A tiled frame structure for a flat panel satellite

Abstract

The application provides a spliced frame structure for a flat plate satellite and belongs to the technical field of satellite structure.The application solves the problems of high production cost and difficulty in batch production of the existing satellite frame.The spliced frame structure comprises a beam unit and a splicing unit.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 orthogonally, and an included angle exists 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.The Y-axis beam unit comprises a first Y-axis beam, a second Y-axis beam and a third Y-axis beam.The inclined beam unit comprises a first inclined beam and a second inclined beam.The splicing unit comprises a Y-axis separation mechanism joint and an X-axis separation mechanism joint.The spliced frame structure is mainly used for the frame structure of a flat plate satellite.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of satellite structure, and particularly relates to a spliced frame structure for a flat-panel satellite. BACKGROUND

[0002] With the continuous updating of satellite manufacturing technology, the diversity of satellite structure provides convenience for carrying different single machines. In order to improve the space layout utilization rate of the satellite in the fairing, launching multiple satellites with one rocket is the key to improve the launch efficiency and reduce the launch cost. The traditional box type structure has insufficient space utilization rate, needs to occupy a large fairing space, and has low general assembly efficiency and is difficult to realize batch production.

[0003] Under the premise of meeting the structural stiffness and strength, small satellites need to reduce the structural mass as much as possible, improve the mass ratio of the load single machine, and improve the space utilization rate of the satellite in the fairing. At present, the commonly used lightweight material of the satellite structure frame is mainly carbon fiber, which can greatly reduce the structure weight, but the manufacturing process of the carbon fiber structure part is limited, and the forming mode of the satellite frame is mainly one-piece mold forming. The large mold used in this forming mode is expensive to process, has high mold wear, and the mold usage frequency is limited. In the process of small batch manufacturing of satellites, when the satellite structure design needs to be iteratively changed, the old carbon fiber frame mold cannot be reused, and the manufacturing of parts according to the new design scheme needs to be re-molded. The iteration of the structure design and the mold processing time is long, which leads to high satellite design iteration cost and brings difficulties to batch satellite production. SUMMARY

[0004] Therefore, the present application aims to provide a spliced frame structure for a flat-panel satellite to solve the problems of high production cost and difficulty in batch production of the existing satellite frame.

[0005] In order to achieve the above object, the present application adopts the following technical scheme: a spliced frame structure for a flat plate satellite, comprising a beam unit and a splicing unit, 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 orthogonally, and there is an included angle 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, the Y-axis beam unit comprises a first Y-axis beam, a second Y-axis beam and a third Y-axis beam, the inclined beam unit comprises a first inclined beam and a second inclined beam, the splicing unit comprises a Y-axis separation mechanism joint and an X-axis separation mechanism joint, the Y-axis separation mechanism joint is a T-shaped structure, two interfaces on the upper part of the T-shaped structure are connected with the first X-axis beam, and the interface on the lower part of the T-shaped structure is connected with the first Y-axis beam, the lower end of the first Y-axis beam is connected with the second X-axis beam, a plurality of first inclined beams are connected between the first X-axis beam and the second X-axis beam, two of the first inclined beams are located at the two ends of the first X-axis beam and the second X-axis beam, and the remaining first inclined beams are symmetrically arranged on the two sides of the first Y-axis beam, the number of the second Y-axis beams is three, 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 inclined beam is arranged between adjacent second Y-axis beams, the two ends of the second inclined beam are connected with the second X-axis beam and the third X-axis beam, the two ends of the third X-axis beam are connected with the two ends of the fourth X-axis beam through the X-axis separation mechanism joint, the number of the third Y-axis beams is multiple, and the two ends of the multiple third Y-axis beams are connected with the third X-axis beam and the fourth X-axis beam, an octagonal structure is formed through the first X-axis beam, the first inclined beam, the second Y-axis beam, the X-axis separation mechanism joint and the fourth X-axis beam, a plurality of cabin sections for installing satellite units are formed through the surrounding of the beam unit and the splicing unit, and the plurality of cabin sections are arranged in the same plane.

