Modularized multifunctional satellite configuration

Abstract

The invention relates to a modular multifunctional satellite configuration which comprises an integrated flat plate, a peripheral frame, a reinforcing frame, four bearing columns and externally-hung side cabins, the integrated flat plate and the reinforcing frame are arranged in the peripheral frame, the number of the externally-hung side cabins is 1-4, the number of the bearing columns is 4, multiple satellites can be stacked in a multi-layer mode through the bearing columns, and the satellites have two stacking modes. One is that four bearing columns between the upper and lower satellites are coaxially stacked; according to the second structure, two force bearing columns between the upper-layer satellite and the lower-layer satellite are coaxially stacked, the other two force bearing columns are provided with compensation columns between the upper-layer satellite and the lower-layer satellite, and the height of the compensation columns adapts to the stacking height design of the interlayer satellites. According to the invention, the engineering requirements of different satellite equipment mounting areas, fairing carrying states and a one-rocket multi-satellite launching mode can be met, a cable mounting bracket does not need to be additionally arranged, the cable network mounting process is simplified, and convenience is provided for batch final assembly of the cable network.

Description

Technical Field

[0001] The invention belongs to the field of aerospace technology, and in particular relates to a modular multifunctional satellite configuration. Background Art

[0002] The low-orbit constellation system has the advantages of low transmission delay, low link loss, and seamless global coverage. It is an important development direction in the field of satellite communications. The low-orbit constellation projects represented by Starlink and OneNet have triggered a new wave of low-orbit constellation development. The low-orbit constellation system is composed of hundreds or thousands of satellites. The coverage of a single low-orbit satellite is small. The number of satellites launched into orbit needs to reach a certain scale before the constellation system can have basic service capabilities. Low-cost and short-cycle deployment has become the key to improving the market competitiveness of low-orbit constellation projects. At the same time, it also puts forward low-cost and rapid production requirements for satellite development for low-orbit satellite contractors.

[0003] Satellite structure, thermal control and cable network products provide mechanical installation interface, thermal control interface and electrical connection interface for onboard electronic equipment respectively. They are important components of satellites to support the normal operation of onboard electronic equipment. In addition to providing installation, support and transmission of launch overload, satellite structure also serves as a carrier for thermal control implementation and onboard cable network installation. Therefore, the production processability of structural products and their adaptability to thermal control implementation and cable network installation will have an important impact on whether satellites can be efficiently and cost-effectively mass-produced.

[0004] Traditional satellite structures use honeycomb sandwich panels, which are composed of surface skins, honeycomb cores, structural adhesives and embedded parts. The structure and thermal control are integrated into a design, and the heat pipes are embedded in the honeycomb sandwich panels. Honeycomb sandwich panels are usually manufactured using hot pressing technology. In an autoclave, the skins, honeycomb cores, structural adhesives and embedded parts are sealed and fixed to the mold with vacuum bags. Under a vacuum state, they go through the processes of heating, pressurizing, heat preservation, cooling and restoring atmospheric pressure. After the structural adhesive is cured, the required honeycomb sandwich panel products are formed. The structural form of honeycomb sandwich panels has many parts, complex processes, long production cycles and high production costs, which cannot meet the low-cost and mass production needs of low-orbit satellites.

[0005] The Chinese patent "Flat-plate satellite platform structure" (authorization announcement number CN114180099B) discloses a flat-plate satellite platform structure, which is characterized by a load-bearing frame in the form of a hollow structure, which is integrally formed using a metal material casting process, and the satellite-borne electronic equipment is dispersedly installed on the load-bearing frame and in multiple accommodating spaces inside the load-bearing frame. This patented technology has the following technical problems: The invention provides a satellite structure solution made of all-metal materials, which solves the problem of mass production of satellite structures through a casting integrated molding process. The hollow-form load-bearing frame cannot provide a good heat pipe installation interface, and thus does not solve the thermal control requirements of satellite-borne electronic equipment. At the same time, the cable network installation path provided by the satellite structure is limited, which is not conducive to the laying and fixing of the cable network.

