Satellite configuration with two satellites in one arrow

Abstract

The invention belongs to the technical field of satellite configurations, and discloses a one-rocket double-satellite satellite configuration which is arranged in a fairing, the fairing comprises a conical containing section and a cylindrical containing section, and the cross sectional area of the conical containing section is gradually reduced in the direction away from the cylindrical containing section. The one-rocket double-satellite satellite configuration comprises two satellites. The two satellites are arranged in a central symmetry mode and contained in the fairing, peripheral modules are arranged on the side portions of the satellites, and part of the peripheral modules on the opposite sides of the two satellites are arranged in a staggered mode. The satellite comprises an upper cabin structure and a lower cabin structure which are sequentially arranged, the cross section area of the upper cabin structure is smaller than that of the lower cabin structure, the lower cabin structure is located on the cylindrical containing section, and the upper cabin structure partially extends to be contained in the conical containing section. According to the one-rocket double-satellite satellite configuration, the space utilization rate and the structural compactness can be improved, double-satellite launching of a large-size high-power satellite is achieved, the launching efficiency is improved, and the launching cost is reduced.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of satellite configuration, and particularly relates to a one-rocket two-satellite satellite configuration. BACKGROUND

[0002] A GEO (Geostationary Earth Orbit) communication satellite is a spacecraft operating in a geostationary orbit.

[0003] The GEO communication satellite has the characteristics of large size and high power, and needs a large-area solar cell array and a heat dissipation surface, and the existing GEO communication satellite needs to carry a large amount of propellant, so the volume and size of the GEO communication satellite are relatively large.

[0004] Due to the limitation of the internal space of the rocket, the existing GEO communication satellite with a large volume can only be launched in the form of single-satellite launching, and has the problems of low space utilization, insufficient structural compactness, low launching efficiency and high launching cost.

[0005] Therefore, there is an urgent need for a one-rocket two-satellite satellite configuration to solve the above problems. SUMMARY

[0006] The purpose of the present application is to provide a one-rocket two-satellite satellite configuration which can improve the space utilization and the structural compactness, realize the two-satellite launching of the large-size high-power satellite, improve the launching efficiency and reduce the launching cost.

[0007] To achieve this purpose, the present application adopts the following technical solutions:

[0008] The one-rocket two-satellite satellite configuration is arranged in a fairing, the fairing comprises a conical accommodating section and a cylindrical accommodating section which are arranged in communication in the height direction, and the cross-sectional area of the conical accommodating section gradually decreases in the direction away from the cylindrical accommodating section.

[0009] The one-rocket two-satellite satellite configuration comprises two satellites, the two satellites are arranged in a central symmetrical form and are accommodated in the fairing, and the satellites are provided with external modules on the side portions, and the external modules on the mutually facing sides of the two satellites are arranged in a staggered manner.

[0010] The satellite comprises an upper cabin structure and a lower cabin structure which are sequentially connected and arranged in the height direction, the cross-sectional area of the upper cabin structure is smaller than that of the lower cabin structure, the lower cabin structure is located in the cylindrical accommodating section, and the upper cabin structure is partially extended and accommodated in the conical accommodating section.

[0011] As a preferred scheme of the one-rocket two-satellite satellite configuration provided by the present application, the satellite comprises a frame structure and a side wall structure, the side wall structure is arranged on the circumferential side of the frame structure, and the upper cabin structure and the lower cabin structure are formed in the frame structure.

[0012] As a preferred scheme of the one-rocket two-satellite satellite configuration provided by the present application, the frame structure comprises a plurality of frame beams, and the cross-sectional area of the frame beams arranged in sequence from bottom to top in the height direction gradually decreases.

[0013] As a preferred scheme of the one-rocket two-satellite satellite configuration provided by the present application, the frame beam is internally hollow.

[0014] As a preferred scheme of the one-rocket two-satellite satellite configuration provided by the present application, the frame beam is made of carbon fiber material.

[0015] As a preferred scheme of the one-rocket two-satellite satellite configuration provided by the present application, the frame structure further comprises a connecting piece, the connecting piece is provided with a connecting channel, the frame beam can be inserted into the connecting channel, and the connecting piece comprises an end connecting piece, a middle connecting piece and a top connecting piece arranged in sequence from bottom to top in the height direction.