[0006] Furthermore, the two ends of the first inclined beam, the lower end of the first Y-axis beam, the two ends of the second Y-axis beam, the two ends of the second inclined beam and the two ends of the third Y-axis beam are all provided with variable angle joints, and the variable angle joints are connected with the beam unit.

[0007] Furthermore, the variable angle joint comprises a first connecting end, a second connecting end and a rotating shaft, the first connecting end and the second connecting end are rotationally connected through the rotating shaft, and the first connecting end and the second connecting end are connected with the corresponding beam unit.

[0008] Furthermore, the Y-axis separation mechanism joint and the X-axis separation mechanism joint are both connected with a satellite-rocket separation mechanism outside.

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

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

[0011] Further, the beam unit is provided with a connecting corner box.

[0012] Further, the connecting part of the beam unit is provided with a flat rivet nut.

[0013] Further, the upper and lower surfaces of the spliced frame structure are provided with deck plates.

[0014] Further, the thickness of the spliced frame structure perpendicular to the distribution plane direction is not more than 600 mm, and the length of the spliced frame structure is not more than 4 m.

[0015] Compared with the prior art, the beneficial effects of the present application are: the present application provides a spliced frame structure for a flat plate satellite, the design of the components in the structure is highly universal, and when the length, width or structural layout of the satellite needs to be changed in the process of satellite iterative design, the component design does not need to be modified, and the design of the beam unit and the spliced unit can be directly reused. The variable angle joint in the spliced unit can meet the angle change within 0-90°, and the spliced unit does not need to be redesigned. Therefore, the small satellite designed using the structure can quickly adjust the satellite structural layout according to different task requirements and adapt to different sizes of single machines. The structure only needs to produce one size of carbon fiber square tube for the beam unit, and then cut the length of the carbon fiber square tube according to the manufacturing requirements, so that the types of carbon fiber structure molds are few, the mold design is simple, and the mold opening cost is low. The structure has few component types, high standardization degree, and is suitable for batch production.

[0016] The specific advantages are as follows:

[0017] (1) The flat plate satellite structure based on the spliced frame structure described in the present application has a small thickness, which can save the internal space of the fairing, can improve the utilization rate of the internal space of the rocket fairing, so that more satellites can be launched by one rocket, facilitating the launch of multiple satellites by one rocket, and improving the construction speed of large-scale satellite constellation.

[0018] (2) The structure of the present application is simple, has few components, is easy to process, has a short production cycle, and can effectively reduce the processing and assembly cost.

[0019] (3) The beam unit section of the present application adopts a rectangular shape, the four surfaces of the rectangular tube can adopt unequal wall thickness design, and the wall thickness of each surface can be adjusted individually according to the mechanical conditions borne by the structure, so as to change the bending resistance and shear resistance of the beam unit, which can more easily adjust the mechanical properties of the structure and save the weight of the structure.

[0020] (4) The flat head rivet nut is used to provide a threaded hole for the thin wall part, and the flat head rivet nut is installed after punching, compared with the commonly used supporting plate nut in the technical field, the flat head rivet nut has the advantages of fast installation speed, less use time, suitable for automatic batch assembly, and the nut pull-off force is greater than 2kN, and the connection reliability is high.

[0021] (5) In the application, the X-axis beam unit, the Y-axis beam unit and the inclined beam unit are connected to form the whole structure through the splicing unit, the variable angle joint is used to realize the splicing of the beam units at a specific angle, the variable angle joint can realize any angle in the range of 0-90°, the standardization of most splicing units is realized, the types and quantities of the splicing units are reduced, the assembly of the units is more convenient, the assembly time is saved, the structure design iteration does not need to redesign the beam unit joints of multiple angles, the workload of the structure design iteration is reduced, and the flexible design of the structure is facilitated.