[0006] The Chinese patent "Mechanical and thermal integrated satellite structure plate and satellite suitable for mass production" (application announcement number CN117429627A) discloses a mechanical and thermal integrated satellite structure plate and satellite suitable for rapid mass production. The satellite structure adopts a metal sheet solution with heat pipe installation grooves, plate reinforcement grooves, plate mounting holes, large heat consumption single-machine installation holes, and ordinary single-machine installation holes. The metal sheet can be produced by die casting, sheet metal, pressurization and other processes. The patented technology has the following technical problems: The invention provides a satellite structure solution made of all-metal materials with heat pipe installation grooves, which solves the problem of mass production of satellite structures and provides a feasible heat pipe installation solution. However, in order to achieve the expected structural stiffness requirements, a large number of reinforcement groove features need to be set on the metal sheet. This feature occupies the installation space of onboard electronic equipment and the heat pipe installation interface, which brings great inconvenience to the layout of onboard equipment. In addition, it is necessary to set up an additional cable mounting bracket for laying and fixing the cable network, which increases the product types and weight of the general assembly direct parts.

[0007] Based on the above technical problems, it is urgent to develop a new type of satellite structure that meets the structural functional requirements while having good functional adaptability such as thermal control implementation and cable network installation, so as to meet the needs of low-cost and mass production of low-orbit satellite structural products. Summary of the invention

[0008] The purpose of the present invention is to overcome the shortcomings of the prior art and provide a modular multifunctional satellite configuration. The satellite configuration of the present invention includes a load-bearing column, a peripheral frame, a reinforcement frame and an integrated flat plate, which supports multi-layer stacking. The load-bearing column, the frame, and the integrated flat plate are modularly designed and used in combination to meet the engineering requirements of different satellite functions, carrier fairing states, and one-shot multi-satellite launch methods. The peripheral frame, the reinforcement frame, and the integrated flat plate constitute the main structure of the satellite. Through the integrated design of the structural thermal control function, an orthogonal heat pipe installation interface is provided on the front and back of the integrated flat plate to meet the heat dissipation requirements of high heat consumption satellite-borne electronic equipment; through the integrated design of the structural electrical function, a cable laying path and a tie installation hole are set at the structural reinforcement beam to meet the installation requirements of the cable network and greatly reduce the design and use of cable installation brackets.

[0009] The above-mentioned purpose of the present invention is mainly achieved through the following technical solutions:

[0010] A modular multifunctional satellite configuration comprises an integrated flat plate, an outer frame, a reinforced frame, a bearing column and an external side cabin, wherein the outer frame comprises two longitudinal frames and two transverse frames, the reinforced frame comprises a plurality of longitudinal beams and transverse beams, and the external side cabin comprises a side cabin frame and a side cabin integrated flat plate; the longitudinal beams and transverse beams are arranged on the integrated flat plate, the integrated flat plate and the reinforced frame are arranged in the outer frame, bearing columns are respectively arranged at the connection between the longitudinal frame and the transverse frame, a connecting frame is arranged on the bearing columns, the side cabin frame and the outer frame are connected to the bearing columns on both sides through the connecting frame, the side cabin integrated flat plate and the integrated flat plate are parallel, and the satellite configuration can be stacked in multiple layers through the bearing columns.

[0011] The number of load-bearing columns is 4, and the number of external side cabins is 1-4.

[0012] The side cabin integrated flat plate is a trapezoidal plate, and the side cabin frame is connected to the bottom edge and two side edges of the side cabin integrated flat plate. The side cabin frame is provided with a mounting interface for connecting the side cabin frame and the connecting frame, and the side cabin integrated flat plate is provided with a side cabin mounting flange for connecting the external side cabin and the outer frame.

[0013] The modular multifunctional satellite configuration includes the following stacking methods: 4 load-bearing columns of the upper and lower satellite configurations are coaxially stacked or 2 load-bearing columns of the upper and lower satellite configurations are coaxially stacked, and compensation columns are set between the other 2 load-bearing columns. The height of the compensation columns is adapted to the design of the inter-layer satellite stacking height.

