Satellite platform suitable for encircling type SAR (Synthetic Aperture Radar) antenna

Abstract

The invention relates to a satellite platform suitable for a surrounding type SAR antenna. The satellite platform comprises a flat plate box cabin shell and a partition plate located in the plate box cabin shell. The top surface of the plate box cabin shell comprises an antenna mounting surface, and the edge part of the top surface is connected with an antenna mounting boss; the bottom surface of the plate box cabin shell comprises a satellite-rocket butt joint surface, and the bottom of the side surface is connected with a satellite-rocket adapter adapter; the plate box cabin shell is composed of cabin plates, concentrated force bearing embedded parts are arranged on the cabin plate portion where the partition plate is connected and the cabin plate portion where the antenna installation boss and the satellite rocket adapter adapter are connected and installed respectively, and the concentrated force bearing embedded parts are arranged in the corresponding cabin plates. The satellite platform has large structural rigidity and low satellite platform height, and the loading force of large-mass equipment can be effectively transmitted to a carrier by optimizing the position and the structure of the concentrated bearing embedded part.

Description

Technical Field

[0001] The present application relates to the technical field of satellite platforms, and in particular to a satellite platform suitable for an encircling SAR antenna. Background Art

[0002] The satellite-borne phased array antenna, i.e., the SAR antenna, is generally a thin plate-shaped configuration. In order to occupy a smaller envelope space of the fairing during launch, 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 folded state, and after being released in orbit, it unfolds to form a coplanar shape. See Figure 1-Figure 2 The structure in .

[0003] More and more SAR satellites' phased array antennas are folded in an embracing manner, that is, the middle sub-array is directly fixed to the satellite's ground-facing cabin, and the two unfolded sub-arrays are folded in an embracing manner below the middle sub-array. When in orbit, the two unfolded sub-arrays are unfolded around the sides of the middle sub-array in turn, and the three sub-array 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 final assembly phase. Only the middle sub-array has a mechanical interface with the satellite platform, and the unfolding mechanism and the clamping and releasing mechanism of the two unfolded sub-arrays only have a mechanical interface with the middle sub-array. Since the SAR antenna is folded on a cabin of the satellite platform, the height of the satellite platform can be reduced a lot and is not affected by the antenna, which is convenient for the layout of multiple satellites and adapting to more carrying envelope space.

[0004] The mass of the SAR antenna accounts for about 40% of the mass of the entire satellite. As the most important single unit on the satellite, the configuration, equipment layout, and structural design of the satellite platform structure all affect the mechanical environment of the SAR antenna installation interface. From the perspective of SAR antenna design, the SAR antenna is heavy, generally not less than 100kg, and has a complex structure. It is difficult for it to achieve high rigidity and structural strength. Therefore, the smaller the mechanical environment of the SAR antenna, the better, which puts forward higher requirements on the satellite platform structure. Summary of the invention

[0005] The purpose of this application is to provide a satellite platform suitable for an embracing SAR antenna, which has greater structural rigidity and a lower satellite platform height. By optimizing the position and structure of concentrated load-bearing embedded parts, the load force of large-mass equipment can be effectively transferred to the carrier.

[0006] In order to achieve the above-mentioned object, the present invention provides a satellite platform suitable for an encircling SAR antenna, comprising 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 portions where the partition plates are connected, and the cabin plate portions where the antenna mounting bosses are connected and installed with the satellite-rocket adapter adapters are respectively provided with concentrated load-bearing embedded parts, and the concentrated load-bearing embedded parts are arranged inside the corresponding cabin plates.

[0007] In an optional embodiment, 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.

[0008] In an optional embodiment, the cabin plate includes a lower cabin plate, on which is disposed a first concentrated load-bearing embedded part corresponding to the star-rocket adapter adapter, 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, and a plurality of the threaded holes are disposed on the side of the first concentrated load-bearing embedded part.