[0016] The cross-sectional area of the connecting channel of the end connecting piece, the cross-sectional area of the connecting channel of the middle connecting piece and the cross-sectional area of the connecting channel of the top connecting piece gradually decrease; and / or,

[0017] The wall thickness of the end connecting piece, the wall thickness of the middle connecting piece and the wall thickness of the top connecting piece gradually decrease.

[0018] As a preferred scheme of the one-rocket two-satellite satellite configuration provided by the present application, the one-rocket two-satellite satellite configuration further comprises a satellite-rocket separation device, the satellite-rocket separation device comprises a docking flange and a force bearing column, the force bearing column is arranged in the docking flange and connected to the bottom of the satellite; the bottom of the fairing is provided with a satellite support, and the docking flange is detachably connected to the satellite support.

[0019] As a preferred scheme of the one-rocket two-satellite satellite configuration provided by the present application, the force bearing column is a plurality of force bearing columns, and the plurality of force bearing columns are uniformly arranged in the docking flange and connected to the bottom of the satellite.

[0020] As a preferred scheme of the one-rocket two-satellite satellite configuration provided by the present application, the external device module comprises a plurality of attitude and orbit control engines, and the bottom and the side of the satellite are respectively provided with the attitude and orbit control engines; and / or,

[0021] The external device module comprises a plurality of star sensors, and the bottom and the side of the satellite are respectively provided with the star sensors.

[0022] As a preferred scheme of the one-rocket two-satellite satellite configuration provided by the application, the external device module comprises a signal receiving antenna, the signal receiving antenna is arranged on a side of the corresponding satellite facing the other satellite, and the signal receiving antennas of the two satellites in the fairing are arranged in a staggered manner.

[0023] The application has the following beneficial effects:

[0024] The one-rocket two-satellite satellite configuration provided by the application is arranged in a fairing, the fairing comprises a conical accommodating section and a cylindrical accommodating section arranged in communication in the height direction, and the cross-sectional area of the conical accommodating section gradually decreases in the direction away from the cylindrical accommodating section. The one-rocket two-satellite satellite configuration comprises two satellites. Through the above arrangement of the fairing, the launch resistance can be reduced.

[0025] The two satellites are arranged in a central symmetric manner and are accommodated in the fairing, the side of the satellite is provided with an external device module, and the external device modules on the sides facing each other of the two satellites are arranged in a staggered manner. Through the above arrangement, the parallel arrangement of two satellites in the same fairing can be realized, which provides an idea for the arrangement of two satellites for satellites with large height dimensions that cannot be arranged in series in the same fairing. The space utilization and structural compactness are improved, the launch of two satellites of large size and high power is realized, the launch efficiency is improved, and the launch cost is reduced.

[0026] The satellite comprises an upper cabin structure and a lower cabin structure connected and arranged in sequence in the height direction, the cross-sectional area of the upper cabin structure is smaller than that of the lower cabin structure, the lower cabin structure is located in the cylindrical accommodating section, and the upper cabin structure is partially extended and accommodated in the conical accommodating section. Through the above arrangement, the shape of the satellite can be more matched with the shape of the fairing, the space in the fairing can be reasonably utilized, the bending stiffness of a single satellite can be improved, the center of mass of the satellite can be reduced, and the fundamental frequency of the satellite can be improved. BRIEF DESCRIPTION OF DRAWINGS

[0027] In order to more clearly illustrate the technical solutions in the embodiments of the application, the drawings needed to be used in the description of the embodiments of the application will be briefly introduced. Obviously, the drawings in the following description are only some embodiments of the application, and other drawings can be obtained by those skilled in the art without creative labor on the basis of the contents of the embodiments of the application and the drawings.

[0028] Figure 1 is a top view of the arrangement of the satellite in the fairing provided by the embodiments of the application;

[0029] Figure 2 is an internal schematic view of the arrangement of the satellite in the fairing provided by the embodiments of the application;

[0030] Figure 3is a structure schematic of a satellite provided by an embodiment of the present application Figure 1 ;

[0031] Figure 4 is a structure schematic of a satellite provided by an embodiment of the present application Figure 2 ;

[0032] Figure 5 is a deployment schematic of a satellite after ejection provided by an embodiment of the present application

[0033] Figure 6 is a schematic of a frame structure of a satellite provided by an embodiment of the present application

[0034] Figure 7 is a schematic of a lower cabin connecting piece of a satellite provided by an embodiment of the present application

[0035] Figure 8 is a schematic of a middle connecting piece of a satellite provided by an embodiment of the present application

