A satellite platform applicable to a hug-type SAR antenna

Abstract

The present application relates to a satellite platform suitable for an embracing SAR antenna, comprising a flat board box shell and a partition located inside the board box shell; the top surface of the board box shell comprises an antenna mounting surface, and an antenna mounting boss is connected to the edge of the top surface; the bottom surface of the board box shell comprises a satellite-rocket docking surface, and a satellite-rocket adapter adapter is connected to the bottom of the side surface; the board box shell is composed of a cabin plate, and the cabin plate portion where the partition is connected and the cabin plate portion where the antenna mounting boss is connected and installed with the satellite-rocket adapter adapter are respectively provided with concentrated load-bearing embedded parts, and the concentrated load-bearing embedded parts are arranged inside the corresponding cabin plate. The satellite platform of the present invention has greater structural rigidity and lower satellite platform height, and by optimizing the position and structure of the concentrated load-bearing embedded parts, the load force of large-mass equipment can be effectively transferred to the carrier.

Description

Technical Field

[0001] This application relates to the technical field of satellite platforms, and more particularly, to a satellite platform suitable for a wrap-around SAR antenna. Background Art

[0002] Spaceborne phased array antennas, i.e., SAR antennas, are generally thin plate-shaped configurations. In order to occupy a smaller envelope space in the fairing during the launch process, the phased array antenna is usually divided into multiple identical antenna sub-arrays along the azimuth direction. During the launch process, it is in a stowed state and unfolds to form a coplanar surface after being released in orbit. Refer to the structure in Figures 1 - 2 below.

[0003] More and more phased array antennas of SAR satellites adopt a wrap-around stowage method, that is, the middle sub-array is directly fixedly connected to the earth-facing cabin plate of the satellite body. The two unfolded sub-arrays are stowed in a wrap-around manner below the middle sub-array. In the on-orbit state, the two unfolded sub-arrays are successively unfolded around both sides of the middle sub-array, and the three sub-array plate antennas form a coplanar surface. The advantage of this configuration is that the integration of the antenna and the satellite platform is relatively simple during the general assembly stage. Only the middle sub-array has a mechanical interface with the satellite platform, and the deployment mechanisms and clamping and release mechanisms of the two unfolded sub-arrays only have mechanical interfaces with the middle sub-array. Since the SAR antenna is stowed on a cabin plate of the satellite platform, the height of the satellite platform can be reduced a lot, without being affected by the antenna, which is convenient for the layout of multiple satellites and adaptation to a larger launch vehicle envelope space.

[0004] The mass of the SAR antenna accounts for about 40% of the total mass of the entire satellite. As the most important single machine on the satellite, the configuration, equipment layout, and structural design of the satellite platform structure all affect the mechanical environment at the installation interface position of the SAR antenna. From the perspective of SAR antenna design, the SAR antenna is generally heavy, not less than 100 kg, and has a complex structure. It is difficult to achieve high stiffness and structural strength by itself. Therefore, the smaller the mechanical environment received by the SAR antenna, the better, which poses higher requirements for the satellite platform structure. Summary of the Invention

[0005] The purpose of this application is to provide a satellite platform suitable for a wrap-around SAR antenna, which has a large structural stiffness and a low satellite platform height. By optimizing the position and structure of the centralized load-bearing embedded parts, the load force of large-mass equipment can be effectively transmitted to the launch vehicle.

[0006] To achieve the above object, the present invention provides a satellite platform suitable for a wrap-around SAR antenna, including a flat plate box cabin shell and a partition located inside the plate box cabin shell;

[0007] The top surface of the plate box cabin shell includes an antenna installation surface, and an antenna installation boss is connected to the edge part of the top surface;

[0008] The bottom surface of the board box cabin shell includes a star-ship docking surface, and a star-ship adapter adapter seat is connected to the bottom of the side surface;

[0009] The board box cabin shell is composed of cabin boards. Concentrated load-bearing embedded parts are respectively arranged at the parts of the cabin boards where the partition boards are connected, and at the parts of the cabin boards where the antenna mounting bosses are connected and installed with the star-ship adapter adapter seat. The concentrated load-bearing embedded parts are arranged inside the corresponding cabin boards.