[0009] In an optional embodiment, the cabin panel includes a front cabin panel and a rear cabin panel; 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 rear and a second reinforcing rib arranged between the second aluminum skins, and a plurality of threaded hole bosses are arranged on the second aluminum skin, the first threaded hole boss located at the upper part constitutes a satellite hanging interface, and the second threaded hole boss located at the lower part 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.

[0010] In an optional embodiment, the front deck and the rear deck are further 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 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.

[0011] In an optional embodiment, the cabin plate includes an upper cabin plate, on which is disposed a fourth concentrated load-bearing embedded part corresponding to the antenna mounting boss, and the fourth concentrated load-bearing embedded part includes fourth aluminum skins distributed up and down and fourth reinforcement ribs disposed between the fourth aluminum skins.

[0012] In an optional 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 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.

[0013] In an optional embodiment, 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.

[0014] In an optional embodiment, the antenna mounting bosses include two pairs arranged on the top of the board box shell, and the satellite-rocket adapter adapters include two pairs arranged on the bottom of the board 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 board box shell; The concentrated load-bearing embedded parts opposite to the partition are arranged at the top corners of the partition.

[0015] In an optional embodiment, the antenna mounting boss and the star-rocket adapter are connected to the middle of the box shell, and the cabin panel and the partition include aluminum-skinned honeycomb sandwich panels.

[0016] By providing a flat board box shell, the overall height of the satellite platform can be reduced, and combined with the partition located inside the board box shell, the overall structural rigidity of the satellite platform can be improved.

[0017] The top surface of the box shell includes the antenna mounting surface, and the bottom surface of the box shell includes the satellite-rocket docking surface. Combined with lowering the overall height of the satellite platform, the installation distance from the satellite-rocket docking surface to the SAR antenna can be shortened, thereby weakening the amplification factor of the mechanical environment at the SAR antenna installation interface.

[0018] By connecting the antenna mounting boss at the edge of the top surface, connecting the satellite-rocket adapter adapter at the bottom of the side, and arranging concentrated load-bearing embedded parts at the cabin plate portion where the partition is connected and at the cabin plate portion where the antenna mounting boss and the satellite-rocket adapter adapter are connected and installed, the position and structural shape of the concentrated load-bearing embedded parts in each cabin plate of the satellite platform can be optimized. By arranging the concentrated load-bearing embedded parts inside the cabin plate, the load force of large mass equipment can be effectively transferred to the carrier.

[0019] The setting of the antenna mounting boss and the satellite-rocket adapter adapter can simplify the integration of the antenna and the satellite platform. Combined with connecting the antenna mounting boss and the satellite-rocket adapter adapter in the middle of the box shell, only the middle sub-array and the satellite platform have a mechanical interface, which simplifies subsequent assembly and operation.

[0020] Other features and advantages of the present application will be described in detail in the subsequent detailed description. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] 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 certain embodiments of the present application and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without paying creative work.

[0022] Figure 1 It is a structural schematic diagram of the phased array antenna in the folded state; Figure 2 It is a structural schematic diagram of the phased array antenna in the unfolded state; Figure 3 This is a schematic diagram of the overall structure of a satellite platform applicable to a wraparound SAR antenna in this application; Figure 4 This is a schematic diagram of the split structure of the satellite platform; Figure 5 It is a schematic diagram of the connection structure between the front deck and the lower deck; Figure 6 It is a schematic diagram of the positioning structure between the front deck and the lower deck; Figure 7 It is a structural schematic diagram of the lower deck; Figure 8 This is a schematic diagram of the overall structure of the first concentrated load-bearing embedded parts; Fig. 9 is a schematic cross-sectional structural diagram of the first concentrated load-bearing embedded part; Fig.10 It is a structural schematic diagram of the rear deck; Fig.11 It is a schematic diagram of the overall structure of the second concentrated load-bearing embedded parts; Fig.12 It is a schematic diagram of the overall structure of the concentrated load-bearing embedded parts at the bottom of the partition; Fig.13 It is a schematic diagram of the overall structure of the concentrated load-bearing embedded parts on the upper part of the partition; Fig.14 It is a structural schematic diagram of the upper deck; Fig.15 It is a schematic diagram of the overall structure of the antenna mounting boss and the fourth concentrated load-bearing embedded part; Fig.16 It is a schematic diagram of the cross-sectional structure of the load-bearing embedded parts in the fourth set; Fig.17 This is a schematic diagram of the structure of the star-rocket adapter from one perspective; Fig.18 This is a structural diagram of the star-rocket adapter from another perspective; Fig.19 It is a perspective installation diagram of different concentrated load-bearing embedded parts on the box shell.

