Splicing type frame structure for flat plate type satellite

Abstract

The invention provides a spliced frame structure for a flat plate type satellite, and belongs to the technical field of satellite structures. The problems that an existing satellite frame is high in production cost and difficult to produce in batches are solved. The beam unit comprises an X-axis beam unit, a Y-axis beam unit and an inclined beam unit, the X-axis beam unit and the Y-axis beam unit are arranged in an orthogonal mode, an included angle is formed between the inclined beam unit and the X-axis beam unit, the X-axis beam unit comprises a first X-axis beam, a second X-axis beam, a third X-axis beam and a fourth X-axis beam, and the X-axis beam unit comprises a first X-axis beam, a second X-axis beam, a third X-axis beam and a fourth X-axis beam. The Y-axis beam unit comprises a first Y-axis beam, a second Y-axis beam and a third Y-axis beam, the oblique beam unit comprises a first oblique beam and a second oblique beam, and the splicing unit comprises a Y-axis separation mechanism connector and an X-axis separation mechanism connector. The frame structure is mainly used for a flat plate type satellite.

Description

Technical Field

[0001] The invention belongs to the technical field of satellite structures, and in particular relates to a spliced ​​frame structure for a flat-plate satellite. Background Art

[0002] With the continuous updating of satellite manufacturing technology, the diversity of satellite structures has provided convenience for the realization of carrying different single machines. In order to improve the utilization rate of satellite space layout in the fairing, the key to improving launch efficiency and reducing launch costs is to use multiple satellites in one launch. The traditional box-type structure has insufficient space utilization, requires a large fairing space, and has low assembly efficiency, making it difficult to achieve mass production.

[0003] Small satellites need to reduce the structural mass as much as possible, increase the mass ratio of the payload, and improve the space utilization of the satellite in the fairing, while meeting the requirements of structural rigidity and strength. At present, the commonly used lightweight materials for satellite structural frames are mainly carbon fiber, which can greatly reduce the weight of the structure, but the manufacturing process of carbon fiber structural parts is limited, and the molding method of satellite frames is mainly one-piece mold molding. The large molds used in this molding method are expensive to process, the mold loss is high, and the number of mold uses is limited. In the process of small-batch manufacturing of satellites, when the satellite structural design needs to be iteratively changed, the old carbon fiber frame mold cannot be reused, and the parts need to be re-molded according to the new design. The long structural design time and mold processing time caused by iteration lead to high satellite design iteration costs, which brings troubles to mass production of satellites. Summary of the invention

[0004] In view of this, the present invention aims to propose a spliced ​​frame structure for a flat-panel satellite to solve the problem that the existing satellite frame has high production cost and is difficult to mass produce.

[0005] To achieve the above-mentioned purpose, the present invention adopts the following technical scheme: a splicing frame structure for a flat-panel satellite, which includes a beam unit and a splicing unit, the beam unit includes an X-axis beam unit, a Y-axis beam unit and an oblique beam unit, the X-axis beam unit is arranged orthogonally to the Y-axis beam unit, and there is an angle between the oblique beam unit and the X-axis beam unit, the X-axis beam unit includes a first X-axis beam, a second X-axis beam, a third X-axis beam and a fourth X-axis beam, the Y-axis beam unit includes a first Y-axis beam, a second Y-axis beam and a third Y-axis beam, the oblique beam unit includes a first oblique beam and a second oblique beam, the splicing unit includes a Y-axis separation mechanism joint and an X-axis separation mechanism joint, the Y-axis separation mechanism joint is a T-shaped structure, the two interfaces on the upper part of the T-shaped structure are connected to the first X-axis beam, the interface on the lower part of the T-shaped structure is connected to the first Y-axis beam, the lower end of the first Y-axis beam is connected to the second X-axis beam, and the first X-axis beam The first X-axis beam and the second X-axis beam are connected to each other through a plurality of first oblique beams, wherein two first oblique beams are located at both ends of the first X-axis beam and the second X-axis beam, and the remaining first oblique beams are symmetrically arranged on both sides of the first Y-axis beam, the number of the second Y-axis beams is three, and the three second Y-axis beams are respectively connected to the middle and both sides of the second X-axis beam and the third X-axis beam, a second oblique beam is arranged between adjacent second Y-axis beams, both ends of the second oblique beam are connected to the second X-axis beam and the third X-axis beam, both ends of the third X-axis beam are connected to both ends of the fourth X-axis beam through an X-axis separation mechanism joint, the number of the third Y-axis beams is multiple, and both ends of the multiple third Y-axis beams are connected to the third X-axis beam and the fourth X-axis beam, an octagonal structure is formed by the first X-axis beam, the first oblique beam, the second Y-axis beam, the X-axis separation mechanism joint and the fourth X-axis beam, a plurality of cabins for installing single satellites are formed by the encirclement of the beam unit and the splicing unit, and the plurality of cabins are arranged in the same plane.