[0010] In an alternative embodiment, stepped through holes and / or threaded holes are respectively arranged on the cabin boards, and the cabin boards are connected by screws passing through the stepped through holes and screwed into the threaded holes;

[0011] Light holes and / or blind holes are respectively arranged on the cabin boards, and the cabin boards are positioned and installed by positioning pins passing through the light holes and embedded in the blind holes.

[0012] In an alternative embodiment, the cabin board includes a lower cabin board, and a first concentrated load-bearing embedded part corresponding to the star-ship adapter adapter seat is arranged on the lower cabin board. The first concentrated load-bearing embedded part includes a first aluminum skin distributed up and down and first reinforcing ribs crisscrossing horizontally and vertically between the first aluminum skins. A plurality of the threaded holes are arranged on the side part of the first concentrated load-bearing embedded part.

[0013] In an alternative embodiment, the cabin board includes a front cabin board and a rear cabin board;

[0014] Second concentrated load-bearing embedded parts corresponding to the star-ship adapter adapter seat are arranged on both the front cabin board and the rear cabin board;

[0015] The second concentrated load-bearing embedded part penetrates through the entire cabin board up and down, and includes second aluminum skins distributed front and back and second reinforcing ribs arranged between the second aluminum skins. A plurality of threaded hole bosses are arranged on the second aluminum skin. The first threaded hole boss located in the upper part forms a satellite hoisting interface, and the second threaded hole boss located in the lower part forms a star-ship adapter adapter seat installation interface;

[0016] Threaded holes are arranged on the top end face of the second concentrated load-bearing embedded part, and stepped through holes are arranged in the thickness direction of the bottom.

[0017] In an alternative embodiment, third concentrated load-bearing embedded parts corresponding to the partition boards are also respectively arranged on the front cabin board and the rear cabin board;

[0018] The third concentrated load-bearing embedded part includes triangular embedded parts with their tips facing each other and arranged top and bottom, and each includes an aluminum skin and a reinforcing rib;

[0019] The tip of the third concentrated load-bearing embedded part located at the bottom faces upward, and a stepped through hole is arranged in the thickness direction;

[0020] The tip of the third centralized load-bearing embedded part located at the top faces downward, and there are threaded holes on the top end face.

[0021] In an alternative embodiment, the cabin plate includes an upper cabin plate, and a fourth centralized load-bearing embedded part corresponding to the antenna mounting boss is provided on the upper cabin plate. The fourth centralized load-bearing embedded part includes a fourth aluminum skin distributed up and down and fourth reinforcing ribs arranged between the fourth aluminum skins.

[0022] In an alternative embodiment, the antenna mounting boss includes a U-shaped boss, the U-shaped boss is connected to the fourth aluminum skin located at the top, and there are a plurality of antenna mounting threaded holes on the U-shaped boss. A stepped through hole is provided in the outer thickness direction of the fourth centralized load-bearing embedded part.

[0023] In an alternative embodiment, the satellite-rocket adapter adapter seat includes a satellite connection surface and an accessory component connection surface, and the satellite connection surface is perpendicular to the accessory component connection surface;

[0024] Multiple groups of interfaces are provided on the satellite-rocket adapter adapter seat, including a connection through hole, a first threaded hole, a second threaded hole, a third threaded hole, and a fourth threaded hole respectively;

[0025] The connection through hole is used to form a connection interface for the second threaded hole boss.

[0026] In an alternative embodiment, there are two pairs of antenna mounting bosses provided on the top of the plate box cabin shell, and there are two pairs of satellite-rocket adapter adapter seats provided on the bottom of the plate box cabin shell. The two pairs of antenna mounting bosses and the two pairs of satellite-rocket adapter adapter seats are vertically opposite in position, and the centralized load-bearing embedded parts on the front and rear sides opposite to them are continuously connected in the circumferential direction of the plate box cabin shell;

[0027] The centralized load-bearing embedded part opposite to the partition is arranged at the top corner part of the partition.

[0028] In an alternative embodiment, the antenna mounting boss and the satellite-rocket adapter adapter seat are connected to the middle of the plate box cabin shell, and the cabin plate and the partition include aluminum skin honeycomb sandwich plates.