[0023] icon: 01-step through hole; 02-threaded hole; 03-blind hole; 04-blind hole; 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 panel; 8-satellite-rocket adapter; 9-antenna mounting boss; 11-first concentrated load-bearing embedded part; 111-first aluminum skin; 112-first reinforcing rib; 21-second concentrated load-bearing embedded part; 211-second aluminum skin; 212-second reinforcing rib; 213-first threaded hole boss; 214-second threaded hole boss; 31-third concentrated load-bearing embedded part; 31a-concentrated load-bearing embedded part at the lower part of the partition; 31b-concentrated load-bearing embedded part at the upper part of the partition; 41-the fourth concentrated load-bearing embedded part; 411-the fourth aluminum skin; 412-the fourth reinforcing rib; 413-the antenna mounting threaded hole; 81 - connecting through hole; 82 - first threaded hole; 83 - second threaded hole; 84 - third threaded hole; 85 - fourth threaded hole. DETAILED DESCRIPTION

[0024] 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.

[0025] 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.

[0026] 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.

[0027] 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.

[0028] See also Figure 3 , combined with Figure 4-Figure 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.

[0029] 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.

[0030] 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.

[0031] 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.

[0032] 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.

[0033] 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.

[0034] 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.

[0035] 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.

[0036] 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.

[0037] 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.

[0038] See also Figure 4 The satellite platform's box cabin shell mainly includes a lower cabin plate 1, an upper cabin plate 4, a left cabin plate 2, a right cabin plate 5, a front cabin plate 6, a rear cabin plate 3, a partition plate 7 and four star-rocket adapter seats 8.

[0039] The left and right decks 2 and 5 have the same structural features, and the front and rear decks 6 and 3 have the same structural features. Based on the structure in the attached drawings, the antenna mounting bosses 9 and the satellite-rocket adapter adapters 8 each include two pairs, which are arranged on the front and rear sides of the box shell.

[0040] The cabin plates are respectively provided with stepped through holes 01 and / or threaded holes 02, and the cabin plates are connected by screws passing through the stepped through holes 01 and screwed into the threaded holes 02; the cabin plates are respectively provided with light holes 03 and / or blind holes 04, and the cabin plates are positioned and installed by positioning pins passing through the light holes 03 and embedded in the blind holes 04.

[0041] Specifically, the connection between the panels is Figure 5 as well as Figure 6Taking the connection between the lower deck plate 1 and the front deck plate 6 in the figure as an example, the lower deck plate 1 and the front deck plate 6 are respectively provided with a stepped through hole 01 and a threaded hole 02. The screw passes through the stepped through hole 01 of the front deck plate 6 and is screwed into the threaded hole 02 of the lower deck plate 1 connected thereto to realize the connection of the two deck plates. The connection of other deck plates is similar.

[0042] In order to ensure the accuracy of repeated installation of the cabin panels, the cabin panels are repeatedly disassembled and positioned by pins. Blind holes 04 and light holes 03 are respectively provided on the lower cabin panel 1 and the front cabin panel 6. The positioning pin passes through the light hole 03 on the front cabin panel 6 and is embedded in the blind hole 04 on the lower cabin panel 1 connected thereto, so as to ensure the positioning and installation accuracy between the cabin panels.

