SAR satellite and launch vehicle

Abstract

The present invention provides a SAR satellite and a carrier rocket, which relate to the field of satellite technology, to optimize the SAR satellite structure to a certain extent, reduce the overall size of the SAR satellite, and ensure the overall satellite structural strength. The SAR satellite provided by the present invention includes a SAR antenna and a bearing bracket; the bearing bracket includes a bracket body, a first extended support plate and a second extended support plate, the first extended support plate and the second extended support plate are respectively located at both ends of the bracket body, and the first extended support plate, the bracket body and the second extended support plate jointly form a bearing platform; the SAR antenna includes a folding section and a body-mounted section, the folding section is rotatably connected to the body-mounted section, and can be flipped relative to the body-mounted section, and the size of the bearing platform is not less than the size of the body-mounted section.

Description

Technical Field

[0001] The present invention relates to the field of satellite technology, and in particular to a SAR satellite and a carrier rocket. Background Art

[0002] With the development of technology, the demand for reducing the cost of satellite launches is getting higher and higher. Therefore, the one-launch-multiple-satellite technology has emerged, which is to launch multiple satellites by one carrier rocket, thereby greatly reducing the launch cost.

[0003] The constellation deployment of SAR satellites will become a future development trend. At present, the launch of multiple satellites with one rocket is mainly achieved by flattening the satellites. However, since the length and width of the SAR satellite antenna are relatively large after unfolding, the current flattened satellite configuration cannot be used in SAR satellites, making it difficult to achieve the launch of multiple satellites with one rocket.

[0004] Therefore, there is an urgent need to provide a SAR satellite and a carrier rocket to solve the problems existing in the prior art to a certain extent. Summary of the invention

[0005] The object of the present invention is to provide a SAR satellite and a carrier rocket, so as to optimize the structure of the SAR satellite to a certain extent, reduce the overall size of the SAR satellite, and ensure the overall satellite structural strength.

[0006] A SAR satellite provided by the present invention comprises a SAR antenna and a bearing bracket; the bearing bracket comprises a bracket body, a first extended support plate and a second extended support plate, the first extended support plate and the second extended support plate are respectively located at two ends of the bracket body, and the first extended support plate, the bracket body and the second extended support plate jointly form a bearing platform; the SAR antenna comprises a folding section and a body-mounted section, the folding section is rotatably connected to the body-mounted section and can be flipped relative to the body-mounted section, and the size of the bearing platform is not less than the size of the body-mounted section.

[0007] The SAR satellite provided by the present invention further includes a satellite body, the bracket body is formed with a receiving space, and the satellite body is arranged in the receiving space.

[0008] Specifically, the bracket body includes a first supporting frame and a second supporting frame, and the first supporting frame and the second supporting frame are relatively arranged to form the accommodating space; the first supporting frame and the second supporting frame are both C-shaped structures, and the first supporting frame and the second supporting frame both include a first supporting section and a second supporting section, the first supporting section of the first supporting frame is connected to the first extended support plate and are located in the same horizontal plane, the first supporting section of the second supporting frame is connected to the second extended support plate and are located in the same horizontal plane, and the first extended support plate, the second extended support plate, the first supporting section of the first supporting frame and the first supporting section of the second supporting frame are all located in the same horizontal plane; the second supporting section of the first supporting frame and the second supporting section of the second supporting frame are respectively located at both ends of the satellite body and are used to support the satellite body.

[0009] Furthermore, a connecting beam is provided between the first supporting section of the first supporting frame and the first supporting section of the second supporting frame.

[0010] Specifically, the first supporting section and the second supporting section are both provided with supporting feet, and the axes of the supporting feet are perpendicular to the first supporting section and the second supporting section.

[0011] Specifically, the SAR satellite provided by the present invention also includes a first solar wing and a second solar wing, and the supporting bracket also includes a first supporting plate and a second supporting plate, the first supporting plate and the second supporting plate are respectively arranged on both sides of the bracket body, the first solar wing is connected to the first supporting plate, and the second solar wing is connected to the second supporting plate.

[0012] Furthermore, the first supporting plate and the second supporting plate are located in the same horizontal plane, and an accommodation distance is formed between the first supporting plate, the second supporting plate and the second supporting section, and the thickness of the first solar wing after folding and the thickness of the second solar wing after folding are not greater than the accommodation distance.