[0029] By providing a flat plate box cabin shell, the overall height of the satellite platform can be reduced. Combined with the partition located inside the plate box cabin shell, the overall structural stiffness of the satellite platform can be improved.

[0030] The top surface of the plate box cabin shell includes an antenna mounting surface, and the bottom surface of the plate box cabin shell includes a satellite-rocket docking surface. Combined with reducing the overall height of the satellite platform, the installation distance from the satellite-rocket docking surface position to the SAR antenna can be shortened, and the magnification factor of the mechanical environment at the SAR antenna installation interface is weakened.

[0031] By connecting the antenna mounting boss at the edge part of the top surface and the satellite-rocket adapter adapter seat at the bottom part of the side surface, and respectively arranging concentrated load-bearing embedded parts at the cabin plate part where the partition boards are connected and at the cabin plate part where the antenna mounting boss and the satellite-rocket adapter adapter seat are connected and installed, it is possible to optimize the positions and structural shapes of the concentrated load-bearing embedded parts in each cabin plate of the satellite platform. By arranging the concentrated load-bearing embedded parts inside the cabin plate, the load force of large-mass equipment can be effectively transmitted to the carrier vehicle.

[0032] The setting of the antenna mounting boss and the satellite-rocket adapter adapter seat can simplify the integration of the antenna and the satellite platform. By connecting the antenna mounting boss and the satellite-rocket adapter adapter seat to the middle part of the board box cabin shell, only the middle sub-array has a mechanical interface with the satellite platform, which simplifies the subsequent general assembly and operation.

[0033] Other features and advantages of the present application will be described in detail in the subsequent specific implementation part. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of the present application, and thus should not be regarded as limiting the scope. For those of ordinary skill in the art, other relevant drawings can also be obtained based on these drawings without creative efforts.

[0035] Figure 1 It is a schematic structural diagram of the phased array antenna in the retracted state;

[0036] Figure 2 It is a schematic structural diagram of the phased array antenna in the deployed state;

[0037] Figure 3 It is a schematic overall structural diagram of the satellite platform applicable to the phased array antenna of the satellite platform;

[0038] Figure 4 It is a schematic split structural diagram of the satellite platform;

[0039] Figure 5 It is a schematic connection structural diagram between the front cabin plate and the lower cabin plate;

[0040] Figure 6 It is a schematic positioning structural diagram between the front cabin plate and the lower cabin plate;

[0041] Figure 7 It is a schematic structural diagram of the lower cabin plate;

[0042] Figure 8 It is a schematic overall structural diagram of the first concentrated load-bearing embedded part;

[0043] Figure 9 Schematic cross-sectional structure diagram of the first set of load-bearing embedded parts

[0044] Figure 10 Schematic structure diagram of the rear cabin panel

[0045] Figure 11 Schematic overall structure diagram of the second set of load-bearing embedded parts

[0046] Figure 12 Schematic overall structure diagram of the load-bearing embedded parts concentrated at the lower part of the partition board

[0047] Figure 13 Schematic overall structure diagram of the load-bearing embedded parts concentrated at the upper part of the partition board

[0048] Figure 14 Schematic structure diagram of the upper cabin panel

[0049] Figure 15 Schematic overall structure diagram of the antenna mounting boss and the fourth set of load-bearing embedded parts

[0050] Figure 16 Schematic cross-sectional structure diagram of the fourth set of load-bearing embedded parts

[0051] Figure 17 Schematic structure diagram of one perspective of the satellite-rocket adapter adapter

[0052] Figure 18 Schematic structure diagram of another perspective of the satellite-rocket adapter adapter

[0053] Figure 19 Perspective installation diagram of different sets of load-bearing embedded parts on the board box cabin shell

[0054] Icon

[0055] 01 - Step through hole; 02 - Threaded hole; 03 - Clear hole; 04 - Blind hole

[0056] 1 - Lower cabin panel; 2 - Left cabin panel; 3 - Rear cabin panel; 4 - Upper cabin panel; 5 - Right cabin panel; 6 - Front cabin panel; 7 - Partition board; 8 - Satellite-rocket adapter adapter; 9 - Antenna mounting boss