[0006] Furthermore, both ends of the first oblique beam, the lower end of the first Y-axis beam, both ends of the second Y-axis beam, both ends of the second oblique beam and both ends of the third Y-axis beam are provided with variable angle joints, and the variable angle joints are connected to the beam units.

[0007] Furthermore, the variable angle joint includes a first connection end, a second connection end and a rotating shaft, the first connection end and the second connection end are rotatably connected via the rotating shaft, and the first connection end and the second connection end are connected to corresponding beam units.

[0008] Furthermore, the outer sides of the Y-axis separation mechanism joint and the X-axis separation mechanism joint are both connected to the satellite-rocket separation mechanism.

[0009] Furthermore, the beam unit is a rectangular tube structure, and the four surfaces of the rectangular tube have equal wall thickness or unequal wall thickness.

[0010] Furthermore, the beam unit is made of carbon fiber material, and the splicing unit is made of aluminum alloy material.

[0011] Furthermore, a connecting corner box is provided in the beam unit.

[0012] Furthermore, flat head rivet nuts are provided at the connection points of the beam units.

[0013] Furthermore, cabin plates are provided on both the upper and lower surfaces of the spliced ​​frame structure.

[0014] Furthermore, the thickness of the spliced ​​frame structure in a direction perpendicular to the distribution plane does not exceed 600 mm, and the length of the spliced ​​frame structure does not exceed 4 m.

[0015] Compared with the prior art, the beneficial effects of the present invention are as follows: the present invention provides a splicing frame structure for flat-panel satellites, and the design of the components in the structure is highly versatile. In the process of iterative satellite design, if the length, width or structural layout of the satellite needs to be changed, the design of the beam unit and the splicing unit can be directly reused without modifying the component design. The variable angle joint in the splicing unit can meet the angle changes within 0-90°, and there is no need to redesign the splicing unit. Therefore, the small satellite using this structural design can quickly adjust the satellite structure layout according to different mission requirements and adapt to single machines of different sizes. The structure only needs to open a mold for the beam unit to produce a size of carbon fiber square tube, and then cut the length of the carbon fiber square tube according to manufacturing requirements, so that the carbon fiber structure mold has a small variety of molds, a simple mold design, and a low mold opening cost. The structure has a small variety of parts and components, a high degree of standardization, and is suitable for mass production.

[0016] The specific advantages are as follows: (1) The flat-plate satellite structure based on the spliced ​​frame structure of the present invention has a small thickness, which can save the internal space of the fairing and improve the utilization rate of the space inside the rocket fairing, so that a single rocket can launch more satellites, facilitate the launch of multiple satellites with one rocket, and increase the construction speed of large-scale satellite constellations.

[0017] (2) The present invention has a simple structure, a small number of parts, is easy to process, has a short production cycle, and can effectively reduce processing and assembly costs.

[0018] (3) The cross-section of the beam unit of the present invention is rectangular, and the four faces of the rectangular tube can be designed with unequal wall thicknesses. The wall thickness of each face can be adjusted individually according to the mechanical conditions borne by the structure, thereby changing the bending and shearing capabilities of the beam unit, making it easier to adjust the mechanical properties of the structure and saving structural weight.