[0043] Based on the fact that the star-rocket adapter adapter 8 is arranged at the bottom of the side of the box shell, taking the lower deck 1 included in the deck as an example, see Figure 7 The lower cabin plate 1 is provided with stepped through holes 01 for connecting with other cabin plates, threaded holes 02 and blind holes 04 for positioning. In addition to the connecting holes, the lower cabin plate 1 is also provided with four first concentrated load-bearing embedded parts 11 corresponding to the satellite-rocket adapter adapter 8.

[0044] See also Figure 8 The overall structural diagram of the first concentrated load-bearing embedded part 11 is shown in FIG. Fig. 9 The cross-sectional structural diagram of the first concentrated load-bearing embedded part 11 is shown. The first concentrated load-bearing embedded part 11 serves to transfer and disperse the connecting force of the satellite-rocket adapter adapter 8 on the box shell to the lower cabin plate 1.

[0045] The first concentrated load-bearing embedded part 11 is a machined part, which is composed of first aluminum skins 111 distributed up and down and first reinforcing ribs 112 staggered horizontally and vertically between the first aluminum skins 111. The first aluminum skins 111 distributed up and down can improve the local bending strength of the lower deck 1, and the first reinforcing ribs 112 play the role of connecting the upper and lower first aluminum skins 111 and transmitting force. Three threaded holes 02 are arranged on the side of the first concentrated load-bearing embedded part 11, which can be connected to other decks.

[0046] The cabin plate includes a front cabin plate 6 and a rear cabin plate 3, and the front cabin plate 6 and the rear cabin plate 3 are both provided with second concentrated load-bearing embedded parts 21 corresponding to the satellite-rocket adapter adapter 8. Combined with the edge of the antenna mounting boss 9 on the top surface of the box shell, and the connection of the satellite-rocket adapter adapter 8 at the bottom of the side corresponding to the antenna mounting boss 9, the second concentrated load-bearing embedded parts 21 are required to transmit the connecting force of the two structures. Based on this, the second concentrated load-bearing embedded parts 21 penetrate the entire cabin plate from top to bottom. At the same time, based on the two pairs respectively included in the two structures, the second concentrated load-bearing embedded parts 21 on the front cabin plate 6 and the rear cabin plate 3 respectively include two arranged on both sides, and each second concentrated load-bearing embedded part 21 corresponds to the installation position of the top antenna mounting boss 9 and the bottom satellite-rocket adapter adapter 8.

[0047] Combination Fig.10 Taking the rear deck 3 as an example, the rear deck 3 is provided with a stepped through hole 01 for connecting with other decks, a threaded hole 02, a light hole 03 and a blind hole 04 for positioning, and two second concentrated load-bearing embedded parts 21 that penetrate the entire deck up and down are respectively arranged on both sides. At the same time, based on the setting of the partition 7, third concentrated load-bearing embedded parts 31 corresponding to the partition 7 are also respectively provided on the front deck 6 and the rear deck 3.

[0048] From the perspective of explaining the two different concentrated load-bearing embedded parts set on the same deck, combined with Fig.11 The second concentrated load-bearing embedded part 21 includes a second aluminum skin 211 distributed front and back and a second reinforcing rib 212 arranged between the second aluminum skins, and a plurality of threaded hole bosses 02 are arranged on the second aluminum skin on one side. The plurality of threaded hole bosses 02 form two groups, including a first threaded hole boss 213 and a second threaded hole boss 214 respectively.

[0049] The first threaded hole boss 213 located at the upper portion constitutes a satellite hanging interface, and the second threaded hole boss 214 located at the lower portion constitutes a mounting interface of the satellite-rocket adapter adapter 8 .

[0050] The top end surface of the second concentrated load-bearing embedded part 21 is provided with two threaded holes 02 for connecting with the upper deck 4 , and the bottom is provided with three stepped through holes 01 in the thickness direction for connecting with the lower deck 1 .

[0051] Combination Fig.12 as well as Fig.13 The third concentrated load-bearing embedded part 31 includes two triangular embedded parts with their tips facing each other and arranged top and bottom, respectively including a concentrated load-bearing embedded part 31a at the lower part of the partition and a concentrated load-bearing embedded part 31b at the upper part of the partition. The concentrated load-bearing embedded part 31a at the lower part of the partition and the concentrated load-bearing embedded part 31b at the upper part of the partition both include aluminum skins and reinforcing ribs.