[0057] 11 - The first set of load-bearing embedded parts; 111 - The first aluminum skin; 112 - The first stiffener

[0058] 21 - The second set of load-bearing embedded parts; 211 - The second aluminum skin; 212 - The second stiffener; 213 - The first threaded hole boss; 214 - The second threaded hole boss

[0059] 31 - The third set of load-bearing embedded parts; 31a - The load-bearing embedded parts concentrated at the lower part of the partition board; 31b - The load-bearing embedded parts concentrated at the upper part of the partition board

[0060] 41-the fourth concentrated load-bearing embedded part; 411-the fourth aluminum skin; 412-the fourth reinforcing rib; 413-the antenna mounting threaded hole;

[0061] 81 - connecting through hole; 82 - first threaded hole; 83 - second threaded hole; 84 - third threaded hole; 85 - fourth threaded hole. DETAILED DESCRIPTION

[0062] In order 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 part of the embodiments of the present application, rather than all of the embodiments. The components of the embodiments of the present application described and shown in the drawings here can be arranged and designed in various different configurations.

[0063] In the description of this application, it should be noted that the terms "inside", "outside", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship in which the product of the application is usually placed when in use, which is only for the convenience of describing this application and simplifying the description, and does 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 a limitation on this application. In addition, the terms "first", "second", etc. are only used to distinguish the description, and cannot be understood as indicating or implying relative importance.

[0064] In the description of this application, it should also be noted that, unless otherwise clearly specified and limited, the terms "disposed" 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 direct connection, or an indirect connection through an intermediate medium, or it can be the internal communication of two elements. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0065] The satellite platform suitable for the surround-type SAR antenna in the present application is mainly used for the installation of the SAR antenna. By optimizing the structure of the satellite platform itself, the overall height of the satellite platform is reduced, the overall structural strength and height are improved, and the mechanical environment of the SAR antenna installation interface is improved.

[0066] See also Figure 3 , combined with Figures 4 - 6 The satellite platform suitable for the wraparound SAR antenna in the present invention has a main structure including a flat board box shell and a partition 7 located inside the board box shell.

[0067] The flat box hull structure forms a regular box-type configuration, which is mainly used to reduce the overall height of the satellite platform and further shorten the installation distance from the satellite-rocket docking position to the SAR antenna. It can effectively weaken the amplification factor of the mechanical environment at the interface from the satellite-rocket docking position to the SAR antenna installation interface.

[0068] Combined with the partition 7 located inside the box shell and the cabin panel in the form of an aluminum skin honeycomb sandwich panel included in the box shell, the overall structural strength and structural rigidity of the satellite platform can be greatly improved, providing a good installation foundation for the SAR antenna and other auxiliary components.

[0069] The top surface of the board box shell includes an antenna installation surface, and an antenna installation boss 9 is connected to the edge of the top surface to provide an installation position for the antenna.

[0070] The bottom surface of the box shell includes a satellite-rocket docking surface, and a satellite-rocket adapter seat 8 is connected to the bottom of the side surface to provide an installation position for other auxiliary components.

[0071] By setting up the satellite-rocket adapter 8 and the antenna mounting boss 9, the integration of the antenna and the satellite platform can be simplified. By installing the two in the middle of the satellite platform box shell, only the middle sub-array has a mechanical interface with the satellite platform, which simplifies subsequent assembly and operation.

[0072] The board box hull is composed of cabin panels, and the cabin panels are respectively composed of aluminum skin honeycomb sandwich panels, which can ensure the structural strength of the board box hull.

[0073] By respectively arranging concentrated load-bearing embedded parts at the cabin plate portion where the partition 7 is connected, and at the cabin plate portion where the antenna mounting boss 9 and the satellite-rocket adapter adapter 8 are connected and installed, and arranging the concentrated load-bearing embedded parts inside the corresponding cabin plates, the position and shape of the concentrated load-bearing embedded parts on the satellite platform can be optimized, thereby effectively transferring the load force of the large mass equipment to the carrier.

[0074] The satellite platform applicable to the wraparound SAR antenna in the present invention is described below based on the specific composition of the satellite platform.