[0022] (6) The satellite structure designed in the application has low installation difficulty of single machines inside the satellite and other structural parts on the satellite, and can effectively reduce the process time required for environmental test modification in the satellite manufacturing process.

[0023] (7) The satellite structure designed in the application has small volume, large installation area, high space utilization rate, can accommodate a large number of single machine products, and improves the number of stacked placement in the fairing of the carrier rocket.

[0024] (8) The satellite structure designed in the application is flexible in design, the layout of the beam units and the splicing units can be changed according to the design requirements of the satellite, and the parts do not need to be redesigned.

[0025] (9) The satellite-rocket separation mechanism designed in the application is used for the connection of the satellite and the rocket, and the stacking connection between the satellites. BRIEF DESCRIPTION OF DRAWINGS

[0026] The accompanying drawings, which form a part of the present application, are used to provide further understanding of the present application, and the illustrative embodiments of the present application and their descriptions are used to explain the present application, and do not constitute improper limitations on the present application. In the drawings:

[0027] Figure 1 It is a whole structure schematic view of the splicing type frame structure for the flat plate type satellite described in the application;

[0028] Figure 2 It is an explosion structure schematic view of the splicing type frame structure for the flat plate type satellite described in the application;

[0029] Figure 3 It is a beam unit structure schematic view described in the application;

[0030] Figure 4The Y-axis separation mechanism joint structure of the present application is shown in the figure.

[0031] Figure 5 The variable angle joint structure of the present application is shown in the figure.

[0032] Figure 6 The X-axis separation mechanism joint structure of the present application is shown in the figure.

[0033] Figure 7 The flat head rivet nut connection structure of the present application is shown in the figure.

[0034] Figure 8 The connection angle box structure of the present application is shown in the figure.

[0035] Figure 9 The cabin plate connection structure of the present application is shown in the figure.

[0036] In the figure:

[0037] 1 - satellite-rocket separation mechanism, 2 - Y-axis separation mechanism joint, 3 - first X-axis beam, 4 - variable angle joint, 5 - first inclined beam, 6 - first Y-axis beam, 7 - second X-axis beam, 8 - second Y-axis beam, 9 - second inclined beam, 10 - third X-axis beam, 11 - third Y-axis beam, 12 - fourth X-axis beam, 13 - X-axis separation mechanism joint, 14 - connection angle box, 15 - flat head rivet nut, 16 - cabin plate. DETAILED DESCRIPTION

[0038] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application. It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict, and the described embodiments are only a part of the embodiments of the present application, not all the embodiments.

[0039] Reference Figures 1-9The embodiment is illustrated by a spliced frame structure for flat plate satellite, which comprises beam units and splicing units. The beam units comprise X-axis beam units, Y-axis beam units and diagonal beam units. The X-axis beam units and Y-axis beam units are arranged orthogonally, and the diagonal beam units have an included angle with the X-axis beam units. The X-axis beam units comprise 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 units comprise a first Y-axis beam 6, a second Y-axis beam 8 and a third Y-axis beam 11. The diagonal beam units comprise a first diagonal beam 5 and a second diagonal beam 9. The splicing units comprise a Y-axis separation mechanism joint 2 and an X-axis separation mechanism joint 13. The Y-axis separation mechanism joint 2 is in a T-shaped structure. Two interfaces on the upper part of the T-shaped structure are connected with the first X-axis beam 3, and an interface on the lower part of the T-shaped structure is connected with the first Y-axis beam 6. The lower end of the first Y-axis beam 6 is connected with the second X-axis beam 7. The first X-axis beam 3 and the second X-axis beam 7 are connected through a plurality of first diagonal beams 5. Two first diagonal beams 5 are arranged at the two ends of the first X-axis beam 3 and the second X-axis beam 7, and the remaining first diagonal beams 5 are symmetrically arranged on the two sides of the first Y-axis beam 6. The second Y-axis beam 8 is in a number of three. The three second Y-axis beams 8 are respectively connected at the middle and both sides of the second X-axis beam 7 and the third X-axis beam 10. The second diagonal beam 9 is arranged between adjacent second Y-axis beams 8. The two ends of the second diagonal beam 9 are connected with 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 with the two ends of the fourth X-axis beam 12 through the X-axis separation mechanism joint 13. The third Y-axis beam 11 is in a plurality of numbers. The two ends of the plurality of third Y-axis beams 11 are connected with the third X-axis beam 10 and the fourth X-axis beam 12. An octagonal structure is formed through the first X-axis beam 3, the first diagonal 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 cabin sections for mounting satellite units are formed through the enclosure of the beam units and the splicing units. The plurality of cabin sections are arranged in the same plane.