[0013] Furthermore, the first solar wing and the second solar wing each include a fitting section and at least one folding section, the folding section is rotatably connected to the fitting section, the fitting section of the first solar wing is fitted with the first supporting plate, and the fitting section of the second solar wing is fitted with the second supporting plate.

[0014] Furthermore, a plurality of support beams are provided between the first bearing plate and the first extended support plate, and between the second bearing plate and the second extended support plate, and the plurality of support beams constitute a plurality of triangular support structures.

[0015] Compared with the prior art, the SAR satellite provided by the present invention has the following advantages:

[0016] The SAR satellite provided by the present invention comprises a SAR antenna and a bearing bracket; the bearing bracket comprises a bracket body, a first extended support plate and a second extended support plate, the first extended support plate and the second extended support plate are respectively located at two ends of the bracket body, and the first extended support plate, the bracket body and the second extended support plate jointly form a bearing platform; the SAR antenna comprises a folding section and a body-mounted section, the folding section is rotatably connected to the body-mounted section and can be flipped relative to the body-mounted section, and the size of the bearing platform is not less than the size of the body-mounted section.

[0017] From this analysis, it can be seen that the SAR antenna can be carried by the carrying bracket, but since the length and width of the SAR antenna in the folded stage are relatively large, the present application arranges the first extended support plate and the second extended support plate on both sides of the bracket body respectively, and the size of the carrying platform formed by the first extended support plate, the bracket body and the second extended support plate is not less than the size of the SAR antenna body segment, so that the body segment of the SAR antenna can be adequately supported, and the thickness of the SAR antenna in the folded state can be compressed to a large extent, thereby realizing the flattening setting of the overall SAR satellite, and ultimately achieving the goal of launching multiple satellites with one rocket.

[0018] In addition, the present invention also provides a launch vehicle, including a carrying platform and a plurality of the above-mentioned SAR satellites; the plurality of the SAR satellites are arranged around the carrying platform or stacked on the carrying platform.

[0019] Since the SAR satellite provided in the present application can reduce the overall space size to a great extent, it can be combined with the overall carrier rocket in a manner of surrounding the carrier platform or stacking on the carrier platform, realizing multiple satellites in one rocket, thereby reducing the cost of a single launch to a certain extent. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] 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.

[0021] Figure 1 A schematic diagram of the structure of a SAR satellite first-person perspective provided by an embodiment of the present invention;

[0022] Figure 2 A schematic diagram of the structure of a SAR satellite second viewing angle provided by an embodiment of the present invention;

[0023] Figure 3 A schematic diagram of a first layout of multiple SAR satellites in a carrier rocket provided by an embodiment of the present invention;

[0024] Figure 4 A schematic diagram of a second layout of multiple SAR satellites in a carrier rocket provided in an embodiment of the present invention.

[0025] In the figure: 1-SAR satellite; 101-bracket body; 1011-accommodating space; 1012-first bearing frame; 1013-second bearing frame; 1014-first supporting section; 1015-second supporting section; 1016-supporting foot; 102-first extended support plate; 103-second extended support plate; 104-SAR antenna; 1041-body-mounted section; 1042-folding section; 105-first solar wing; 1051-fitting section; 1052-folding section; 106-second solar wing; 107-first bearing plate; 108-second bearing plate; 109-accommodating spacing; 110-support beam; 111-satellite body; 2-carrying platform. DETAILED DESCRIPTION

[0026] To make the purpose, technical scheme and advantages of the embodiments of the present application clearer, the technical scheme in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all of the embodiments. The components of the embodiments of the present application generally described and shown in the drawings here can be arranged and designed in various different configurations. Therefore, the following detailed description of the embodiments of the present application provided in the drawings is not intended to limit the scope of the application claimed for protection, but merely represents the selected embodiments of the present application. Based on the embodiments of the present application, all other embodiments obtained by those skilled in the art without making creative work belong to the scope of protection of the present application.