[0075] First of all, we start from the basic composition of the satellite platform and the connection between the various cabin panels. Figure 3 The satellite platform configuration is a regular box-type configuration, which specifically includes a flat box cabin shell. The overall height of the satellite platform is relatively low. The lower part of the platform is the satellite-rocket docking surface, and the upper part of the platform is the SAR antenna installation surface. The distance from the satellite-rocket docking surface to the SAR antenna installation is short, which weakens the amplification factor of the mechanical environment at the interface from the satellite-rocket docking surface to the SAR antenna installation interface.

[0076] See also Figure 4, the plate box hull of the satellite platform mainly includes a lower deck 1, an upper deck 4, a left deck 2, a right deck 5, a front deck 6, a rear deck 3, a partition 7, and 4 satellite-rocket adapter adapter seats 8.

[0077] Among them, the left deck 2 and the right deck 5 have the same structural features, and the front deck 6 and the rear deck 3 have the same structural features. Based on the structure in the attached drawing, there are two pairs of antenna mounting bosses 9 and satellite-rocket adapter adapter seats 8 respectively, which are arranged on the front and rear sides of the plate box hull.

[0078] Step through holes 01 and / or threaded holes 02 are respectively provided on the decks, and the decks are connected by screws passing through the step through holes 01 and screwed into the threaded holes 02; light holes 03 and / or blind holes 04 are respectively provided on the decks, and the decks are positioned and installed by positioning pins passing through the light holes 03 and embedded in the blind holes 04.

[0079] Specifically, taking the connection between the lower deck 1 and the front deck 6 as an example, step through holes 01 and threaded holes 02 are respectively provided on the lower deck 1 and the front deck 6. The screw passes through the step through hole 01 of the front deck 6 and is screwed into the threaded hole 02 of the lower deck 1 connected thereto to realize the connection of the two decks. The connection of other decks is the same. Figure 5 and Figure 6 For the connection between the lower deck 1 and the front deck 6, step through holes 01 and threaded holes 02 are respectively provided on the lower deck 1 and the front deck 6. The screw passes through the step through hole 01 of the front deck 6 and is screwed into the threaded hole 02 of the lower deck 1 connected thereto to realize the connection of the two decks. The connection of other decks is the same.

[0080] In order to ensure the accuracy of repeated installation of the decks, positioning is achieved by pins when the decks are repeatedly disassembled. Blind holes 04 and light holes 03 are respectively provided on the lower deck 1 and the front deck 6. The positioning pin passes through the light hole 03 on the front deck 6 and is embedded in the blind hole 04 on the lower deck 1 connected thereto to ensure the positioning and installation accuracy between the decks.

[0081] Based on the satellite-rocket adapter adapter seat 8 being arranged at the side bottom of the plate box hull, taking the lower deck 1 included in the deck as an example, see Figure 7 , step through holes 01, threaded holes 02 for connecting with other decks and blind holes 04 for positioning are provided on the lower deck 1. In addition to the connection holes, four first concentrated load-bearing embedded parts 11 corresponding to the satellite-rocket adapter adapter seat 8 are also provided on the lower deck 1.

[0082] See Figure 8 for the overall structural schematic diagram of the first concentrated load-bearing embedded part 11 shown and Figure 9 for the sectional structural schematic diagram of the first concentrated load-bearing embedded part 11 shown. The first concentrated load-bearing embedded part 11 serves to transfer and disperse the connection force of the satellite-rocket adapter adapter seat 8 on the plate box hull to the lower deck 1.

[0083] In the first set of load-bearing embedded parts 11, they are machined parts, which are composed of the first aluminum skins 111 distributed vertically and the first reinforcing ribs 112 crisscrossing horizontally and vertically between the first aluminum skins 111. The first aluminum skins 111 distributed vertically can improve the local bending strength of the lower cabin plate 1, and the first reinforcing ribs 112 play the role of connecting the upper and lower first aluminum skins 111 and transmitting force. There are three threaded holes 02 provided on the side of the first set of load-bearing embedded parts 11, which can be connected to other cabin plates.