[0019] (4) The present invention adopts a flat head rivet nut to provide a threaded hole for the thin-walled part of the structure, and the flat head rivet nut is installed after drilling. Compared with the support plate nut commonly used in the technical field, the flat head rivet nut has a fast installation speed and uses less man-hours, is suitable for automated batch assembly, and the nut pull-out force is greater than 2kN, with high connection reliability.

[0020] (5) In the present invention, the X-axis beam unit, the Y-axis beam unit, and the oblique beam unit are connected by splicing units to form a whole structure. Variable angle joints are used to realize the splicing of beam units at specific angles. The variable angle joints can realize any angle within the range of 0-90°, thereby realizing the standardization of most splicing units, reducing the types and number of splicing units, making the unit assembly more convenient, saving assembly time, and eliminating the need to redesign beam unit joints of various angles during structural design iterations, thereby reducing the workload of structural design iterations and facilitating the realization of flexible structural design.

[0021] (6) The satellite structure designed by the present invention has low difficulty in installing the internal unit and other structural parts of the satellite, which can effectively reduce the process time required for environmental testing and modification during the satellite manufacturing process.

[0022] (7) The satellite structure designed by the present invention has a small volume, a large installation area, and a high space utilization rate. It can accommodate a large number of single-unit products and increase the number of stacked products in the launch vehicle fairing.

[0023] (8) The satellite structure cabin designed by the present invention is flexible in design. The layout of the beam unit and the splicing unit can be changed according to the satellite design requirements without redesigning the components.

[0024] (9) The satellite-rocket separation mechanism designed by the present invention is used for connecting a satellite to a rocket, and for stacking satellites. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] The accompanying drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the accompanying drawings: Figure 1 This is a schematic diagram of the overall structure of a spliced ​​frame structure for a flat-panel satellite according to the present invention; Figure 2 This is a schematic diagram of an exploded structure of a spliced ​​frame structure for a flat-panel satellite according to the present invention; Figure 3 It is a schematic diagram of the beam unit structure of the present invention; Figure 4 This is a schematic diagram of the joint structure of the Y-axis separation mechanism of the present invention; Figure 5This is a schematic diagram of the variable angle joint structure of the present invention; Figure 6 This is a schematic diagram of the joint structure of the X-axis separation mechanism of the present invention; Figure 7 This is a schematic diagram of the flat head rivet nut connection structure of the present invention; Figure 8 This is a schematic diagram of the connecting corner box structure of the present invention; Fig. 9 The figure is a schematic diagram of the cabin panel connection structure of the present invention.

[0026] In the figure: 1-star-rocket separation mechanism, 2-Y-axis separation mechanism joint, 3-first X-axis beam, 4-variable angle joint, 5-first oblique beam, 6-first Y-axis beam, 7-second X-axis beam, 8-second Y-axis beam, 9-second oblique beam, 10-third X-axis beam, 11-third Y-axis beam, 12-fourth X-axis beam, 13-X-axis separation mechanism joint, 14-connecting corner box, 15-flat head rivet nut, 16-cabin plate. DETAILED DESCRIPTION

[0027] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely explain the technical solutions in the embodiments of the present invention. It should be noted that the embodiments of the present invention and the features in the embodiments can be combined with each other without conflict, and the described embodiments are only part of the embodiments of the present invention, not all of the embodiments.