[0036] Figure 9 is a schematic of a satellite-rocket separation device provided by an embodiment of the present application

[0037] Figure 10 is an internal schematic of a lower cabin structure of a satellite provided by an embodiment of the present application

[0038] In the figure:

[0039] 100, fairing; 110, conical accommodating section; 120, cylindrical accommodating section;

[0040] 200, satellite; 210, upper cabin structure; 220, lower cabin structure; 221, fixed mounting frame; 230, frame structure; 231, upper cabin frame beam; 232, lower cabin frame beam; 233, lower cabin connecting piece; 234, upper cabin connecting piece; 235, middle connecting piece; 2351, first connecting passage; 2352, second connecting passage;

[0041] 300, satellite-rocket separation device; 310, docking flange; 320, force bearing column;

[0042] 400, external device module; 410, attitude and orbit control engine; 420, star sensor; 430, signal receiving antenna; 440, heat dissipation panel; 450, solar cell array; 461, lower cabin phased array antenna; 462, lower cabin reflector antenna; 471, upper cabin phased array antenna; 472, upper cabin reflector antenna; 473, TT&C antenna; 480, sun sensor;

[0043] 500, propelling storage tank. DETAILED DESCRIPTION

[0044] The technical solutions of the present application will be further described below in combination with the drawings and through specific embodiments.

[0045] In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be described clearly and completely below in combination with the drawings of the embodiments of the present application. Obviously, the described embodiments are only some of the embodiments of the present application, but not all the embodiments. The components of the embodiments of the present application described and shown in the drawings can be arranged and designed in various different configurations.

[0046] 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 claimed present application, but only represents selected embodiments of the present application. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present application without making creative efforts fall within the scope of protection of the present application.

[0047] It should be noted that: similar reference numerals and letters represent similar items in the following drawings, therefore, once an item is defined in one drawing, it does not need to be further defined and explained in subsequent drawings.

[0048] In the description of the present application, it should be noted that the terms "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship when the product of the present application is usually placed, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the indicated device or element must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application. In addition, the terms "first", "second", "third" and the like are only used to distinguish the description, and cannot be understood as indicating or implying relative importance. In the description of the present application, unless otherwise specified, the meaning of "a plurality of" is two or more.

[0049] In the description of the present application, it should also be noted that, unless otherwise specified and limited, the terms "arranged", "connected", "fixed" should be understood broadly, for example, can be fixedly connected, can be detachably connected, or integrally connected; can be mechanically connected, or electrically connected. For those of ordinary skill in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0050] In the present application, unless otherwise explicitly specified and limited, "on" or "under" of a first feature to a second feature can include that the first and second features are in direct contact, or can include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, "on", "above" and "over" of a first feature to a second feature includes that the first feature is directly above and obliquely above the second feature, or only indicates that the first feature is higher than the second feature in horizontal height. "Under", "below" and "underneath" of a first feature to a second feature includes that the first feature is directly below and obliquely below the second feature, or only indicates that the first feature is lower than the second feature in horizontal height.

[0051] In the present application, the term "and / or" is only used to describe the association relationship of the associated objects, which means that there can be three relationships, for example, A and / or B can represent the three cases of A alone, A and B together, and B alone. In addition, the character " / " in the present application generally represents that the front and rear associated objects are in an "or" relationship.

[0052] The embodiments of the present application are described in detail below, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference signs represent the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by referring to the accompanying drawings are exemplary and are only used to explain the present application, and cannot be understood as a limitation of the present application.

[0053] Figure 1 A top view of the satellite arranged in the fairing according to an embodiment of the present application is shown; Figure 2 An internal schematic view of the satellite arranged in the fairing according to an embodiment of the present application is shown. Referring to Figures 1-2 The present embodiment provides a one-launch dual-satellite satellite configuration. The one-launch dual-satellite satellite configuration is arranged in a fairing 100, and the one-launch dual-satellite satellite configuration includes two satellites 200. The two satellites 200 are loaded in the fairing 100 for launching, and can be separated from the fairing 100 after launching and ascending into orbit for work.

[0054] Specifically, the fairing 100 includes a conical containing section 110 and a cylindrical containing section 120 arranged in communication in the height direction, and the cross-sectional area of the conical containing section 110 gradually decreases in the direction away from the cylindrical containing section 120. Through the above arrangement of the fairing 100, the launch resistance can be reduced.

