Center line concentration type satellite structure and assembling method thereof

Abstract

The invention discloses a center line concentration type satellite structure and an assembling method thereof, belongs to the technical field of satellite structures, and particularly relates to a cable centralized management structure suitable for a hexahedral configuration satellite and an assembling method thereof. The problems that in the prior art, due to the fact that the allowance of cables is large, the cables can be inserted into the stand-alone end only by changing a preset wiring path or binding point, and cable binding takes a long time are solved, and the problem that the deviation between the actual center of mass of the satellite and the theoretical center of mass is large often is solved. The structure comprises a force bearing frame and at least one line concentration cabin. The center line concentration type satellite structure and the assembling method thereof are suitable for centralized management of cables of a hexahedral configuration satellite.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite structures, and in particular to a cable centralized management structure suitable for a hexahedral configuration satellite and an assembly method thereof. Background Art

[0002] In traditional simple hexahedral structure satellites, each single device is directly installed on the inner wall of the satellite cabin, and the cables are laid flat along the surface of the cabin and tied and fixed on the cabin.

[0003] For non-mass-produced satellites, the cable length is difficult to accurately measure using a three-dimensional model, which often results in a large cable margin. It is necessary to change the predetermined routing path or binding point in order to plug it into the single-machine end, and cable binding takes a long time.

[0004] In addition, the satellite structure design fails to consider the impact of the weight of the cables distributed and fixed on each cabin board on the actual center of mass position of the satellite, resulting in the actual center of mass of the satellite often deviating greatly from the theoretical center of mass. Summary of the Invention

[0005] The present invention proposes a centrally located satellite structure and an assembly method thereof, which solves the problems in the prior art of large cable margins requiring changes to predetermined routing paths or binding points in order to plug into a single-machine end, a long time spent on cable binding, and a problem that the actual center of mass of the satellite often deviates significantly from the theoretical center of mass.

[0006] The central line collection type satellite cabin plate structure of the present invention comprises: a load-bearing frame and at least one line collection cabin; The load-bearing frame includes a bottom plate, a top plate, four side plates and a corner box; The at least one cable collection cabin is provided inside the load-bearing frame and is a columnar structure with upper and lower openings, and its side is provided with evenly arranged cable passage holes and cable tying holes; The top plate and bottom plate are respectively provided with top plate wire outlet holes and bottom plate wire outlet holes corresponding to the upper and lower opening positions of the wiring cabin; The wiring cabin is fixedly connected to the bottom plate and the top plate through a corner box; The four side panels are arranged from most to least according to the number of the single machines as the first to the fourth side panels, and are all detachably connected to the bottom panel.

[0007] Furthermore, a preferred embodiment is provided, wherein the wiring collection cabin is a rectangular parallelepiped structure with upper and lower openings.

[0008] Furthermore, a preferred embodiment is provided, wherein the wiring collection cabin is a cylindrical structure open at the top and bottom.

[0009] Furthermore, a preferred embodiment is provided, wherein the size of the cable binding hole is larger than the size of the cable entry hole; The cable binding holes are arranged at given intervals; A plurality of cable passage holes arranged in a matrix are provided between the cable binding holes.

[0010] Furthermore, a preferred embodiment is provided, in which the position and number of the cable collection cabins are adjusted according to the layout of the satellite units to ensure that the length of the cables hanging in the air meets the process requirements.

[0011] Furthermore, a preferred embodiment is provided, wherein the diameter of the cable penetration hole is determined according to the model of the cable end connector.

[0012] Furthermore, a preferred embodiment is provided, wherein the diameter of the cable binding hole is determined according to the diameter of the wire harness in the wiring compartment.

[0013] The present invention also proposes a central hub type satellite structure, which comprises: a central hub type satellite cabin plate structure and a single device as described in any one of the above items; The stand-alone equipment includes an outboard stand-alone device and an inboard stand-alone device; The outboard single unit is connected to the cable collection cabin through the bottom plate outlet hole and the top plate outlet hole; The units in the cabin are distributed on the first to fourth side panels in descending order of number, and are connected to the cables in the wiring cabin through the cable holes.