[0028] See also Figure 1-9The present embodiment is described, a splicing frame structure for a flat-panel satellite comprises a beam unit and a splicing unit, the beam unit comprises an X-axis beam unit, a Y-axis beam unit and an oblique beam unit, the X-axis beam unit is arranged orthogonally to the Y-axis beam unit, an angle is formed between the oblique beam unit and the X-axis beam unit, the X-axis beam unit comprises a first X-axis beam 3, a second X-axis beam 7, a third X-axis beam 10 and a fourth X-axis beam 12, the Y-axis beam unit comprises a first Y-axis beam 6, a second Y-axis beam 8 and a third Y-axis beam 11, the oblique beam unit comprises a first oblique beam 5 and a second oblique beam 9, the splicing unit comprises a Y-axis separation mechanism joint 2 and an X-axis separation mechanism joint 13, the Y-axis separation mechanism joint 2 is a T-shaped structure, two interfaces at the upper part of the T-shaped structure are connected to the first X-axis beam 3, an interface at the lower part of the T-shaped structure is connected to the first Y-axis beam 6, the lower end of the first Y-axis beam 6 is connected to the second X-axis beam 7, the first X-axis beam 3 and the second X-axis beam 7 are connected by a plurality of first The oblique beams 5 are connected, wherein two first oblique beams 5 are located at both ends of the first X-axis beam 3 and the second X-axis beam 7, and the remaining first oblique beams 5 are symmetrically arranged on both sides of the first Y-axis beam 6. The number of the second Y-axis beams 8 is three, and the three second Y-axis beams 8 are respectively connected to the middle and both sides of the second X-axis beam 7 and the third X-axis beam 10. A second oblique beam 9 is arranged between adjacent second Y-axis beams 8, and the two ends of the second oblique beam 9 are connected to the second X-axis beam 7 and the third X-axis beam 10. The two ends of the third X-axis beam 10 are connected to the two ends of the fourth X-axis beam 12 through an X-axis separation mechanism joint 13. The number of the third Y-axis beams 11 is multiple, and the two ends of multiple third Y-axis beams 11 are connected to the third X-axis beam 10 and the fourth X-axis beam 12. An octagonal structure is formed by the first X-axis beam 3, the first oblique beam 5, the second Y-axis beam 8, the X-axis separation mechanism joint 13 and the fourth X-axis beam 12. A plurality of cabins for installing satellite units are formed by the encirclement of beam units and splicing units, and the plurality of cabins are arranged in the same plane.

[0029] In this embodiment, both ends of the first oblique beam 5, the lower end of the first Y-axis beam 6, both ends of the second Y-axis beam 8, both ends of the second oblique beam 9, and both ends of the third Y-axis beam 11 are provided with variable angle joints 4, and the variable angle joints 4 are connected to the beam unit. The variable angle joints 4 include a first connection end, a second connection end, and a rotating shaft, the first connection end and the second connection end are rotatably connected through the rotating shaft, and the first connection end and the second connection end are connected to the corresponding beam unit.

[0030] The outer sides of the Y-axis separation mechanism joint 2 and the X-axis separation mechanism joint 13 are both connected to the rocket-satellite separation mechanism 1. The beam unit is a rectangular tube structure, and the four sides of the rectangular tube have equal wall thickness or unequal wall thickness. The beam unit is made of carbon fiber, and the splicing unit is made of aluminum alloy. A connecting corner box 14 is provided in the beam unit. A flat head rivet nut 15 is provided at the connection of the beam unit. Cabin plates 16 are provided on both the upper and lower surfaces of the spliced ​​frame structure. The thickness of the spliced ​​frame structure perpendicular to the distribution plane does not exceed 600 mm, and the length of the spliced ​​frame structure does not exceed 4 m.

[0031] The embodiments will be described in detail below with reference to the accompanying drawings.

[0032] like Figure 1 and Figure 2 As shown, a splicing frame structure for a flat-panel satellite includes a beam unit and a splicing unit. The beam units are connected by the splicing unit to form a whole structure. The beam unit includes an X-axis beam unit, a Y-axis beam unit and an oblique beam unit. The X-axis beam unit is arranged orthogonally to the Y-axis beam unit. There is an angle between the oblique beam unit and the X-axis beam unit. The X-axis beam unit includes a first X-axis beam 3, a second X-axis beam 7, a third X-axis beam 10 and a fourth X-axis beam 12. The Y-axis beam unit includes a first Y-axis beam 6, a second Y-axis beam 8 and a third Y-axis beam 11. The oblique beam unit includes a first oblique beam 5 and a second oblique beam 9. The splicing unit includes a Y-axis separation mechanism joint 2, an X-axis separation mechanism joint 13 and a variable angle joint 4. The variable angle joint 4 includes a first connection end, a second connection end and a rotating shaft. The first connection end and the second connection end are rotatably connected by the rotating shaft.