[0014] The integrated flat plate is a plate-like structure, one side of the surface is a smooth surface, and the other side of the surface is a ribbed surface, the smooth surface is connected to the reinforcement frame, and the ribbed surface is provided with reinforcement ribs.

[0015] A mounting flange is arranged on the outer edge of the integrated flat plate, and the integrated flat plate is connected to the peripheral frame via the mounting flange.

[0016] The longitudinal beam and the cross beam are plate-like structures with a C-shaped cross section, wherein a side wing plate serves as an installation interface between the longitudinal beam and the cross beam and the integrated flat plate.

[0017] The longitudinal frame and the transverse frame are hollow profiles with rectangular cross-sections, and mounting interfaces are arranged at the end faces. The mounting interfaces are connected to the connecting frames to realize the connection between the outer frame and the load-bearing columns.

[0018] The integrated flat panel can be cut according to the installation area requirements of the satellite equipment or the cross-sectional size requirements of the satellite in the fairing. By adaptively adjusting the size of the outer frame and the reinforced frame and combining the load-bearing columns, the flexible design of the satellite structure can be achieved.

[0019] Satellite-borne equipment can be installed on the smooth surface and ribbed surface of the integrated flat plate. Horizontal heat pipes are arranged on the smooth surface in the vertical direction along the reinforcement ribs, and longitudinal heat pipes are arranged on the ribbed surface. The longitudinal heat pipes are orthogonal to the horizontal heat pipes, and cables are arranged on the walls of the outer frame and the reinforcement frame.

[0020] Tie-wrap mounting holes and cable through holes are arranged on the outer frame and the reinforcement frame. Clamps are arranged on the tie-wrap mounting holes for fixing the cables, and the cable through holes are used for the cables to pass through the cabin.

[0021] The integrated flat plate, the reinforcement frame and the peripheral frame are provided with a plurality of through holes and threaded holes for screwing or riveting the transverse heat pipes and the longitudinal heat pipes of the satellite-borne equipment.

[0022] Compared with the prior art, the present invention has at least the following beneficial effects:

[0023] (1) The modular multifunctional satellite configuration of the present invention includes four modules: a load-bearing column, an outer frame, a reinforcement frame, and an integrated flat plate. Each module is adaptively adjusted and used in combination based on the initial design to meet the engineering requirements of different satellite equipment installation areas, carrier fairing states, and one-rocket multi-satellite launch methods.

[0024] (2) The present invention supports the expansion of external side cabins, and the side cabins and the main cabin share the load-bearing column module. In this case, the load-bearing column module adds a rectangular cross-section connection frame according to the side cabin frame angle.

[0025] (3) Each module of the present invention has simple features and is manufactured using a mature, low-cost, and mass-producible mechanical processing method. The interface between modules is clear and the connection links are simple, which is convenient for improving production capacity and meeting the needs of large-scale low-orbit constellation satellite deployment.

[0026] (4) The present invention provides longitudinal and transverse orthogonal heat pipe installation interfaces on both sides of the integrated flat panel module, achieving the effect of embedding heat pipes in traditional honeycomb sandwich panels. The heat pipes of the present invention are connected to the structure by external attachment through assembly processes such as screwing and riveting, avoiding the long cycle and complex multi-step production process of the traditional honeycomb sandwich panel heat pipe pre-embedded design solution.

[0027] (5) The satellite structure of the present invention provides an installation interface for the cable network at the outer frame and the reinforced frame web, without the need for additional cable installation brackets, thus simplifying the cable network installation process and facilitating mass assembly of the cable network. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 This is a schematic diagram of the modular multifunctional satellite configuration of the present invention;

[0029] Figure 2 This is a schematic diagram of the modular multifunctional satellite configuration of the present invention;

[0030] Figure 3 This is a schematic diagram of the integrated flat panel structure of the modular multifunctional satellite configuration of the present invention;

[0031] Figure 4 This is a schematic diagram of the installation of the onboard equipment of the modular multifunctional satellite configuration of the present invention;