[0014] The present invention also proposes a method for assembling a central hub satellite structure, the method comprising the following steps: Step S1: pre-integration of the wiring module: Pre-lay cables in the cable collection cabin, so that cables connecting single units inside the cabin are led out from the cable holes, and cables connecting single units outside the cabin are passed out from the upper and lower openings of the cable collection cabin. The cables are temporarily fixed at the openings. Step S2, bottom plate assembly: Fix the cable collection cabin to the bottom plate through the corner box, pass the lower exposed cable through the bottom plate outlet hole, and then plug it into the single unit outside the cabin on the outside of the bottom plate; Step S3, first side panel assembly: The single units in the cabin are installed on the first to fourth side panels in descending order of number; Connect the cables led out from the cable holes to the cabin units on the first side panel where the most cabin units are installed, and assemble the first side panel to the bottom panel; Step S4, assembling the second side panel: Connect the cables led out from the cable hole to the single unit in the cabin on the second side panel, and assemble the second side panel to the bottom panel; Step S5, assembling the third side panel: Connect the cables led out from the cable hole to the single unit in the cabin on the third side panel, and assemble the third side panel to the bottom panel; Step S6: Cable fixing: Use the cable binding holes to secure the cables that have been plugged in the wiring compartment. Step S7, assembling the fourth side panel: Connect the cables led out from the cable hole to the single unit in the cabin on the fourth side panel, assemble the fourth side panel to the bottom panel to complete the assembly of the entire satellite.

[0015] Furthermore, a preferred embodiment is provided, in step S7, during the assembly of the fourth side panel: Reserve a margin for the cable leading out of the cable hole to be plugged into a single unit in the cabin on the fourth side panel. Tie the remaining portion to the root of the branch point in the cable collection cabin with a lashing line. The two ends of the lashing wire pass through the upper and lower openings of the cable collection compartment; After installing the fourth side panel, use the binding wire to pull the remaining part into the cable collection compartment and tie it in place.

[0016] The present invention has the following beneficial effects: 1. The central cable-harvesting satellite cabin panel structure described in the present invention uses a cable-harvesting cabin (or cable-harvesting cabin) which not only integrates cables but also serves as the load-bearing structure of the entire satellite.

[0017] 2. The central cable-harvesting satellite cabin structure described in the present invention uses a cable-harvesting cabin as the largest load-bearing structure for the entire satellite's cables. The cable weight is distributed centrally, which facilitates the estimation of the total cable weight, reduces the impact of the cables on the center of mass position of the entire satellite, and reduces the deviation between the actual center of mass and the theoretical center of mass.

[0018] 3. The central hub satellite cabin panel structure described in the present invention adopts a hub cabin to lead out a radial regular wire harness, and there is no extra wire length when leading out the wire harness to the single-machine interface, thereby shortening the cable length between single machines in the cabin, reducing power loss, reducing cable processing costs, and shortening the processing cycle.

[0019] 4. The central cable-harvesting satellite cabin panel structure described in the present invention can be used as a modular structure during satellite mass production. The cables can be routed and fixed in the cabin in advance, and the cables that need to be led out can be passed through the corresponding cabin holes in advance, thereby realizing pre-integration of the cabin body and reducing the assembly time.

[0020] 5. The centrally-connected satellite cabin structure described in the present invention is centrally fixed by cable surplus, thus avoiding vibration of the entire satellite caused by untied cables.

[0021] The central cable-collecting satellite structure and the assembly method thereof described in the present invention are suitable for centralized cable management of hexahedral satellites. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0023] Figure 1 A front view of a central hub satellite structure in one embodiment of the present invention; Figure 2 An exploded view of a central hub satellite structure in one embodiment of the present invention; Reference numerals: 1. Bottom plate; 2. Top plate; 3. Cable compartment; 4. Corner box; 5. First side plate; 6. Second side plate; 7. Third side plate; 8. Fourth side plate; 9. Bottom plate cable outlet hole; 10. Top plate cable outlet hole; 11. Cable entry hole; 12. Cable binding hole. DETAILED DESCRIPTION

[0024] In order to make the technical solutions and advantages of the present invention more clearly described, the specific embodiments of the present invention will be further described in detail and completely in conjunction with the accompanying drawings. The various embodiments described below are only part of the preferred embodiments of the present invention, rather than all implementation plans; the various embodiments described below are intended to explain the present invention and cannot be understood as limiting the present invention; the reasonable combination of the technical features defined in the various embodiments of the present invention, as well as all other implementation plans obtained by ordinary technicians in this field based on the embodiments of the present invention without making creative work, all fall within the scope of protection of the present invention.