[0084] The cabin plates include the front cabin plate 6 and the rear cabin plate 3. Second set of load-bearing embedded parts 21 corresponding to the star-ship adapter adapter 8 are provided on both the front cabin plate 6 and the rear cabin plate 3. Considering the connection between the edge part of the top surface of the plate box cabin shell of the antenna mounting boss 9 and the connection at the bottom side of the star-ship adapter adapter 8 corresponding to the antenna mounting boss 9, the second set of load-bearing embedded parts 21 are required to transfer the connection forces of the two structures. Based on this, the second set of load-bearing embedded parts 21 penetrate through the entire cabin plate vertically. At the same time, based on the two pairs included in the two structures respectively, the second set of load-bearing embedded parts 21 on the front cabin plate 6 and the rear cabin plate 3 respectively include two provided on both sides, and each second set of load-bearing embedded parts 21 respectively corresponds to the installation positions of the antenna mounting boss 9 at the top and the star-ship adapter adapter 8 at the bottom.

[0085] Combined with Figure 10 , taking the rear cabin plate 3 as an example, stepped through holes 01, threaded holes 02 for connecting with other cabin plates, and optical holes 03 and blind holes 04 for positioning are provided on the rear cabin plate 3. Two second set of load-bearing embedded parts 21 that penetrate through the entire cabin plate vertically are respectively provided on both sides. At the same time, based on the setting of the partition 7, third set of load-bearing embedded parts 31 corresponding to the partition 7 are also respectively provided on the front cabin plate 6 and the rear cabin plate 3.

[0086] From the perspective of separately explaining two different sets of load-bearing embedded parts provided on the same cabin plate, combined with Figure 11 , the second set of load-bearing embedded parts 21 include second aluminum skins 211 distributed front and back and second reinforcing ribs 212 provided between the second aluminum skins. There are a plurality of threaded hole bosses 02 provided on one side of the second aluminum skin. The plurality of threaded hole bosses 02 are formed into two groups, respectively including the first threaded hole boss 213 and the second threaded hole boss 214.

[0087] The first threaded hole boss 213 located in the upper part constitutes the satellite hoisting interface, and the second threaded hole boss 214 located in the lower part constitutes the installation interface of the star-ship adapter adapter 8.

[0088] Two threaded holes 02 are provided on the top end face of the second set of load-bearing embedded parts 21 for connecting with the upper cabin plate 4, and three stepped through holes 01 are provided in the thickness direction at the bottom for connecting with the lower cabin plate 1.

[0089] Combined with Figure 12and Figure 13 In the third episode, the intermediate load-bearing embedded part 31 includes two triangular embedded parts with their tips facing each other and arranged vertically, including a lower diaphragm concentrated load-bearing embedded part 31a and an upper diaphragm concentrated load-bearing embedded part 31b respectively. Both the lower diaphragm concentrated load-bearing embedded part 31a and the upper diaphragm concentrated load-bearing embedded part 31b include an aluminum skin and reinforcing ribs.

[0090] For the purpose of distinction, the tip of the lower diaphragm concentrated load-bearing embedded part 31a faces upward, and a stepped through-hole 01 is provided in the thickness direction for connection with the diaphragm 7.

[0091] The tip of the upper diaphragm concentrated load-bearing embedded part 31b faces downward, and a threaded hole 02 is provided on the top end face for connection with the upper cabin plate 4.

[0092] See Figure 14 and in combination with Figures 15 - 16 From the perspective of the structure of the antenna mounting boss 9 and the structure of the upper cabin plate 4, the upper cabin plate 4 is provided with a stepped through-hole 01 for connection with other cabin plates. At the same time, based on the connection of the antenna mounting boss 9 on the upper cabin plate 4, four fourth concentrated load-bearing embedded parts 41 corresponding to the antenna mounting boss 9 are provided on the upper cabin plate 4. The fourth concentrated load-bearing embedded part 41 includes an upper and lower distributed fourth aluminum skin 411 and fourth reinforcing ribs 412 provided between the fourth aluminum skins 411.

[0093] The antenna mounting boss 9 includes a U-shaped boss, the U-shaped boss is connected to the fourth aluminum skin 411 at the top, and a plurality of antenna mounting threaded holes 413 are provided on the U-shaped boss. Two stepped through-holes 01 are provided in the thickness direction on the outer side of the fourth concentrated load-bearing embedded part 41 for connection with other cabin plates.