[0033] The Y-axis separation mechanism joint 2 is a T-shaped structure, the two interfaces on the upper part of the T-shaped structure are each connected to a first X-axis beam 3, the interface on the lower part of the T-shaped structure is connected to the first Y-axis beam 6, the lower end of the first Y-axis beam 6 is connected to the first connecting end of the variable angle joint 4, and the second connecting end of the variable angle joint 4 is connected to the second X-axis beam 7.

[0034] The first X-axis beam 3 and the second X-axis beam 7 are connected via four first oblique beams 5, wherein two first oblique beams 5 are located at the two ends of the first X-axis beam 3 and the second X-axis beam 7, and the remaining two first oblique beams 5 are symmetrically arranged on both sides of the first Y-axis beam 6, and variable angle joints 4 are arranged at both ends of each first oblique beam 5, the first oblique beam 5 is connected to the first connecting end of the variable angle joint 4, and the second connecting end of the variable angle joint 4 on each first oblique beam 5 is respectively connected to the first X-axis beam 3 and the second X-axis beam 7.

[0035] There are three second Y-axis beams 8, and the three second Y-axis beams 8 are respectively connected to the middle and both sides of the second X-axis beam 7 and the third X-axis beam 10. A second oblique beam 9 is arranged between adjacent second Y-axis beams 8. Both ends of the second oblique beam 9 are connected to the second X-axis beam 7 and the third X-axis beam 10. Both ends of each second Y-axis beam 8 and the second oblique beam 9 are provided with a variable angle joint 4. The second Y-axis beam 8 and the second oblique beam 9 are connected to the first connecting end of the variable angle joint 4, and the second connecting end of the variable angle joint 4 on each second Y-axis beam 8 and the second oblique beam 9 is respectively connected to the second X-axis beam 7 and the third X-axis beam 10.

[0036] The two ends of the third X-axis beam 10 are connected to the two ends of the fourth X-axis beam 12 through the X-axis separation mechanism joint 13. The number of the third Y-axis beams 11 is three. Both ends of each third Y-axis beam 11 are provided with a variable angle joint 4. The third Y-axis beam 11 is connected to the first connecting end of the variable angle joint 4. The second connecting end of the variable angle joint 4 on each third Y-axis beam 11 is respectively connected to the third X-axis beam 10 and the fourth X-axis beam 12. The three third Y-axis beams 11 are arranged in the middle and on both sides of the fourth X-axis beam 12.

[0037] The outer sides of the Y-axis separation mechanism joint 2 and the X-axis separation mechanism joint 13 are both connected to the satellite-rocket separation mechanism 1. The first X-axis beam 3, the second X-axis beam 7, the third X-axis beam 10 and the fourth X-axis beam 12 are arranged in parallel, and the Y-axis separation mechanism joint 2 provides an installation interface for the satellite-rocket separation mechanism. The outer side of the structure is composed of an octagonal structure through the first X-axis beam 3, the first oblique beam 5, the second Y-axis beam 8, the X-axis separation mechanism joint 13 and the fourth X-axis beam 12. The size of the outer side of the structure is designed according to the inner diameter of the fairing, which can maximize the use of the space of the fairing. The inside of the structure is divided into multiple areas on the inner side of the structure through the second X-axis beam 7, the third X-axis beam 10, the first Y-axis beam 6, the second Y-axis beam 8 and the third Y-axis beam 11, the first oblique beam 5 and the second oblique beam 9 to form a cabin section for installing a single satellite. Multiple cabin sections are arranged in the same plane, and threaded holes are provided on the outer side of the beam unit. The satellite payload can be installed on the surface of the beam unit through the threaded holes. The thickness of the structure perpendicular to the distribution plane does not exceed 600 mm, and the length of the spliced ​​frame structure does not exceed 4 m.

[0038] The overall structure is flat, which allows for a larger assembly area and ample installation space between units, allowing for multiple people to work simultaneously, saving the overall assembly time of the satellite and facilitating mass production. The satellite assembly line can also be used to mass-assemble the units and payloads required for the satellite, thereby improving satellite assembly efficiency and reducing assembly costs.