[0025] Embodiment 1: Provided is a centrally-connected satellite cabin plate structure, comprising: a load-bearing frame and at least one cable-connected cabin 3; The load-bearing frame includes a bottom plate 1, a top plate 2, four side plates and a corner box 4; The at least one cable collection cabin 3 is provided inside the load-bearing frame and is a columnar structure with upper and lower openings, and its side is provided with evenly arranged cable passage holes 11 and cable binding holes 12; The top plate 2 and the bottom plate 1 are respectively provided with a top plate outlet hole 10 and a bottom plate outlet hole 9 corresponding to the upper and lower opening positions of the wiring compartment 3; The wiring cabin 3 is fixedly connected to the bottom plate 1 and the top plate 2 through the corner box 4; The four side panels are arranged from most to least according to the number of the units, namely the first to the fourth side panels, and are all detachably connected to the bottom panel 1 .

[0026] In addition, in this embodiment, the wiring collection cabin 3 is a rectangular parallelepiped structure with upper and lower openings.

[0027] In addition, in this embodiment, the wiring collection cabin 3 is a cylindrical structure with upper and lower openings.

[0028] In addition, in this embodiment, the size of the cable binding hole 12 is larger than the size of the cable passage hole 11; The cable binding holes 12 are arranged at given intervals; A plurality of cable passage holes 11 arranged in a matrix are provided between the cable binding holes 12 .

[0029] In this embodiment, cable binding holes for the cables in the wiring collection cabin are reserved at given intervals, so that the cables in the wiring collection cabin can be directly bound and fixed on the wiring collection cabin.

[0030] In addition, in this embodiment, the position and number of the cable collection cabins 3 are adjusted according to the layout of the satellite units to ensure that the length of the cables suspended in the air meets the process requirements.

[0031] In this embodiment, the location, size and number of the wiring pods are determined based on the satellite unit layout and the overall configuration of the satellite, to avoid the suspended portion of the cable leading out from the wiring pod to the side panel unit interface exceeding the cable laying process requirements, and to avoid the design length of the single cable between adjacent units being too long due to the need to fix it on the wiring pod.

[0032] In addition, in this embodiment, the diameter of the cable passage hole 11 is determined according to the type of the cable end connector.

[0033] In addition, in this embodiment, the diameter of the cable binding hole 12 is determined according to the diameter of the wire harness in the wiring compartment 3 .

[0034] In this embodiment, the cable collection cabin is a metal cabin in the satellite cabin that centrally manages cables and has both load-bearing and cable fixing functions.

[0035] In this embodiment, the cable through-hole is a hole in the side wall of the wiring compartment, which is used to pass through the cables connected to the single machine, and the hole diameter is customized according to the size of the connector.

[0036] In this embodiment, the cable binding hole is a hole opened on the side wall of the wiring compartment, used to fix the cable bundle, and the hole diameter is determined according to the diameter of the wire bundle.

[0037] In this embodiment, the corner box (or connecting corner box) is an L-shaped metal connector that achieves mechanical fixation between the wiring cabin and the cabin board.

[0038] In this embodiment, the cable margin is the extra cable length reserved to accommodate assembly, which is ultimately gathered in the cable collection compartment.

[0039] In this implementation, the satellite (cabin) structure adopts a tree-like hierarchical design: Overall frame: A hexahedral load-bearing structure consisting of a bottom plate, a top plate, and four side plates connected by corner boxes.

[0040] Core components: Cable collection cabin: a rectangular (or cylindrical) metal cabin with open upper and lower ends, and matrix cable entry holes and spaced cable tying holes on the side.

[0041] Corner box: An L-shaped metal connector that secures the upper and lower ends of the cable bay to the bottom and top plates, respectively.

[0042] Opening design: A cable outlet hole is provided in the center of the bottom plate / top plate, aligned with the opening of the cable collection compartment 3; The diameter of the cable entry hole is adapted to the connector size, and the diameter of the cable binding hole is adapted to the wire harness diameter.

[0043] Implementation 2: Provide a specific embodiment of a central hub type satellite cabin panel structure: A central hub type satellite cabin panel structure comprises a bottom panel 1, a top panel 2, a hub cabin 3, a corner box 4 and four side panels; the four side panels are divided into a first side panel 5, a second side panel 6, a third side panel 7 and a fourth side panel 8 in descending order according to the number of single devices in the cabin.