[0094] See Figures 17 - 18 In the present invention, the satellite-rocket adapter adapter 8 includes a satellite connection surface and other accessory component connection surfaces, and the satellite connection surface and the accessory component connection surface are vertically arranged, which is more suitable for the situation where the satellite is side-hung on the launch support for launch.

[0095] Multiple groups of interfaces are reserved on the satellite-rocket adapter adapter 8, including a connection through-hole 81, a first threaded hole 82, a second threaded hole 83, a third threaded hole 84, and a fourth threaded hole 85 respectively.

[0096] Among them, the connection through-hole 81 is a connection interface with the second threaded hole boss 214 on the second concentrated load-bearing embedded part 21; the first threaded hole 82 is an installation interface with the satellite-rocket separation switch; the second threaded hole 83 is an installation interface with the satellite reference prism; the third threaded hole 84 is an installation interface with the satellite-rocket adapter; the fourth threaded hole 85 is an external lifting interface for the entire satellite, so as to simplify the number of external interfaces of the satellite platform structure and simplify the subsequent general assembly and operation.

[0097] See also Figure 19 The antenna mounting bosses 9 include two pairs arranged on the top of the box shell, and the star-rocket adapter adapters 8 include two pairs arranged on the bottom of the box shell. The two pairs of antenna mounting bosses 9 are opposite to the two pairs of star-rocket adapter adapters 8 in upper and lower positions, and the concentrated load-bearing embedded parts on the front and rear sides opposite to them are continuously connected in the circumferential direction of the box shell. Furthermore, the concentrated load-bearing embedded parts opposite to the partition 7 are arranged at the top corner of the partition 7.

[0098] Specifically, through this arrangement, the satellite-rocket adapter 8, the first concentrated load-bearing embedded parts 11, the second concentrated load-bearing embedded parts 21, and the fourth concentrated load-bearing embedded parts 41 can be interconnected to form a complete force transmission path, thereby improving the connection stiffness of each cabin panel. The SAR antenna is installed on the top of the upper cabin panel 4, and the load force is transmitted to the satellite-rocket adapter 8 through the fourth concentrated load-bearing embedded parts 41. Other large-mass single machines are installed near the concentrated embedded parts of each cabin panel, so that the satellite platform as a whole has better mechanical environmental conditions.

[0099] Compared with the prior art, the satellite platform suitable for the encircling SAR antenna in the present invention has a regular plate-box configuration, a relatively low height of the satellite platform, and a relatively short distance from the satellite-rocket docking position to the SAR antenna installation, which weakens the magnification of the mechanical environment at the SAR antenna installation interface;

[0100] The integration of the antenna and the satellite platform is relatively simple. Only the middle sub-array has a mechanical interface with the satellite platform, so the subsequent assembly and operation are relatively simple.

[0101] Each cabin plate of the satellite platform is an aluminum skin honeycomb sandwich plate, with a partition 7 added in the middle, so the structural rigidity of the entire satellite platform is relatively large;

[0102] By optimizing the position and shape of concentrated load-bearing embedded parts in each cabin of the satellite platform, the load force of large-mass equipment can be effectively transferred to the carrier.

[0103] It should be noted that, in the absence of conflict, the features in the embodiments of this application may be combined with each other.

