellite platform.

[0053] The solar panels in this embodiment adopt a wraparound stacked structure, which can be centrally installed on a single surface on the satellite platform. Combined with the satellite stacking configuration of the following embodiment, and through actual verification and analysis, this configuration layout ensures that there is no interference between the multiple antennas and the solar panels during deployment, and the performance indicators meet the requirements, making the solution reasonable and feasible.

[0054] Example 4

[0055] Based on any of the above embodiments, this embodiment provides a preferred structure for the first antenna 2. For example... Figure 1 , Figure 2 and Figure 3 As shown, the first antenna 2 in this embodiment adopts a planar configuration. The first antenna 2 includes a central antenna plate 21 and two side antenna plates 22. The two side antenna plates 22 are respectively hinged to both sides of the central antenna plate 21 along the axial direction of the satellite platform 1. The two side antenna plates 22 can be folded onto the central antenna plate 21 and connected to the first mounting surface 11 through a second locking and releasing mechanism 23. The central antenna plate 21 is fixed to the first mounting surface 11. The first antenna adopts a planar configuration, which facilitates expansion to both sides.

[0056] In this embodiment, the two side antenna plates 22 of the first antenna 2 are deployed to both sides of the two end faces of the satellite platform 1, which means that the deployment direction of the two side antenna plates 22 is the same as the deployment direction of the first solar panel 4 and the second solar panel 5.

[0057] In this embodiment, the second locking and releasing mechanism 23 can be a locking and releasing mechanism commonly used in aerospace. In the locked state, it can fold and press the two side antenna plates 22 of the first antenna onto the middle antenna plate 21. In the released state, it can release the lock on the two side antenna plates 22. The two side antenna plates 22 are not locked by the second locking and releasing mechanism 23 and automatically unfold. The unfolding and closing mechanism between the side antenna plates 22 and the middle antenna plate also adopts the commonly used folding and unfolding structure of antenna plates.

[0058] Example 5

[0059] Based on any of the above embodiments, this embodiment provides a preferred structure for the second antenna 3. For example... Figure 1 , Figure 2 and Figure 4As shown, the second antenna 3 in this embodiment adopts a stacked configuration. The second antenna 3 includes an mounting antenna plate 31, a first connecting antenna plate 32, and a second connecting antenna plate 33. The first connecting antenna plate 32 is hinged to the side of the mounting antenna plate 31 away from the first antenna 2 and can be stacked on the mounting antenna plate 31. The second connecting antenna plate 33 is hinged to the side of the first connecting antenna plate 32 away from the mounting antenna plate 31 and can be stacked on the first connecting antenna plate 32. The second connecting antenna plate 33 is connected to the second mounting surface 12 through a third locking and releasing mechanism 34. The mounting antenna plate 31 is fixed on the second mounting surface 12. The stacked configuration of the second antenna facilitates sequential unfolding away from the first antenna. The second antenna and the first antenna do not interfere with each other in the unfolded and stacked states.

[0060] In this embodiment, the third locking and releasing mechanism 34 can be a locking and releasing mechanism commonly used in aerospace. In the locked state, it can fold and press the first connecting antenna plate 32 and the second connecting antenna plate 33 of the second antenna onto the mounting antenna plate 31. In the released state, it can release the lock on the first connecting antenna plate 32 and the second connecting antenna plate 33. The first connecting antenna plate 32 and the second connecting antenna plate 33 are not locked by the third locking and releasing mechanism 34 and automatically unfold. The unfolding and closing mechanism between the mounting antenna plate 31, the first connecting antenna plate 32 and the second connecting antenna plate 33 also adopts the commonly used folding and unfolding structure of antenna plates.

[0061] In this embodiment, the deployment direction of the first connecting antenna plate 32 and the second connecting antenna plate 33 of the second antenna 3 is perpendicular to the deployment direction of the first antenna 2.

[0062] The satellite platform in this embodiment still adopts a cubic form. By changing the collapsible state of the first and second antennas, the size envelope of the SAR antenna in the collapsible state is reduced.

[0063] The multi-antenna SAR satellite configuration in this embodiment, combining the antennas and solar panels of the above embodiments, features a compact overall satellite layout, adaptable to multi-antenna layout requirements, high integration, and high packing ratio, which helps improve satellite performance. Simultaneously, the launch vehicle is highly adaptable, the satellite volume envelope is small, enabling multiple satellite launches with a single rocket, reducing satellite launch costs.

[0064] Example 6

[0065] This embodiment provides a rocket, such as Figure 7 As shown, the rocket in this embodiment includes multiple multi-antenna SAR satellite configurations as described above, and also includes a rocket body 6. The fourth mounting surface 14 of the satellite platform 1 is connected to the peripheral sidewall of the rocket body 6 through a fourth locking and releasing mechanism 61.