[0055] More specifically, the two satellites 200 are arranged in a centrally symmetrical manner, both housed within the fairing 100. External modules 400 are located on the sides of each satellite 200, with the portions of these modules 400 facing each other on opposite sides of the two satellites 200 being staggered. This arrangement enables the parallel connection of two satellites 200 within the same fairing 100, providing a solution for satellites 200 with larger dimensions that cannot be arranged in series within the same fairing 100. This improves the space utilization of the fairing 100 and the overall compactness of the dual-satellite configuration, enabling the launch of two large, high-power satellites 200, increasing launch efficiency, and reducing launch costs.

[0056] More specifically, the satellite 200 includes an upper cabin structure 210 and a lower cabin structure 220 connected sequentially along the altitude direction. The cross-sectional area of ​​the upper cabin structure 210 is smaller than that of the lower cabin structure 220. The lower cabin structure 220 is located within the cylindrical receiving section 120, and the upper cabin structure 210 partially extends and is received within the conical receiving section 110. This arrangement allows the shape of the satellite 200 to better match the shape of the fairing 100, achieving efficient use of the space within the fairing 100, increasing the bending stiffness of the individual satellite 200, lowering the center of mass of the satellite 200, and increasing the fundamental frequency of the satellite 200.

[0057] Figure 3 This diagram illustrates the structure of a satellite provided in an embodiment of the present invention. Figure 1 ; Figure 4 This diagram illustrates the structure of a satellite provided in an embodiment of the present invention. Figure 2 . Reference Figure 3 and Figure 4 The peripheral module 400 specifically includes multiple attitude and orbit control engines 410. These engines 410 are located on the bottom and sides of the satellite 200. The peripheral module 400 also includes multiple star sensors 420, which are also located on the bottom and sides of the satellite 200. Compared to the prior art where both the attitude and orbit control engines 410 and star sensors 420 are located on the top of the satellite 200, the arrangement provided in this embodiment can reduce the space occupied by the satellite 200 in the height direction, thereby lowering the center of mass of the satellite 200.

[0058] Continue to refer to Figures 1-3The peripheral module 400 comprises a signal receiving antenna 430. The signal receiving antenna 430 is arranged on the side of the corresponding satellite 200 facing the other satellite 200, and the signal receiving antennas 430 of the two satellites 200 in the fairing 100 are arranged in a staggered manner. The signal receiving antenna 430 is a GNSS antenna in the prior art, which is a core component for signal reception in a satellite navigation system. It provides support for high-precision positioning in complex environments through multi-constellation signal compatibility, centimeter-level positioning technology, and anti-interference design.

[0059] Specifically, the satellite 200 is also provided with a heat dissipation panel 440. The heat dissipation panel 440 is arranged on the opposite sides of the satellite 200. Since the power of the satellite 200 is high, the area of the heat dissipation panel 440 is set to be large, which can extend from the bottom to the top of the satellite 200 in the height direction.

[0060] Figure 5 A satellite deployment diagram after the satellite is deployed out of the cabin is shown. Referring to Figure 5 The satellite 200 is also provided with a solar cell array 450, which is arranged on the side of the heat dissipation panel 440 through a support. When the satellite 200 is deployed out of the cabin, the solar cell array 450 can be deployed to utilize solar energy.

[0061] Specifically, the satellite 200 is also provided with a heat dissipation panel 440. The heat dissipation panel 440 is arranged on the opposite sides of the satellite 200. Since the power of the satellite 200 is high, the area of the heat dissipation panel 440 is set to be large, which can extend from the bottom to the top of the satellite 200 in the height direction.

[0062] Figure 6 A satellite deployment diagram after the satellite is deployed out of the cabin is shown. Referring to Figure 6 The satellite 200 comprises a frame structure 230 and a side wall structure. The side wall structure is arranged on the periphery of the frame structure 230, and forms the upper cabin structure 210 and the lower cabin structure 220 in the frame structure 230.

[0063] Specifically, the frame structure 230 comprises a plurality of frame beams, the frame beams corresponding to the upper cabin structure 210 are upper cabin frame beams 231, and the frame beams corresponding to the lower cabin structure 220 are lower cabin frame beams 232. The cross-sectional area of the upper cabin frame beams 231 is smaller than the cross-sectional area of the lower cabin frame beams 232. Through the above arrangement, the space in the cylindrical accommodating section 120 of the fairing 100 can be more reasonably utilized, and the bending stiffness of the satellite 200 as a whole can be improved, which is conducive to reducing the center of mass of the satellite 200 and improving the fundamental frequency of the satellite 200.