[0027] In the description of the embodiments of the present application, it should be noted that the terms "upper", "lower", "left", "right", "vertical", "horizontal", "inside", "outside", etc. indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, or are the positions or positional relationships in which the invented product is usually placed when in use. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply 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", "third", etc. are only used to distinguish the description, and cannot be understood as indicating or implying relative importance.

[0028] In addition, the terms "horizontal", "vertical" and the like do not mean that the components are required to be absolutely horizontal or suspended, but can be slightly tilted. For example, "horizontal" only means that its direction is more horizontal than "vertical", and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0029] In the description of the embodiments of the present application, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "setting", "installation", "connection", and "connection" 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 connection of two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0030] As used herein, the term "and / or" includes any one of the associated listed items and any combination of any two or more items.

[0031] For ease of description, spatial relative terms such as "above", "upper", "below", and "lower" may be used herein to describe the relationship of one element to another element as shown in the drawings. Such spatial relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the drawings.

[0032] The terms used herein are only used to describe various examples and are not used to limit the present disclosure. Unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. The terms "include", "comprise" and "have" list the stated features, quantities, operations, components, elements and / or their combinations that exist, but do not exclude the existence or addition of one or more other features, quantities, operations, components, elements and / or their combinations.

[0033] Variations in the shapes shown in the drawings may occur due to manufacturing techniques and / or tolerances. Therefore, the examples described herein are not limited to the specific shapes shown in the drawings but include variations in shapes that occur during manufacturing.

[0034] The features of the examples described herein may be combined in various ways that will be apparent after understanding the disclosure of the present application. In addition, although the examples described herein have various configurations, other configurations are possible as will be apparent after understanding the disclosure of the present application. In addition, the technical solutions between the various embodiments may be combined with each other, but must be based on the ability of ordinary technicians in the field to implement. When the combination of technical solutions is mutually contradictory or cannot be implemented, it should be considered that the combination of such technical solutions does not exist and is not within the scope of protection required by the present application.

[0035] like Figure 1 Combination Figure 2As shown, the present invention provides a SAR satellite 1, including a SAR antenna 104 and a bearing bracket; the bearing bracket includes a bracket body 101, a first extended support plate 102 and a second extended support plate 103, the first extended support plate 102 and the second extended support plate 103 are respectively located at two ends of the bracket body 101, and the first extended support plate 102, the bracket body 101 and the second extended support plate 103 jointly form a bearing platform; the SAR antenna 104 includes a folding section 1042 and a body-mounted section 1041, the folding section 1042 is rotatably connected to the body-mounted section 1041, and can be flipped relative to the body-mounted section 1041, and the size of the bearing platform is not less than the size of the body-mounted section 1041.

[0036] Compared with the prior art, the SAR satellite 1 provided by the present invention has the following advantages:

[0037] The SAR satellite 1 provided by the present invention can carry a SAR antenna 104 through a carrying bracket. However, since the length and width of the SAR antenna 104 in the folded stage are relatively large, the present application arranges a first extended support plate 102 and a second extended support plate 103 on both sides of the bracket body 101, and the size of the carrying platform jointly formed by the first extended support plate 102, the bracket body 101 and the second extended support plate 103 is not less than the size of the body-mounted section 1041 of the SAR antenna 104, so that the body-mounted section 1041 of the SAR antenna 104 can be sufficiently supported, so that the thickness of the SAR antenna 104 in the folded state can be compressed to a large extent, thereby realizing the flattening setting of the overall SAR satellite 1, and finally achieving the purpose of launching multiple satellites with one rocket.

[0038] It is understandable that in the present application, the body section 1041 can be a whole antenna board or a plurality of spliced ​​pieces, and the folding section 1042 can be made of Figure 1 Combination Figure 2 The two-segment folded form shown in the figure includes two folding segments 1042 arranged opposite to each other. When the antenna needs to be unfolded, the two folding segments 1042 rotate relative to the body-mounted segment 1041 at the same time, thereby realizing the unfolding of the antenna.

[0039] It should be noted that in some cases, the SAR antenna 104 may also be in the form of a one-stage folding, that is, the size of the folding section 1042 is the same as the size of the body-mounted section 1041, one end of the folding section 1042 is rotatably connected to the body-mounted section 1041, and folds to one side when folding. Regardless of whether it is a one-stage folding or a multi-stage folding, it is only necessary to ensure that the size of the bearing platform composed of the first extended support plate 102, the bracket body 101 and the second extended support plate 103 provided in this application is not less than the size of the body-mounted section 1041.