[0066] Specifically, such as Figure 7 As shown, the rocket body 6 of this embodiment is provided with multiple layers of the multi-antenna SAR satellite configuration along its own axis. Each layer includes multiple multi-antenna SAR satellite configurations. The axis of the satellite platform 1 is arranged parallel to the axis of the rocket body 6. In two circumferentially adjacent satellite platforms 1, the first antenna 2 on one satellite platform 1 is arranged adjacent to the stacked solar panels on the other satellite platform 1.

[0067] The fourth locking and releasing mechanism 61 in this embodiment can be a locking and releasing mechanism commonly used in aerospace. In the locked state, it can lock the satellite platform to the peripheral wall of the rocket body 6, and release the satellite platform by unlocking.

[0068] like Figure 7 As shown, this embodiment can set two layers of multi-antenna SAR satellite configurations on the rocket body 6, with each layer containing four multi-antenna SAR satellite configurations.

[0069] The rocket in this embodiment can launch multiple satellites in one launch, meet the requirements of multi-antenna layout within the limited envelope space of the rocket body, improve the integration and storage ratio of small satellites, and simultaneously meet the needs of both the satellite provider and the launch vehicle provider.

[0070] In the description of this invention, it should be understood that the terms "top", "bottom", "inner", "outer", "axial", "circumferential", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing this invention and 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, and therefore should not be construed as a limitation of this invention.

[0071] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0072] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0073] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "over," and "on top" of the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0074] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0075] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

Claims

1. A multi-antenna SAR satellite configuration, characterized in that, The system includes a satellite platform, a first antenna, a second antenna, a first solar panel, and a second solar panel. The satellite platform has a columnar structure. The peripheral surfaces of the satellite platform include a first mounting surface, a second mounting surface, a third mounting surface, and a fourth mounting surface arranged sequentially along its circumference. The first antenna is mounted on the first mounting surface and can be deployed in a direction parallel to the axis of the satellite platform. The second antenna is mounted on the second mounting surface and can be deployed in a direction away from the first antenna. The first solar panel and the second solar panel are respectively mounted on the two end faces of the satellite platform along its axial direction and can be stacked around the third mounting surface. The fourth mounting surface serves as a rocket mounting surface. The included angle between the first mounting surface and the second mounting surface is greater than 90°; The satellite platform also includes a fifth mounting surface, which is connected between the first mounting surface and the fourth mounting surface, and the angle between the fifth mounting surface and the fourth mounting surface is greater than 90°. The second mounting surface is arranged perpendicularly to the third mounting surface, and the third mounting surface is arranged perpendicularly to the fourth mounting surface; The first solar panel and the second solar panel are respectively mounted on the two end faces of the satellite platform along the axial direction via a first mounting bracket and a second mounting bracket. When the first solar panel and the second solar panel are stacked around the third mounting surface, the first solar panel and the second solar panel are connected to the third mounting surface via a first locking and releasing mechanism. The first mounting bracket and the second mounting bracket are respectively folded on the two end faces of the satellite platform along the axial direction. When the first solar panel and the second solar panel are in the deployed state, the first solar panel and the first mounting bracket are respectively deployed and located on the same plane at one end of the satellite platform along the axial direction, and the second solar panel and the second mounting bracket are respectively deployed and located on the same plane at the other end of the satellite platform along the axial direction. The length of the first mounting bracket is greater than the length of the second mounting bracket, and the first solar panel, after being folded, wraps around the outside of the second solar panel; The first antenna adopts a planar configuration and includes a central antenna plate and two side antenna plates. The two side antenna plates are respectively hinged to both sides of the central antenna plate along the axial direction of the satellite platform. The two side antenna plates can be folded onto the central antenna plate and connected to the first mounting surface through a second locking and releasing mechanism. The central antenna plate is fixed on the first mounting surface. The second antenna adopts a stacked configuration. The second antenna includes an mounting antenna plate, a first connecting antenna plate, and a second connecting antenna plate. The first connecting antenna plate is hinged to the side of the mounting antenna plate away from the first antenna and can be stacked on the mounting antenna plate. The second connecting antenna plate is hinged to the side of the first connecting antenna plate away from the mounting antenna plate and can be stacked on the first connecting antenna plate. The second connecting antenna plate is connected to the second mounting surface through a third locking and releasing mechanism. The mounting antenna plate is fixed on the second mounting surface.

2. A rocket, characterized in that, The system includes multiple multi-antenna SAR satellite configurations as described in claim 1, and also includes a rocket body. The fourth mounting surface of the satellite platform is connected to the peripheral sidewall of the rocket body via a fourth locking and releasing mechanism.

3. The rocket according to claim 2, characterized in that, The rocket body is provided with multiple layers of the aforementioned multi-antenna SAR satellite configuration along its own axis, each layer including multiple of the aforementioned multi-antenna SAR satellite configurations, and the axis of the satellite platform is arranged parallel to the axis of the rocket body; In two circumferentially adjacent satellite platforms, the first antenna on one satellite platform is arranged adjacent to the circumferentially stacked solar panels on the other satellite platform.

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