[0064] Specifically, the frame beams are internally hollow. Through the above arrangement, the lightweight target of the satellite 200 can be achieved.

[0065] Optionally, the frame beams are made of carbon fiber material. In the embodiment, high modulus carbon fiber material can be specifically used, which has the characteristics of high temperature resistance, friction resistance, heat conduction facilitation, corrosion resistance, etc.

[0066] Figure 7 A schematic view of an end connector of a satellite provided by an embodiment of the present application is shown; Figure 8 A schematic view of a middle connector of a satellite provided by an embodiment of the present application is shown. Referring to Figures 6-8 The frame structure 230 further comprises connectors. The connectors are provided with connecting channels, and the frame beams can be inserted into the connecting channels. The connectors comprise lower cabin connectors 233 and upper cabin connectors 234. The lower cabin frame beams 232 are connected to each other through the lower cabin connectors 233, and the upper cabin frame beams 231 are connected to each other through the upper cabin connectors 234. The cross-sectional area of the connecting channel of the lower cabin connector 233 is greater than the cross-sectional area of the connecting channel of the upper cabin connector 234, so as to adapt to the connection of the upper cabin frame beams 231 with smaller cross-sectional area and the lower cabin frame beams 232 with larger cross-sectional area.

[0067] Preferably, the wall thickness of the lower cabin connector 233 is greater than the wall thickness of the upper cabin connector 234. Through the above arrangement, the lightweight effect of the frame structure 230 can be further improved under the premise of meeting the connection strength.

[0068] Specifically, since the cross-sectional area of the upper cabin structure 210 is smaller than that of the lower cabin structure 220, the cross-sectional area of the frame structure 230 corresponding to a portion of the upper cabin structure 210 is also smaller than that of the frame structure 230 corresponding to a portion of the lower cabin structure 220. The lower cabin frame beams 232 located at the top of the lower cabin structure 220 and the upper cabin frame beams 231 located at the bottom of the upper cabin structure 210 need to be connected by an intermediate connecting piece 235. The intermediate connecting piece 235 is provided with three first connecting channels 2351 with large cross-sectional areas, which are arranged perpendicular to each other and used to connect the three lower cabin frame beams 232 arranged at an angle. The intermediate connecting piece 235 is also provided with a second connecting channel 2352 with a small cross-sectional area, which is used to connect the one upper cabin frame beam 231 arranged vertically.

[0069] Figure 9 A schematic diagram of a satellite-rocket separation device provided by an embodiment of the present application is shown. Referring to Figure 4 、 Figure 5 and Figure 9 , the one-rocket-two-satellite satellite configuration also includes a satellite-rocket separation device 300. The satellite-rocket separation device 300 includes a docking flange 310 and a load-bearing column 320, which is arranged in the docking flange 310 and connected to the bottom of the frame structure 230. The bottom of the fairing 100 is provided with a satellite support, and the docking flange 310 is detachably connected to the satellite support. When the satellite 200 is ejected from the cabin, the docking flange 310 can rotate relative to the satellite support and be separated from the satellite support, so that the satellite 200 is ejected from the satellite support. The way in which the docking flange 310 is separated from the satellite support is a prior art, and the specific process will not be described here in this embodiment.

[0070] Specifically, the load-bearing column 320 is a plurality of load-bearing columns 320, which are uniformly arranged in the docking flange 310 and connected to the bottom of the frame structure 230. Through the above arrangement, the balance and reliability of the support of the satellite-rocket separation device 300 on the frame structure 230 can be improved.

[0071] Figure 10 A schematic diagram of the inside of a lower cabin structure of a satellite provided by an embodiment of the present application is shown. Referring to Figure 10 , the lower cabin structure 220 is provided with a fixed mounting frame 221. The satellite 200 is also provided with a propellant storage tank 500 for storing propellant energy. The propellant storage tank 500 is in a cylindrical structure, and an annular flange is arranged on the side thereof. The outer side of the annular flange is connected to the inside of a mounting hole formed by the fixed mounting frame 221, so as to realize the fixation of the propellant storage tank 500 in the mounting hole of the fixed mounting frame 221.