[0040] Preferably, in order to ensure the strength of the overall structure, the first extended support plate 102 and the second extended support plate 103 are integrally formed with the bracket body 101 in the present application, thereby being able to ensure stable support for the SAR antenna 104 to a certain extent.

[0041] It is understandable that if Figure 1 Combination Figure 2 As shown, the SAR satellite 1 provided by the present invention further includes a satellite body 111 , the bracket body 101 is formed with a receiving space 1011 , and the satellite body 111 is arranged in the receiving space 1011 .

[0042] The accommodation space 1011 formed by the bracket body 101 can stably carry and protect the satellite body 111 , and can combine the satellite body 111 with the SAR antenna 104 .

[0043] Preferably, if Figure 1 Combination Figure 2 As shown, the bracket body 101 in the present application includes a first supporting frame 1012 and a second supporting frame 1013, and the first supporting frame 1012 and the second supporting frame 1013 are arranged opposite to each other to form a receiving space 1011; the first supporting frame 1012 and the second supporting frame 1013 are both C-shaped structures, and the first supporting frame 1012 and the second supporting frame 1013 both include a first supporting section 1014 and a second supporting section 1015, and the first supporting section 1014 of the first supporting frame 1012 is connected to the first extended support plate 102 and is located at the same level The first supporting section 1014 of the second supporting frame 1013 is connected to the second extended support plate 103 and are located in the same horizontal plane, and the first extended support plate 102, the second extended support plate 103, the first supporting section 1014 of the first supporting frame 1012 and the first supporting section 1014 of the second supporting frame 1013 are all located in the same horizontal plane; the second supporting section 1015 of the first supporting frame 1012 and the second supporting section 1015 of the second supporting frame 1013 are respectively located at both ends of the satellite body 111 and are used to support the satellite body 111.

[0044] The first extended support plate 102, the second extended support plate 103, the first supporting section 1014 of the first bearing frame 1012 and the first supporting section 1014 of the second bearing frame 1013 are all located in the same horizontal plane, which can make the body section 1041 of the SAR antenna 104 fit more stably with the formed bearing platform, thereby achieving stable bearing of the SAR antenna 104. In order to ensure the connection strength between the first bearing frame 1012 and the second bearing frame 1013, and to ensure the flatness of the formed bearing platform, the present application sets a connecting beam between the first supporting section 1014 of the first bearing frame 1012 and the first supporting section 1014 of the second bearing frame 1013, so that the first bearing frame 1012 and the second bearing frame 1013 can form a whole, so as to achieve stable bearing of the SAR antenna 104 and to ensure the overall strength of the bracket body 101 to a certain extent.

[0045] It can be understood that in the present application, the first supporting frame 1012, the second supporting frame 1013 and the connecting beam therebetween can be arranged by welding or integrally forming. By adopting this structure, it is possible to reduce the overall weight of the bracket body 101 while ensuring the structural strength and load-bearing capacity, thereby reducing the weight of the entire SAR satellite 1 and reducing the overall load on the carrier rocket.

[0046] It is necessary to add that, if Figure 2 As shown, since the first supporting section 1014 in the present application needs to carry the SAR antenna 104, the size of the first supporting section 1014 in the present application is larger than the size of the second supporting section 1015, thereby being able to further reduce the weight of the overall bracket body 101 and reduce the load on the launch vehicle.

[0047] It is necessary to further explain that the width of the first carrier frame 1012 and the second carrier frame 1013 in the present application is slightly larger than the width of the satellite body. On the one hand, the satellite body can be fully protected after the satellite body is installed into the accommodation space 1011. On the other hand, when the SAR satellite 1 needs to be stacked in the launch vehicle, it is necessary to connect the support legs 1016 to the bracket body 101. Figure 1 Combination Figure 2 As shown, in the present application, both the first supporting segment 1014 and the second supporting segment 1015 are provided with supporting feet 1016 , and the axes of the supporting feet 1016 are perpendicular to the first supporting segment 1014 and the second supporting segment 1015 .