[0040] The two ends of the first diagonal beam 5, the lower end of the first Y-axis beam 6, the two ends of the second Y-axis beam 8, the two ends of the second diagonal beam 9 and the two ends of the third Y-axis beam 11 are provided with variable angle joints 4, which are connected with the beam units. The variable angle joint 4 comprises a first connecting end, a second connecting end and a rotating shaft. The first connecting end and the second connecting end are rotationally connected through the rotating shaft. The first connecting end and the second connecting end are connected with the corresponding beam units.

[0041] The Y-axis separation mechanism joint 2 and the X-axis separation mechanism joint 13 are connected with the star-rocket separation mechanism 1 outside. The beam unit is a rectangular tube structure, and the four surfaces of the rectangular tube are equal or unequal in wall thickness. The beam unit is made of carbon fiber material, and the splicing unit is made of aluminum alloy material. The beam unit is provided with a connecting angle box 14. The connecting part of the beam unit is provided with a flat head rivet nut 15. The upper and lower surfaces of the splicing frame structure are provided with cabin plates 16. The thickness of the splicing frame structure perpendicular to the distribution plane direction is not more than 600 mm, and the length of the splicing frame structure is not more than 4 m.

[0042] The embodiments will be described in detail below with reference to the drawings.

[0043] As shown in Figure 1 and Figure 2 A splicing frame structure for a flat plate satellite includes a beam unit and a splicing unit, the beam unit is connected through the splicing unit to form the whole structure, the beam unit includes 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 orthogonally, and there is an included angle between the inclined 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 inclined beam unit includes a first inclined beam 5 and a second inclined beam 9, and 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 connecting end, a second connecting end and a rotating shaft, and the first connecting end and the second connecting end are rotationally connected through the rotating shaft.

[0044] The Y-axis separation mechanism joint 2 is a T-shaped structure, two interfaces on the upper part of the T-shaped structure are connected with one first X-axis beam 3 respectively, and the interface on the lower part of the T-shaped structure is connected with a first Y-axis beam 6, the lower end of the first Y-axis beam 6 is connected with the first connecting end of the variable angle joint 4, and the second connecting end of the variable angle joint 4 is connected with a second X-axis beam 7.

[0045] The first X-axis beam 3 and the second X-axis beam 7 are connected through four first inclined beams 5, two of which are located at the two ends of the first X-axis beam 3 and the second X-axis beam 7, and the other two are symmetrically arranged on the two sides of the first Y-axis beam 6, the two ends of each first inclined beam 5 are provided with a variable angle joint 4, the first inclined beam 5 is connected with the first connecting end of the variable angle joint 4, and the second connecting end of the variable angle joint 4 on each first inclined beam 5 is connected with the first X-axis beam 3 and the second X-axis beam 7 respectively.

[0046] The second Y-axis beam 8 is three in number, and 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, and a second inclined beam 9 is arranged between adjacent second Y-axis beams 8, and the two ends of the second inclined beam 9 are connected to the second X-axis beam 7 and the third X-axis beam 10, and a variable angle joint 4 is arranged at the two ends of each second Y-axis beam 8 and second inclined beam 9, and the second Y-axis beam 8 and the second inclined 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 second inclined beam 9 is respectively connected to the second X-axis beam 7 and the third X-axis beam 10.