[0032] Figure 5 This is a schematic diagram of the expansion of a single side cabin of a modular multifunctional satellite configuration of the present invention;

[0033] Figure 6 It is a schematic diagram of the expansion of the double side cabins of the modular multifunctional satellite configuration of the present invention;

[0034] Figure 7 This is a schematic diagram of a modular multifunctional satellite configuration with double side cabins and multiple satellites stacked in an extended configuration;

[0035] Figure 8 It is a schematic diagram of stacking multiple satellites in a single-side cabin expansion configuration of a modular multi-functional satellite configuration according to the present invention. DETAILED DESCRIPTION

[0036] The present invention is further described in detail below with reference to the accompanying drawings and specific embodiments:

[0037] like Figure 1 , Figure 2 and Figure 5As shown, the modular multifunctional satellite configuration of the present invention includes a modular multifunctional satellite configuration, which is characterized in that: it includes an integrated flat plate 1, an outer frame, a reinforced frame, a bearing column 6 and an external side cabin 7, wherein the outer frame includes two longitudinal frames 2 and two transverse frames 3, the reinforced frame includes multiple longitudinal beams 4 and transverse beams 5, and the external side cabin 7 includes a side cabin frame 702 and a side cabin integrated flat plate 701; the longitudinal beams 4 and the transverse beams 5 are arranged on the integrated flat plate 1, the integrated flat plate 1 and the reinforced frame are arranged in the outer frame, the bearing columns 6 are respectively arranged at the connection between the longitudinal frame 2 and the transverse frame 3, and the bearing columns 6 are arranged on the connecting frame 601. The side cabin frame 702 is connected to the bearing columns 6 on both sides through the connecting frame 601, the side cabin integrated flat plate 701 is parallel to the integrated flat plate 1, the number of the bearing columns 6 is 4, and multiple satellites can be stacked in multiple layers through the bearing columns 6.

[0038] The peripheral frames are all made of hollow profiles with rectangular cross-sections, and installation interfaces 202 are set at the end faces to achieve connection with the load-bearing columns 6. The load-bearing columns 6 are hollow cylinders, and connection frames 601 are set at the outer walls. The preferred cross-section is a hollow rectangle, which is used to connect with the side cabin frames 702 of the peripheral frames. The connection frames 601 of the load-bearing columns 6 match the connection frames 202 of the end faces of the longitudinal frames 2, and the two are mechanically connected to form a combination. The preferred mechanical connection methods include rubber screws, riveting, etc. The number of connection frames 601 of the load-bearing columns 6 is 2-4, and the corresponding relationship between this number and the number of external side cabins 7 is: the number of external side cabins 7 connected to the load-bearing columns 6 is 0, and the number of connection frames 601 is 2; the number of external side cabins 7 connected to the load-bearing columns 6 is 1, and the number of connection frames 601 is 3; the number of external side cabins 7 connected to the load-bearing columns 6 is 2, and the number of connection frames 601 is 4.

[0039] like Figure 3 As shown, the cross beam 5 and the longitudinal beam 4 are designed as a metal thin-walled plate structure with a C-shaped cross-section, and the integrated flat plate 1 is a plate-like structure, including a smooth surface 101 and a ribbed surface 102, the smooth surface 101 is connected to a reinforcing frame, and reinforcing ribs 103 are arranged on the surface of the ribbed surface 102, and the thickness of the reinforcing ribs 103 is 1-3 mm.

[0040] The reinforcing rib 103 preferably has an L-shaped cross section and a preferred characteristic cross section thickness of 2 mm. The reinforcing rib 103 is along the length direction of the plate. A mounting flange 104 is provided at the outer edge of the integrated plate 1 to achieve connection with the peripheral frame. The mounting flange 104 has a thickness of 1-3 mm, preferably 2 mm.