[0048] By providing the support legs 1016 on the first supporting section 1014 and the second supporting section 1015, on the one hand, the overall SAR satellite 1 can be stably placed; on the other hand, Figure 4As shown, when the SAR satellites 1 are stacked on the carrier platform 2 of the launch vehicle, the legs 1016 can also play a connecting role, that is, the legs 1016 are connected to each other to achieve a stable connection between the stacked SAR satellites 1.

[0049] It can be understood that in order to ensure the stable placement of the SAR satellite 1 and facilitate the smooth docking of adjacent SAR satellites 1 when stacking is required, the diameter of the support leg 1016 connected to the second supporting segment 1015 in the present application is larger than the diameter of the support leg 1016 connected to the first supporting segment 1014, and the end of the support leg 1016 connected to the second supporting segment 1015 is formed with a socket into which the support leg 1016 provided on the first supporting segment 1014 can be inserted, so that when the SAR satellite 1 is placed alone, the support leg 1016 on the second supporting segment 1015 can provide stable support, and when stacking and docking is required, by inserting the support leg 1016 on the first supporting segment 1014 into the corresponding socket, stable stacking of two adjacent SAR satellites 1 can be achieved.

[0050] It is understandable that if Figure 1 Combination Figure 2 As shown, the SAR satellite 1 provided by the present invention also includes a first solar wing 105 and a second solar wing 106, and the supporting bracket also includes a first supporting plate 107 and a second supporting plate 108, the first supporting plate 107 and the second supporting plate 108 are respectively arranged on both sides of the bracket body 101, the first solar wing 105 is connected to the first supporting plate 107, and the second solar wing 106 is connected to the second supporting plate 108.

[0051] The first solar wing 105 and the second solar wing 106 mentioned in the present application are solar panels. The first supporting plate 107 and the second supporting plate 108 arranged on both sides of the bracket body 101 can realize the combination of the first solar wing 105, the second solar wing 106, the SAR antenna 104 and the satellite body, thereby forming an integrated SAR satellite 1.

[0052] Preferably, in the present application, the first supporting plate 107 and the second supporting plate 108 are located on the same horizontal plane, and are parallel to the plane of the supporting platform formed by the first extended support plate 102, the second extended support plate 103 and the bracket body 101, so that the first solar wing 105 and the second solar wing 106 can be parallel to the SAR antenna 104 after unfolding.

[0053] More preferably, if Figure 1 Combination Figure 2As shown, in the present application, the first supporting plate 107 and the second supporting plate 108 are located in the same horizontal plane, and an accommodation spacing 109 is formed between the first supporting plate 107 and the second supporting plate 108 and the second supporting section 1015, and the thickness of the first solar wing 105 after folding and the thickness of the second solar wing 106 after folding are not greater than the accommodation spacing 109.

[0054] In the present application, the first solar wing 105 and the second solar wing 106 both adopt a three-section two-folding structure, that is, the first solar wing 105 and the second solar wing 106 in the present application both include a fitting section 1051 and two folding sections 1052, one end of one folding section 1052 is rotatably connected to one end of the fitting section 1051, and the other end is rotatably connected to one end of the other folding section 1052, thereby forming the above-mentioned three-section two-folding structure.

[0055] Taking this solar wing structure as an example, in order to ensure that the space occupied by the entire SAR satellite 1 is more regular, the present application makes the thickness of the first solar wing 105 after folding not greater than the accommodation spacing 109 formed between the first supporting plate 107 and the second supporting section 1015 corresponding to the first supporting frame 1012, and the thickness of the second solar wing 106 after folding not greater than the accommodation spacing 109 formed between the second supporting section 1015 corresponding to the second supporting plate 108 and the second supporting frame 1013. This allows the space occupied by the entire SAR satellite 1 to be closer to a hexahedron, thereby making the overall structure more regular, facilitating planning and layout, and achieving the purpose of carrying more SAR satellites 1 in a limited carrying space.

[0056] Preferably, if Figure 1 Combination Figure 2 As shown, in the present application, a plurality of support beams 110 are provided between the first bearing plate 107 and the first extended support plate 102 and between the second bearing plate 108 and the second extended support plate 103 , and the plurality of support beams 110 form a plurality of triangular support structures.