[0044] In this embodiment, there is one wiring pod 3 located in the center of the cabin. During the actual satellite structure design phase, the number of wiring pods 3 is increased or decreased, and their positions are arranged in the cabin according to the satellite structure characteristics, the size of the individual units in the cabin, and the layout of the individual units.

[0045] In this embodiment, a bottom plate wire outlet hole 9 is opened on the bottom plate 1 , and a top plate wire outlet hole 10 is opened on the top plate 2 ; the bottom plate wire outlet hole 9 and the top plate wire outlet hole 10 correspond to the opening of the wire collection cabin 3 .

[0046] In this embodiment, the cable entry holes 11 and the cable binding holes 12 are evenly distributed on the wiring collection cabin 3; the size of the cable entry holes 11 is determined according to the cable end connector model, and the size of the cable binding holes 12 is determined according to the cable bundle diameter (or wire bundle diameter) in the wiring collection cabin 3.

[0047] In this embodiment, the wiring collection cabin 3 is a rectangular parallelepiped structure, and the contact portion between the rectangular parallelepiped structure and the bottom plate 1 and the top plate 2 is open.

[0048] In this embodiment, the wiring compartment 3 is connected and fixed to the bottom plate 1 and the top plate 2 via a corner box 4 .

[0049] Implementation 3: A central hub type satellite structure is provided, comprising: a central hub type satellite cabin structure and a single device as described in any one of the above implementations; The stand-alone equipment includes an outboard stand-alone device and an inboard stand-alone device; The outboard single unit is connected to the cable collection cabin 3 via the bottom plate outlet hole 9 and the top plate outlet hole 10; The units in the cabin are distributed on the first to fourth side panels in descending order of number, and are connected to the wiring cabin 3 via cable holes 11 .

[0050] Embodiment 4: A method for assembling a central hub satellite structure is provided, the method comprising the following steps: Step S1: pre-integration of the wiring module: Pre-lay cables in the wiring cabin 3 so that the cables connecting the single units in the cabin are led out from the cable through-hole 11, and the cables connecting the single units outside the cabin are passed out from the upper and lower openings of the wiring cabin 3. The cables are temporarily fixed at the openings. Step S2, bottom plate assembly: Fix the cable collection cabin 3 to the bottom plate 1 through the corner box 4, and pass the lower open cable through the bottom plate outlet hole 9 and then plug it into the single unit outside the cabin on the outside of the bottom plate 1; Step S3, assembling the first side panel: The single units in the cabin are installed on the first to fourth side panels in descending order of number; Insert the cables led out from the cable hole 11 into the cabin units on the first side panel 5 where the most cabin units are installed, and assemble the first side panel 5 to the bottom panel 1; Step S4, assembling the second side panel: Insert the cables led out from the cable hole 11 into the single unit in the cabin on the second side panel 6, and assemble the second side panel 6 to the bottom panel 1; Step S5, assembling the third side panel: Insert the cables led out from the cable hole 11 into the single unit in the cabin on the third side panel 7, and assemble the third side panel 7 to the bottom panel 1; Step S6: Cable fixing: Tie and secure the cables that have been plugged into the wiring compartment 3 through the cable tying holes 12; Step S7, assembling the fourth side panel: Insert the cables led out from the cable hole 11 into the single unit in the cabin on the fourth side panel 8, assemble the fourth side panel 8 to the bottom panel 1, and complete the assembly of the entire satellite.

[0051] In addition, in this embodiment, in step S7, assembling the fourth side panel: The cable leading out from the cable hole 11 and plugging into the single unit in the cabin on the fourth side plate 8 is reserved for a margin, and the remaining part is tied to the root of the branch point in the cable collection cabin 3 with a tying line; The two ends of the lashing wire pass through the upper and lower openings of the wiring compartment 3; After the fourth side panel 8 is installed, the remaining portion is pulled into the cable collection compartment 3 and tied and fixed using the tying line.

[0052] In this embodiment, the assembly method is used for whole-satellite assembly.