[0047] 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, and the third Y-axis beam 11 is three in number, and a variable angle joint 4 is arranged at the two ends of each third Y-axis beam 11, and the third Y-axis beam 11 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 third Y-axis beam 11 is respectively connected to the third X-axis beam 10 and the fourth X-axis beam 12, and the three third Y-axis beams 11 are arranged in the middle and on both sides of the fourth X-axis beam 12.

[0048] The Y-axis separation mechanism joint 2 and the X-axis separation mechanism joint 13 are connected to the star rocket separation mechanism 1 on the outside. 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 a mounting interface for the star rocket separation mechanism. The outside of the structure is composed of an octagonal structure through the first X-axis beam 3, the first inclined beam 5, the second Y-axis beam 8, the X-axis separation mechanism joint 13 and the fourth X-axis beam 12, and the size of the outside of the structure is designed according to the inner diameter of the fairing, so that the space of the fairing can be utilized to the greatest extent. The inside of the structure is divided into multiple areas 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 inclined beam 5 and the second inclined beam 9, and a cabin section for mounting satellite single machines is formed, and multiple cabin sections are arranged in the same plane, and screw holes are provided on the outside of the beam unit, and satellite loads can be mounted on the surface of the beam unit through the screw holes. The thickness of the structure perpendicular to the distribution plane direction is not more than 600mm, and the length of the spliced frame structure is not more than 4m.

[0049] The overall structure of the structure is flat, so that the total assembly area is larger, the installation space between single machines is sufficient, multiple people can work at the same time, the overall assembly time of the satellite is saved, batch production is easy to realize, and satellite single machines and loads required for satellite assembly can be assembled through a satellite assembly line, satellite assembly efficiency is improved, and assembly cost is reduced.

[0050] As Figure 3As shown, the beam unit is a rectangular tube structure of carbon fiber material, the cross section adopts four unequal wall thickness of rectangle, which provides larger contact area for the installation of structure and single machine, and the unequal wall thickness design can change the bending resistance and shear resistance of the rectangular tube according to the mechanical conditions of the structure, so that the mechanical properties of the structure can be easily adjusted, and the weight of the structure is saved. The structure is prepared by using prepreg molding process, which is suitable for batch production, and the carbon fiber tube can be cut into different lengths according to actual needs. The beam unit is provided with a connecting corner box 14, and the connecting position of the beam unit and the splicing unit is enhanced by the connecting corner box 14 to increase the local stiffness and strength of the structure. In addition, the local position of the beam unit has rectangular holes of different sizes, which are used for the cabin arrangement of the internal single machine cable of the satellite.

[0051] As shown in Figures 4-6 The splicing unit includes Y-axis separation mechanism joint 2, X-axis separation mechanism joint 13 and variable angle joint 4, which are made of aluminum alloy material. The variable angle joint 4 can meet the angle change in the range of 0-90°.

[0052] As shown in Figure 7 The connecting position of the beam unit is provided with a flat head rivet nut 15. Since the cross section of the beam unit is thin, it is not conducive to process threads, so the flat head rivet nut 15 is used to provide threaded holes for the thin-walled part of the structure. After punching holes on the carbon fiber tube, the flat head rivet nut 15 is installed, and the height of the flat head rivet nut 15 after installation is 15mm, the pulling force is greater than 2kN, and the carbon fiber tube forms an integral whole, which becomes part of the beam unit, effectively avoiding the problems of large operation space requirement, complicated assembly, long assembly time and the like when using hexagonal nut and backing nut.

[0053] As shown in Figure 8 The connecting corner box 14 adopts a large number of hollow design for weight reduction, and the connecting corner box 14 is designed with a rib plate to provide support for the carbon fiber tube wall, thereby improving the local stiffness and strength of the carbon fiber tube, and avoiding deformation and damage of the carbon fiber tube wall caused by pre-tightening force during bolt installation.