[0057] It can be understood that the multiple support beams 110 in the present application may include support beams 110 extending in the vertical direction and support beams 110 arranged at an angle, so that multiple stable triangular support structures can be formed by the multiple support beams 110, thereby ensuring the structural strength and load-bearing capacity of the overall supporting bracket.

[0058] In addition, if Figure 3 Combination Figure 4 As shown, the present invention further provides a launch vehicle, comprising a carrying platform 2 and a plurality of the above-mentioned SAR satellites 1 ; the plurality of SAR satellites 1 are arranged around the carrying platform 2 or stacked on the carrying platform 2 .

[0059] Since the SAR satellite 1 provided in the present application can reduce the overall space size to a large extent, it can be combined with the overall carrier rocket in a manner of surrounding the carrier platform 2 or stacked on the carrier platform 2, achieving multiple satellites in one launch, thereby reducing the cost of a single launch to a certain extent.

[0060] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A SAR satellite, characterized in that: Including SAR antenna and carrying bracket; The load-bearing bracket includes a bracket body, a first extended support plate and a second extended support plate, wherein the first extended support plate and the second extended support plate are respectively located at two ends of the bracket body, and the first extended support plate, the bracket body and the second extended support plate together form a load-bearing platform; The SAR antenna comprises a folding section and a body-mounted section, the folding section is rotatably connected to the body-mounted section and can be flipped relative to the body-mounted section, and the size of the bearing platform is not less than the size of the body-mounted section; It also includes a satellite body, the bracket body is formed with a receiving space, and the satellite body is arranged in the receiving space; The bracket body includes a first carrying frame and a second carrying frame, and the first carrying frame and the second carrying frame are arranged opposite to each other to form the accommodating space; The first bearing frame and the second bearing frame are both C-shaped structures, and the first bearing frame and the second bearing frame both include a first supporting section and a second supporting section, the first supporting section of the first bearing frame is connected to the first extended support plate and are located in the same horizontal plane, the first supporting section of the second bearing frame is connected to the second extended support plate and are located in the same horizontal plane, and the first extended support plate, the second extended support plate, the first supporting section of the first bearing frame, and the first supporting section of the second bearing frame are all located in the same horizontal plane; The second supporting section of the first supporting frame and the second supporting section of the second supporting frame are respectively located at two ends of the satellite body and are used to support the satellite body.

2. The SAR satellite according to claim 1, characterized in that: A connecting beam is provided between the first supporting section of the first carrying frame and the first supporting section of the second carrying frame.

3. The SAR satellite according to claim 1, characterized in that: The first supporting section and the second supporting section are both provided with supporting feet, and the axes of the supporting feet are perpendicular to the first supporting section and the second supporting section.

4. The SAR satellite according to claim 1, characterized in that: It also includes a first solar wing and a second solar wing, and the supporting bracket also includes a first supporting plate and a second supporting plate, the first supporting plate and the second supporting plate are respectively arranged on both sides of the bracket body, the first solar wing is connected to the first supporting plate, and the second solar wing is connected to the second supporting plate.

5. The SAR satellite according to claim 4, characterized in that: The first supporting plate and the second supporting plate are located in the same horizontal plane, and an accommodation distance is formed between the first supporting plate, the second supporting plate and the second supporting section, and the thickness of the first solar wing after folding and the thickness of the second solar wing after folding are not greater than the accommodation distance.

6. The SAR satellite according to claim 4, characterized in that: The first solar wing and the second solar wing each include a fitting section and at least one folding section, the folding section is rotatably connected to the fitting section, the fitting section of the first solar wing is fitted with the first supporting plate, and the fitting section of the second solar wing is fitted with the second supporting plate.

7. The SAR satellite according to claim 4, characterized in that: A plurality of support beams are provided between the first bearing plate and the first extended support plate, and between the second bearing plate and the second extended support plate, and the plurality of support beams constitute a plurality of triangular support structures.

8. A launch vehicle, characterized in that: A carrier platform and a plurality of SAR satellites as described in any one of claims 1 to 7; The plurality of SAR satellites are arranged around the carrying platform or stacked on the carrying platform.

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