[0053] In this embodiment, step S1, pre-integration of the wiring module: The cables in the wiring cabin 3 are pre-laid, and the corresponding cables (cables connecting the single machines in the cabin) are led out from the corresponding cable holes 11 according to the cable design drawings; the cables of the single machines outside the cabin extend from the open ends of the wiring cabin 3, and the cables extending out of the wiring cabin 3 are temporarily fixed.

[0054] In this embodiment, step S2, bottom plate assembly: Fix the base plate 1, fix the cable collection cabin 3 on the base plate 1 through the corner box 4, and the cables extending from one end (lower open) of the cable collection cabin 3 pass through the base plate outlet hole 9 on the base plate 1 and plug into the single unit outside the cabin of the base plate 1.

[0055] In this embodiment, step S3, first side panel assembly: Assemble the first side panel 5 with the most units in the cabin with the bottom panel 1 first, and plug the cables led out from the cable holes 11 of the wiring cabin 3 into the (inside) unit ends on the first side panel 5 .

[0056] In this embodiment, step S4, second side panel assembly: The lead-out cable is plugged into the single unit on the second side panel 6 and the second side panel 6 is installed.

[0057] In this embodiment, step S5, the third side panel is assembled: The lead-out cable is plugged into the single unit on the third side panel 7 and the third side panel 7 is installed.

[0058] In this embodiment, in step S6, the cable is fixed: The cables in the cable collection compartment are tied and fixed together with the cable collection compartment through the cable binding holes 12 .

[0059] In this embodiment, step S7, the fourth side panel is assembled: Lead out the cable and plug it into the single device on the fourth side panel 8; From the initial design stage, a certain margin will be left in the length of the cable for plugging into the single machine on the fourth side panel 8 to facilitate the plugging of the cable on the panel with the single machine end; As for the length surplus of the cable plugged into the single machine on the fourth side panel 8, this part of the cable is tied to the root surplus of the cable branch point in the cable collection cabin 3 with a binding line in advance, and the binding line is thrown out from the two ends of the cable collection cabin 3. After the fourth side panel 8 is installed, the cable surplus is pulled into the cable collection cabin 3 through the thrown-out binding line, and tied and fixed at the appropriate position, so that the cable surplus is concentrated in the cable collection cabin 3, avoiding the influence of the cable surplus not tied and fixed in the cabin on the vibration of the whole satellite.

[0060] in: The root margin of the lead-out cable branching point refers to the key node position where the wiring harness branches out from the main body of the wiring compartment into a single cable, located inside the wiring compartment 3, close to the inner entrance of the cable hole 11; this point is the dividing point between the main wiring harness in the compartment (tied state) and the single lead-out cable (untied state); the reserved extra cable length is coiled into a ring at this node and temporarily fixed with a binding line.

[0061] Tie wire pulling path: The tie wire passes through the upper opening of the cable collection compartment (connected to the cable outlet hole 10 on the top plate) and the lower opening (connected to the cable outlet hole 9 on the bottom plate); leading the tie wire out from the opening can ensure that the pulling direction is parallel to the axis of the cable collection compartment, avoiding cable bending.

[0062] In this embodiment, the logical relationship of the assembly method is: Time series relationship: Steps S1→S7 are strictly executed in sequence, and subsequent steps depend on the results of previous steps (for example, steps S3-S5 must be executed after the wiring cabin is fixed in S2).

[0063] Functional synergy: The pre-integration in step S1 and the binding and fixing in step S6 work together to realize centralized cable management; The margin processing in step S7 prevents cable vibration by tying the wires in conjunction with the tying step in step S6.

[0064] Material conversion relationship: In step S7, the reserved cable surplus is converted into a fixed form in the cable collection cabin through physical pulling.

[0065] The above further describes the technical solution provided by the present invention in detail through several specific embodiments in order to highlight the advantages and benefits of the technical solution provided by the present invention. However, the several specific embodiments described above are not intended to limit the present invention. Any reasonable changes and improvements to the present invention, reasonable combinations of implementation methods and equivalent replacements based on the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A centrally located satellite cabin panel structure, characterized in that: The structure comprises: a load-bearing frame and at least one wiring compartment (3); The load-bearing frame comprises a bottom plate (1), a top plate (2), four side plates and a corner box (4); The at least one cable collection cabin (3) is arranged inside the load-bearing frame and is a columnar structure with upper and lower openings, and its side surfaces are provided with evenly arranged cable passage holes (11) and cable binding holes (12); The top plate (2) and the bottom plate (1) are respectively provided with a top plate wire outlet hole (10) and a bottom plate wire outlet hole (9) corresponding to the upper and lower opening positions of the wiring compartment (3); The wiring cabin (3) is fixedly connected to the bottom plate (1) and the top plate (2) via a corner box (4); The four side panels are arranged from most to least in order of the number of units as first to fourth side panels (5, 6, 7, 8), and are all detachably connected to the bottom panel (1).