[0054] As shown in Figure 9 The upper and lower surfaces of the splicing type frame structure are provided with cabin plates 16, which form a closed cabin after installation.

[0055] The parts in the above embodiment structure have strong design universality, and in the process of iterative design of the satellite, if the length, width or structural layout of the satellite needs to be changed, the part design does not need to be modified, and the design of the beam unit and the splicing unit can be directly reused. The variable-angle joint in the splicing unit can meet the angle change within 0-90°, and the splicing unit does not need to be redesigned. Therefore, the small satellite using the structure design can quickly adjust the satellite structural layout according to different task requirements, and adapt to different sizes of single machines. The structure only needs to produce one size of carbon fiber square tube for the beam unit, and then cut the length of the carbon fiber square tube according to the manufacturing requirements, so that the types of carbon fiber structure molds are few, the mold design is simple, and the mold opening cost is low. The structure has few types of parts, high standardization and is suitable for batch production. The flat plate type satellite structure based on the structure has small thickness, can save the internal space of the fairing, can improve the utilization rate of the internal space of the rocket fairing, so that more satellites can be launched by one rocket, the one rocket multiple satellite launch is facilitated, and the construction speed of large-scale satellite constellation is improved.

[0056] The above disclosed embodiments of the application are only used to help explain the application. The embodiments do not describe all the details, nor limit the application to the specific embodiments described. According to the content of the specification, many modifications and changes can be made. The specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the application, so that those skilled in the art can well understand and utilize the application.

Claims

1. A tiled frame structure for a flat panel satellite, characterized by: It includes beam units and splicing units, the beam units include X-axis beam units, Y-axis beam units and oblique beam units, the X-axis beam units and Y-axis beam units are arranged orthogonally, there is an included angle between the oblique beam units and the X-axis beam units, the X-axis beam units include 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 units include a first Y-axis beam (6), a second Y-axis beam (8) and a third Y-axis beam (11), the oblique beam units include a first oblique beam (5) and a second oblique beam (9), the splicing units include 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 on the upper part of the T-shaped structure are connected with the first X-axis beam (3), an interface on the lower part of the T-shaped structure is connected with the first Y-axis beam (6), the lower end of the first Y-axis beam (6) is connected with the second X-axis beam (7), the first X-axis beam (3) and the second X-axis beam (7) are connected through a plurality of first oblique beams (5), two of the 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 first oblique beams (5) are symmetrically arranged on the two 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 with 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 with 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 multiple, the two ends of the multiple third Y-axis beams (11) are connected with the third X-axis beam (10) and the fourth X-axis beam (12), an octagonal structure is formed 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), a plurality of cabin sections for installing satellite units are formed through the surrounding of the beam units and the splicing units, and the plurality of cabin sections are arranged in the same plane.

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

3. A tiled frame structure for a flat panel satellite according to claim 2, characterized in that: The variable angle joint (4) includes a first connecting end, a second connecting end and a rotating shaft, the first connecting end and the second connecting end are rotationally connected through the rotating shaft, and the first connecting end and the second connecting end are connected with corresponding beam units.

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

5. A tiled frame structure for a flat panel satellite according to claim 1, wherein: The beam units are rectangular tube structures, and the four surfaces of the rectangular tube are equal wall thickness or unequal wall thickness.

6. A tiled frame structure for a flat panel satellite according to claim 1, characterized in that: The beam units are made of carbon fiber material, and the splicing units are made of aluminum alloy material.

7. A tiled frame structure for a flat panel satellite according to claim 1, wherein: A connecting angle box (14) is arranged in the beam unit.

8. A tiled frame structure for a flat panel satellite according to claim 1, wherein: The connecting part of the beam unit is provided with a flat head rivet nut (15).

9. A tiled frame structure for a flat panel satellite according to claim 1, wherein: The spliced frame structure is provided with a hatch board (16) on the upper and lower surfaces.

10. A tiled 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 direction is not more than 600 mm, and the length of the spliced frame structure is not more than 4 m.

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