[0041] like Figure 4 As shown, the integrated flat surface 101 serves as the main mounting surface of the satellite-borne equipment 8. On the back of the footprint of the satellite-borne equipment, there are reinforcing ribs 103 and longitudinal heat pipes 106. The reinforcing ribs 103 provide rigidity support, and the longitudinal heat pipes 106 are used for equipment heat dissipation.

[0042] The ribbed surface 102 of the integrated flat plate 1 serves as a secondary mounting surface for satellite-borne equipment. The wing plate with longitudinal rib features provides an equipment mounting flange. The satellite-borne equipment mounting surface, the longitudinal rib features, and the area surrounded by the panel are provided with longitudinal heat pipes 106.

[0043] The smooth surface 101 of the integrated flat plate 1 provides a space for laying the transverse heat pipe 105 along the vertical direction of the reinforcing rib 103. The transverse heat pipe 105 is orthogonal to the longitudinal heat pipe 106, providing a better heat dissipation interface for high heat consumption satellite-borne equipment.

[0044] Cables 9 are arranged on the wall of the peripheral frame and the reinforcement frame. The spoke surface of the peripheral frame and the reinforcement frame is used as a cable net laying path, and provides tie installation holes 10 and cable through hole features 11 for cable net binding and fixing and passing through the cabin. A clamp 901 is arranged on the tie installation hole 10 for fixing the cable 9.

[0045] The integrated plate 1, the reinforcement frame and the peripheral frame provide through holes or threaded holes for the installation of the satellite-borne equipment 8 and the heat pipe. The preferred installation process is screwing or riveting. For the threaded hole requirement, it is preferred to use a mounting bracket nut or an adapter block.

[0046] The satellite configuration has modular expansion capability according to the requirements of satellite equipment installation area, multiple satellite launch method, satellite layout method in fairing, etc. The outer side of the peripheral frame supports the design of 7 external side cabins, and the maximum number of external side cabins 7 is 4.

[0047] like Figure 5 , Figure 6 As shown, the external side cabin 7 is composed of a side cabin frame 702 and a side cabin integrated flat plate 701. The side cabin frame 702 is constructed in the same manner as the external frame, and the side cabin integrated flat plate 701 is constructed in the same manner as the integrated flat plate 1. The side cabin frame 702 is provided with a mounting interface for connecting the side cabin frame 702 and the connecting frame 601, and the side cabin integrated flat plate 701 is provided with a side cabin mounting flange 703 for connecting the external side cabin 7 and the external frame.

[0048] like Figure 7 , Figure 8 As shown, the satellites have two stacking methods. One is that four load-bearing columns 6 are coaxially stacked between the upper and lower satellites; the other is that two load-bearing columns 6 are coaxially stacked between the upper and lower satellites, and compensation columns are set at the other two load-bearing columns between the upper and lower satellites. The height of the compensation columns is designed to adapt to the stacking height of the satellites between the layers.

[0049] The height of the load-bearing column is adjusted according to the space requirements for the installation of satellite-borne equipment and the stacking height of satellites between layers.

[0050] The above description is only the best specific implementation mode of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by any technician familiar with the technical field within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention.

[0051] The contents not described in detail in the specification of the present invention belong to the common knowledge of the professionals in this field.

Claims

1. A modular multifunctional satellite configuration, characterized in that: The invention comprises an integrated flat plate (1), an outer frame, a reinforced frame, a bearing column (6) and an external side cabin (7), wherein the outer frame comprises two longitudinal frames (2) and two transverse frames (3), the reinforced frame comprises a plurality of longitudinal beams (4) and transverse beams (5), and the external side cabin (7) comprises a side cabin frame (702) and a side cabin integrated flat plate (701); the longitudinal beams (4) and transverse beams (5) are arranged on the integrated flat plate (1), the integrated flat plate (1) and the reinforced frame are arranged in the outer frame, bearing columns (6) are respectively arranged at the connection between the longitudinal frames (2) and the transverse frames (3), a connecting frame (601) is arranged on the bearing columns (6), the side cabin frame (702) and the outer frame are connected to the bearing columns (6) on both sides through the connecting frame (601), the side cabin integrated flat plate (701) and the integrated flat plate (1) are parallel, and the satellite configuration can be stacked in multiple layers through the bearing columns (6).