[0104] The above description is only the preferred embodiment of the present application and is not intended to limit the present application. For those skilled in the art, the present application may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A satellite platform suitable for a wraparound SAR antenna, characterized in that: It comprises a flat board box shell and a partition located inside the board box shell; The top surface of the box shell includes an antenna mounting surface, and an antenna mounting boss is connected to the edge of the top surface; The bottom surface of the box shell includes a satellite-rocket docking surface, and a satellite-rocket adapter is connected to the bottom of the side surface; The box cabin shell is composed of cabin plates, and the cabin plate portion where the partitions are connected, and the cabin plate portion where the antenna mounting boss and the satellite-rocket adapter adapter are connected and installed are respectively provided with concentrated load-bearing embedded parts, and the concentrated load-bearing embedded parts are arranged inside the corresponding cabin plates; The cabin plate includes a lower cabin plate, on which a first concentrated load-bearing embedded part corresponding to the satellite-rocket adapter adapter is arranged, and the first concentrated load-bearing embedded part includes first aluminum skins distributed up and down and first reinforcing ribs staggered horizontally and vertically between the first aluminum skins; The deck includes a front deck and a rear deck; The front deck and the rear deck are both provided with second concentrated load-bearing embedded parts corresponding to the satellite-rocket adapter adapter; The second concentrated load-bearing embedded part passes through the entire cabin plate from top to bottom, including a second aluminum skin distributed front and back and a second reinforcing rib arranged between the second aluminum skins; The front deck and the rear deck are also respectively provided with third concentrated load-bearing embedded parts corresponding to the partitions; The third concentrated load-bearing embedded parts include triangular embedded parts with their tips facing each other and arranged top and bottom, and both include aluminum skins and reinforcing ribs; The deck comprises an upper deck, on which a fourth concentrated load-bearing embedded part corresponding to the antenna mounting boss is arranged.

2. The satellite platform according to claim 1, characterized in that: The cabin plates are respectively provided with stepped through holes and / or threaded holes, and the cabin plates are connected by screws passing through the stepped through holes and screwed into the threaded holes; The cabin plates are respectively provided with light holes and / or blind holes, and the cabin plates are positioned and installed by positioning pins passing through the light holes and embedded in the blind holes.

3. The satellite platform according to claim 2, characterized in that: A plurality of threaded holes are provided on the side of the first concentrated load-bearing embedded part.

4. The satellite platform according to claim 1, characterized in that: The second aluminum skin is provided with a plurality of threaded hole bosses, the first threaded hole boss located at the upper portion constitutes a satellite hanging interface, and the second threaded hole boss located at the lower portion constitutes a satellite-rocket adapter adapter installation interface; The top end surface of the second concentrated load-bearing embedded part is provided with a threaded hole, and the bottom is provided with a stepped through hole in the thickness direction.

5. The satellite platform according to claim 4, characterized in that: The third concentrated load-bearing embedded part located at the bottom has its tip facing upward and is provided with a stepped through hole in the thickness direction; The tip of the third concentrated load-bearing embedded part located at the top faces downward, and a threaded hole is arranged on the top end surface.

6. The satellite platform according to claim 1, characterized in that: The fourth concentrated load-bearing embedded part includes fourth aluminum skins distributed up and down and fourth reinforcing ribs arranged between the fourth aluminum skins.

7. The satellite platform according to claim 6, characterized in that: The antenna mounting boss includes a U-shaped boss, which is connected to the fourth aluminum skin located at the top, and a plurality of antenna mounting threaded holes are arranged on the U-shaped boss, and a stepped through hole is arranged in the outer thickness direction of the fourth concentrated load-bearing embedded part.

8. The satellite platform according to claim 4, characterized in that: The satellite-rocket adapter adapter includes a satellite connection surface and an accessory component connection surface, and the satellite connection surface is vertically arranged with respect to the accessory component connection surface; The star-rocket adapter is provided with a plurality of interfaces, including a connecting through hole, a first threaded hole, a second threaded hole, a third threaded hole and a fourth threaded hole respectively; The connecting through hole is used to form a connecting interface of the second threaded hole boss.

9. The satellite platform according to claim 6, characterized in that: The antenna mounting bosses include two pairs arranged on the top of the box shell, and the satellite-rocket adapter adapters include two pairs arranged on the bottom of the box shell. The two pairs of antenna mounting bosses are opposite to the two pairs of satellite-rocket adapter adapters in upper and lower positions, and the concentrated load-bearing embedded parts on the front and rear sides opposite to them are continuously connected in the circumferential direction of the box shell; The concentrated load-bearing embedded parts opposite to the partition are arranged at the top corners of the partition.

10. The satellite platform according to any one of claims 1 to 9, characterized in that: The antenna mounting boss and the star-rocket adapter are connected to the middle of the box shell, and the cabin plate and the partition plate include aluminum-skinned honeycomb sandwich panels.

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