2. A central hub type satellite cabin panel structure according to claim 1, characterized in that: The wiring collection cabin (3) is a rectangular parallelepiped structure with upper and lower openings.

3. The central hub type satellite cabin panel structure according to claim 1, characterized in that: The wiring collection cabin (3) is a cylindrical structure with upper and lower openings.

4. The central hub type satellite cabin panel structure according to claim 1, characterized in that: The size of the cable binding hole (12) is larger than the size of the cable penetration hole (11); The cable binding holes (12) are arranged at given intervals; A plurality of cable penetration holes (11) arranged in a matrix are provided between the cable binding holes (12).

5. The central hub type satellite cabin panel structure according to claim 1, characterized in that: The position and number of the cable collection cabins (3) are adjusted according to the layout of the satellite units to ensure that the cable hanging length meets the process requirements.

6. The central hub type satellite cabin panel structure according to claim 1, characterized in that: The diameter of the cable penetration hole (11) is determined according to the type of the cable end connector.

7. The central hub type satellite cabin panel structure according to claim 1, characterized in that: The diameter of the cable binding hole (12) is determined according to the diameter of the wire harness in the wiring compartment (3).

8. A central hub satellite structure, characterized in that: The structure comprises: a centrally-connected satellite cabin panel structure and a stand-alone device according to any one of claims 1 to 7; The stand-alone equipment includes an outboard stand-alone device and an inboard stand-alone device; The outboard single unit is connected to the cable of the wiring cabin (3) via the bottom plate outlet hole (9) and the top plate outlet hole (10); The single units in the cabin are distributed on the first to fourth side panels (5, 6, 7, 8) in descending order of number, and are connected to the wiring cabin (3) via cable holes (11).

9. A method for assembling a central hub satellite structure, characterized in that: The method comprises the following steps: Step S1: pre-integration of the wiring module: Cables are pre-laid in the wiring cabin (3), so that the cables connecting the single units in the cabin are led out from the cable through-hole (11), and the cables connecting the single units outside the cabin are passed out from the upper and lower openings of the wiring cabin (3), and the cables are temporarily fixed at the openings; Step S2, bottom plate assembly: The cable collection cabin (3) is fixed to the bottom plate (1) through the corner box (4), and the lower open cable is passed through the bottom plate outlet hole (9) and then plugged into the outer cabin single unit outside the bottom plate (1); Step S3, assembling the first side panel: The single units in the cabin are installed on the first to fourth side panels (5, 6, 7, 8) in descending order of number; Insert the cables led out from the cable hole (11) into the cabin units on the first side panel (5) where the most cabin units are installed, and assemble the first side panel (5) to the bottom panel (1); Step S4, assembling the second side panel: Insert the cable drawn out from the cable hole (11) into the cabin unit on the second side panel (6), and assemble the second side panel (6) to the bottom panel (1); Step S5, assembling the third side panel: Insert the cable drawn out from the cable hole (11) into the single unit in the cabin on the third side panel (7), and assemble the third side panel (7) to the bottom panel (1); Step S6: Cable fixing: The cables inserted into the wiring compartment (3) are tied and fixed through the cable tying holes (12); Step S7, assembling the fourth side panel: The cable led out from the cable hole (11) is plugged into the single unit in the cabin on the fourth side panel (8), and the fourth side panel (8) is assembled to the bottom panel (1) to complete the assembly of the entire satellite.

10. The method for assembling a central hub satellite structure according to claim 9, characterized in that: In step S7, the fourth side panel is assembled: A reserve of cables for plugging into a single unit in the cabin on the fourth side panel (8) is provided, and the remaining portion is tied to the root of the branch point in the cable collection cabin (3) with a tying wire; The two ends of the lashing line pass through the upper and lower openings of the wiring compartment (3); After the fourth side panel (8) is installed, the remaining portion is pulled into the wiring compartment (3) and tied and fixed using the tying wire.

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