[0072] The above description is merely a preferred embodiment of the present invention and an explanation of the technical principles employed. Those skilled in the art should understand that the scope of disclosure in this invention is not limited to technical solutions formed by specific combinations of the above-described technical features, but should also cover other technical solutions formed by arbitrary combinations of the above-described technical features or their equivalents without departing from the above-disclosed concept. For example, technical solutions formed by substituting the above features with (but not limited to) technical features with similar functions disclosed in this invention.

[0073] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the implementation of the present invention. Those skilled in the art will be able to make various obvious changes, readjustments, and substitutions without departing from the scope of protection of the present invention. It is neither necessary nor possible to exhaustively describe all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the scope of protection of the claims of the present invention.

Claims

1. A dual-satellite configuration launched on a single rocket, characterized in that: The fairing (100) is disposed in a fairing (100), which includes a conical receiving section (110) and a cylindrical receiving section (120) connected in the height direction, and the cross-sectional area of ​​the conical receiving section (110) gradually decreases in the direction away from the cylindrical receiving section (120). The dual-satellite configuration includes two satellites (200), which are arranged in a centrally symmetrical manner and are both housed in the fairing (100). The satellites (200) are provided with peripheral modules (400) on their sides, and the peripheral modules (400) on the opposite side of the two satellites (200) are staggered. The satellite (200) includes an upper cabin structure (210) and a lower cabin structure (220) connected sequentially along the altitude direction. The cross-sectional area of ​​the upper cabin structure (210) is smaller than that of the lower cabin structure (220). The lower cabin structure (220) is located within the cylindrical receiving section (120), and the upper cabin structure (210) extends into the conical receiving section (110).

2. The dual-satellite configuration according to claim 1, characterized in that, The satellite (200) includes a frame structure (230) and a side structure. The side structure is disposed on the periphery of the frame structure (230) and forms the upper cabin structure (210) and the lower cabin structure (220) within the frame structure (230).

3. The dual-satellite configuration according to claim 2, characterized in that, The frame structure (230) includes multiple frame beams. The frame beam corresponding to the upper cabin structure (210) is the upper cabin frame beam (231), and the frame beam corresponding to the lower cabin structure (220) is the lower cabin frame beam (232). The cross-sectional area of ​​the upper cabin frame beam (231) is smaller than that of the lower cabin frame beam (232).

4. The dual-satellite configuration according to claim 3, characterized in that, The frame beam is hollow inside.

5. The dual-satellite configuration according to claim 3, characterized in that, The frame beams are made of carbon fiber.

6. The dual-satellite configuration according to claim 3, characterized in that, The frame structure (230) also includes connectors, which have connection channels. The frame beams can be inserted into the connection channels. The connectors include lower cabin connectors (233) and upper cabin connectors (234). The lower cabin frame beams (232) are connected to each other through the lower cabin connectors (233), and the upper cabin frame beams (231) are connected to each other through the upper cabin connectors (234). The cross-sectional area of ​​the connecting channel of the lower cabin connector (233) is larger than the cross-sectional area of ​​the connecting channel of the upper cabin connector (234); and / or, The wall thickness of the lower cabin connector (233) is greater than the wall thickness of the upper cabin connector (234).

7. The dual-satellite configuration according to claim 2, characterized in that, The dual-satellite configuration also includes a satellite-rocket separation device (300), which includes a docking flange (310) and a support column (320). The support column (320) passes through the docking flange (310) and is connected to the bottom of the satellite (200). A satellite support is provided at the bottom of the fairing (100), and the docking flange (310) is detachably connected to the satellite support.

8. The dual-satellite configuration according to claim 7, characterized in that, There are multiple load-bearing columns (320), which are evenly arranged in an array on the docking flange (310) and are all connected to the bottom of the satellite (200).

9. The dual-satellite configuration according to any one of claims 1-8, characterized in that, The peripheral module (400) includes multiple attitude and orbit control engines (410), and the attitude and orbit control engines (410) are respectively disposed on the bottom and sides of the satellite (200); and / or, The peripheral module (400) includes multiple star sensors (420), and the star sensors (420) are respectively provided on the bottom and side of the satellite (200).

10. The dual-satellite configuration according to any one of claims 1-8, characterized in that, The peripheral module (400) includes a signal receiving antenna (430), which is disposed on the side of the corresponding satellite (200) facing the other satellite (200). The signal receiving antennas (430) of the two satellites (200) in the fairing (100) are staggered.

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