2. A modular multifunctional satellite configuration according to claim 1, characterized in that: The number of the load-bearing columns (6) is 4, and the number of the external side cabins (7) is 1-4.

3. A modular multifunctional satellite configuration according to claim 1, characterized in that: The side cabin integrated flat plate (701) is a trapezoidal plate, the side cabin frame (702) is connected to the bottom edge and two side edges of the side cabin integrated flat plate (701), a mounting interface is provided on the side cabin frame (702) for realizing the connection between the side cabin frame (702) and the connecting frame (601), and a side cabin mounting flange (703) is provided on the side cabin integrated flat plate (701) for realizing the connection between the external side cabin (7) and the peripheral frame.

4. A modular multifunctional satellite configuration according to claim 2, characterized in that: The modular multifunctional satellite configuration includes the following stacking methods: four load-bearing columns (6) of the upper and lower satellite configurations are coaxially stacked or two load-bearing columns (6) of the upper and lower satellite configurations are coaxially stacked, and compensation columns are arranged between the other two load-bearing columns (6) of the upper and lower satellite configurations, and the height of the compensation columns is adapted to the design of the inter-layer satellite stacking height.

5. A modular multifunctional satellite configuration according to claim 1, characterized in that: The integrated flat plate (1) is a plate-like structure, one side surface is a smooth surface (101), and the other side surface is a ribbed surface (102), the smooth surface (101) is connected to a reinforcement frame, and reinforcement ribs (103) are arranged on the ribbed surface (102).

6. A modular multifunctional satellite configuration according to claim 1, characterized in that: A mounting flange (104) is provided on the outer edge of the integrated flat plate (1), and the integrated flat plate (1) is connected to the peripheral frame via the mounting flange (104).

7. A modular multifunctional satellite configuration according to claim 1, characterized in that: The longitudinal beam (4) and the cross beam (5) are plate-like structures with a C-shaped cross section, wherein a side wing plate serves as an installation interface between the longitudinal beam (4) and the cross beam (5) and the integrated flat plate (1).

8. A modular multifunctional satellite configuration according to claim 1, characterized in that: The longitudinal frame (2) and the transverse frame (3) are hollow profiles with rectangular cross-sections, and mounting interfaces (202) are arranged at the end surfaces. The mounting interfaces (202) are connected to the connection frames (601) to realize the connection between the peripheral frame and the load-bearing columns.

9. A modular multifunctional satellite configuration according to claim 1, characterized in that: The integrated flat plate (1) can be cut according to the satellite equipment installation area requirements or the satellite cross-sectional size requirements in the fairing, and after the outer frame and the reinforced frame sizes are adaptively adjusted and combined with the load-bearing columns (6), the satellite structure can be flexibly designed.

10. A modular multifunctional satellite configuration according to claim 1, characterized in that: Satellite-borne equipment (8) can be arranged on the smooth surface (101) and the ribbed surface (102) of the integrated flat plate (1), a transverse heat pipe (105) is arranged on the smooth surface (101) in a vertical direction along the reinforcing rib (103), a longitudinal heat pipe (106) is arranged on the ribbed surface (102), the longitudinal heat pipe (106) and the transverse heat pipe (105) are orthogonal, and cables (9) are arranged on the outer frame and the wall surface of the reinforcing frame.

11. A modular multifunctional satellite configuration according to claim 10, characterized in that: The outer frame and the reinforcement frame are provided with a tie installation hole (10) and a cable through hole (11); a clamp (901) is provided on the tie installation hole (10) for fixing the cable (9); and the cable through hole (11) is used for the cable (9) to pass through the cabin.

12. A modular multifunctional satellite configuration according to claim 1, characterized in that: The integrated flat plate (1), the reinforcement frame and the peripheral frame are provided with a plurality of through holes and threaded holes for screwing or riveting the transverse heat pipes (105) and the longitudinal heat pipes (106) of the satellite-borne equipment (8).

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