[0039] like Figure 3As shown, the beam unit is a rectangular tube structure made of carbon fiber material, and the cross-section adopts a rectangle with unequal wall thickness on four sides, which provides a larger contact area for the installation of the structure and the single machine. The unequal wall thickness design allows the rectangular tube to change the bending and shearing resistance of the beam unit according to the mechanical conditions borne by the structure, which can more easily adjust the mechanical properties of the structure and save the weight of the structure. The structure is prepared by a prepreg molding process, which is suitable for mass production. The carbon fiber tube can be cut into different lengths according to actual needs. A connecting corner box 14 is provided in the beam unit, and the position where the beam unit is connected to the splicing unit is reinforced by a connecting corner box 14 to increase the local stiffness and strength of the structure. In addition, there are rectangular holes of different sizes at local positions of the beam unit, which are used for the cabin layout of the single-machine cable inside the satellite.

[0040] like Figure 4-Figure 6 As shown, the splicing unit includes a Y-axis separation mechanism joint 2, an X-axis separation mechanism joint 13 and a variable angle joint 4, all of which are made of aluminum alloy. The variable angle joint 4 can meet the angle change within the range of 0-90°.

[0041] like Figure 7 As shown, the connection of the beam unit is provided with a flat head rivet nut 15. Since the cross-section thickness of the beam unit is relatively thin, it is not conducive to processing threads, so the flat head rivet nut 15 is used to provide threaded holes for the thin-walled part of the structure. The flat head rivet nut 15 is installed after drilling holes on the carbon fiber tube. After installation, the flat head rivet nut 15 has a height of 15mm and a pull-out force greater than 2kN. It forms a whole with the carbon fiber tube and becomes a part of the beam unit, effectively avoiding the problems of large operating space requirements, cumbersome assembly, and long assembly time when using hexagonal nuts and pallet nuts.

[0042] like Figure 8 As shown, the connecting corner box 14 adopts a large number of hollow designs to reduce weight. The connecting corner box 14 is designed with ribs to provide support for the carbon fiber tube wall, thereby improving the local stiffness and strength of the carbon fiber tube and preventing the carbon fiber tube wall from being deformed and damaged by the pre-tightening force when the bolts are installed.

[0043] like Fig. 9 As shown, the upper and lower surfaces of the spliced ​​frame structure are provided with cabin panels 16, which form a closed cabin after installation.

[0044] The component design in the above embodiment structure is highly versatile. In the process of iterative satellite design, if the length, width or structural layout of the satellite needs to be changed, the design of the beam unit and the splicing unit can be directly reused without modifying the component design. The variable angle joint in the splicing unit can meet the angle change within 0-90°, and there is no need to redesign the splicing unit. Therefore, the small satellite using this structural design can quickly adjust the satellite structure layout according to different mission requirements and adapt to single machines of different sizes. The structure only needs to open a mold to produce a carbon fiber square tube of one size for the beam unit, and then cut the length of the carbon fiber square tube according to manufacturing requirements, so that the carbon fiber structure mold has fewer types, the mold design is simple, and the mold opening cost is low. The structure has fewer types of components, a high degree of standardization, and is suitable for mass production. The flat-panel satellite structure based on this structure has a smaller thickness, which can save the internal space of the fairing, and can improve the utilization rate of the space inside the rocket fairing, so that a rocket can launch more satellites, facilitate the launch of multiple satellites with one rocket, and improve the construction speed of large-scale satellite constellations.

[0045] The embodiments of the present invention disclosed above are only used to help illustrate the present invention. The embodiments do not describe all the details in detail, nor do they limit the invention to the specific implementation methods described. According to the content of this specification, many modifications and changes can be made. This specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the present invention, so that those skilled in the art can understand and use the present invention well.