[0052] In order to be distinguishable, the tip of the concentrated load-bearing embedded part 31a at the bottom of the partition is facing upward, and a stepped through hole 01 is provided in the thickness direction for connection with the partition 7.

[0053] The tip of the concentrated load-bearing embedded part 31b on the upper part of the partition is facing downward, and a threaded hole 02 is provided on the top end surface for connecting with the upper cabin plate 4.

[0054] See also Fig.14 , and combined with Figure 15-16From the perspective of the structure of the antenna mounting boss 9 and the structure of the upper deck 4, the upper deck 4 is provided with a stepped through hole 01 for connecting with other decks. At the same time, based on the connection of the antenna mounting boss 9 on the upper deck 4, four fourth concentrated load-bearing embedded parts 41 corresponding to the antenna mounting boss 9 are provided on the upper deck 4. The fourth concentrated load-bearing embedded parts 41 include fourth aluminum skins 411 distributed up and down and fourth reinforcement ribs 412 arranged between the fourth aluminum skins 411.

[0055] The antenna mounting boss 9 includes a U-shaped boss, which is connected to the fourth aluminum skin 411 located at the top, and a plurality of antenna mounting threaded holes 413 are arranged on the U-shaped boss. Two stepped through holes 01 are arranged in the outer thickness direction of the fourth concentrated load-bearing embedded part 41 for connecting with other cabin panels.

[0056] See also Figure 17-Figure 18 The satellite-rocket adapter 8 of the present invention includes a satellite connection surface and other accessory component connection surfaces. The satellite connection surface and the accessory component connection surface are vertically arranged, which is more suitable for launching when the satellite is side-mounted on a carrier bracket.

[0057] A plurality of interfaces are reserved on the star-rocket adapter adapter 8, including a connecting through hole 81, a first threaded hole 82, a second threaded hole 83, a third threaded hole 84 and a fourth threaded hole 85.

[0058] Among them, the connecting through hole 81 is the connection interface with the second threaded hole boss 214 on the second concentrated load-bearing embedded part 21; the first threaded hole 82 is the installation interface with the satellite-rocket separation switch; the second threaded hole 83 is the installation interface with the satellite reference prism; the third threaded hole 84 is the installation interface with the satellite-rocket adapter; the fourth threaded hole 85 is used as the external lifting interface of the entire satellite, thereby simplifying the number of external interfaces of the satellite platform structure and simplifying subsequent assembly and operation.

[0059] See also Fig.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.

[0060] 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.

[0061] 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; 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. 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; 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.

[0062] It should be noted that, in the absence of conflict, the features in the embodiments of this application may be combined with each other.

[0063] 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 portions where the partition plates are connected, and the cabin plate portions where the antenna mounting bosses are connected and installed with the satellite-rocket adapter adapters are respectively provided with concentrated load-bearing embedded parts, and the concentrated load-bearing embedded parts are arranged inside the corresponding cabin plates.

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: The cabin plate includes a lower cabin plate, on which a first concentrated load-bearing embedded part corresponding to the star-rocket adapter adapter is arranged, the first concentrated load-bearing embedded part includes a first aluminum skin distributed up and down and a first reinforcing rib staggered horizontally and vertically between the first aluminum skins, and a plurality of threaded holes are arranged on the side of the first concentrated load-bearing embedded part.

4. The satellite platform according to claim 1, characterized in that: 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 rear and a second reinforcing rib arranged between the second aluminum skins, and a plurality of threaded hole bosses are arranged on the second aluminum skin, the first threaded hole boss located at the upper part constitutes a satellite hanging interface, and the second threaded hole boss located at the lower part 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 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 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 cabin plate includes an upper cabin plate, on which a fourth concentrated load-bearing embedded part corresponding to the antenna mounting boss is arranged, and 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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