Claims

1. A spliced ​​frame structure for a flat-panel satellite, characterized in that: It comprises a beam unit and a splicing unit, wherein the beam unit comprises an X-axis beam unit, a Y-axis beam unit and an oblique beam unit, wherein the X-axis beam unit is arranged orthogonally to the Y-axis beam unit, and an angle exists between the oblique beam unit and the X-axis beam unit, wherein the X-axis beam unit comprises a first X-axis beam (3), a second X-axis beam (7), a third X-axis beam (10) and a fourth X-axis beam (12), wherein the Y-axis beam unit comprises a first Y-axis beam (6), a second Y-axis beam (8) and a third Y-axis beam (11), wherein the oblique beam unit comprises a first oblique beam (5) and a second The splicing unit comprises a Y-axis separation mechanism joint (2) and an X-axis separation mechanism joint (13), wherein the Y-axis separation mechanism joint (2) is a T-shaped structure, wherein two interfaces at the upper part of the T-shaped structure are connected to the first X-axis beam (3), and an interface at the lower part of the T-shaped structure is connected to the first Y-axis beam (6), and the lower end of the first Y-axis beam (6) is connected to the second X-axis beam (7), and the first X-axis beam (3) and the second X-axis beam (7) are connected via a plurality of first oblique beams (5), wherein two first oblique beams (5) are located at the first The invention relates to a first X-axis beam (3) and two ends of a second X-axis beam (7), the remaining first oblique beams (5) are symmetrically arranged on both sides of the first Y-axis beam (6), the number of the second Y-axis beams (8) is three, the three second Y-axis beams (8) are respectively connected to the middle and both sides of the second X-axis beam (7) and the third X-axis beam (10), a second oblique beam (9) is arranged between adjacent second Y-axis beams (8), the two ends of the second oblique beam (9) are connected to the second X-axis beam (7) and the third X-axis beam (10), and the two ends of the third X-axis beam (10) are connected by an X-axis splitter. The separation mechanism joint (13) is connected to both ends of the fourth X-axis beam (12); the third Y-axis beam (11) is in plurality; both ends of the plurality of third Y-axis beams (11) are connected to the third X-axis beam (10) and the fourth X-axis beam (12); an octagonal structure is formed by the first X-axis beam (3), the first oblique beam (5), the second Y-axis beam (8), the X-axis separation mechanism joint (13) and the fourth X-axis beam (12); a plurality of cabins for installing satellite units are formed by the encirclement of beam units and splicing units; and the plurality of cabins are arranged in the same plane.

2. A spliced ​​frame structure for a flat-panel satellite according to claim 1, characterized in that: Both ends of the first oblique beam (5), the lower end of the first Y-axis beam (6), both ends of the second Y-axis beam (8), both ends of the second oblique beam (9) and both ends of the third Y-axis beam (11) are provided with variable angle joints (4), and the variable angle joints (4) are connected to the beam units.

3. The spliced ​​frame structure for a flat-panel satellite according to claim 2, characterized in that: The variable angle joint (4) comprises a first connection end, a second connection end and a rotating shaft, the first connection end and the second connection end are rotationally connected via the rotating shaft, and the first connection end and the second connection end are connected to corresponding beam units.

4. The spliced ​​frame structure for a flat-panel satellite according to claim 1, characterized in that: The outer sides of the Y-axis separation mechanism joint (2) and the X-axis separation mechanism joint (13) are both connected to a satellite-rocket separation mechanism (1).

5. The spliced ​​frame structure for a flat-panel satellite according to claim 1, characterized in that: The beam unit is a rectangular tube structure, and the four surfaces of the rectangular tube have equal wall thickness or unequal wall thickness.

6. The spliced ​​frame structure for a flat-panel satellite according to claim 1, characterized in that: The beam unit is made of carbon fiber material, and the splicing unit is made of aluminum alloy material.

7. The spliced ​​frame structure for a flat-panel satellite according to claim 1, characterized in that: A connecting corner box (14) is arranged in the beam unit.

8. The spliced ​​frame structure for a flat-panel satellite according to claim 1, characterized in that: A flat head rivet nut (15) is provided at the connection of the beam unit.

9. The spliced ​​frame structure for a flat-panel satellite according to claim 1, characterized in that: Both the upper and lower surfaces of the spliced ​​frame structure are provided with cabin boards (16).

10. The spliced ​​frame structure for a flat-panel satellite according to claim 1, characterized in that: The thickness of the spliced ​​frame structure perpendicular to the distribution plane does not exceed 600 mm, and the length of the spliced ​​frame structure does not exceed 4 m.

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