A central hub satellite structure and method of assembly thereof

Abstract

The application discloses a central hub type satellite structure and an assembling method thereof, and belongs to the technical field of satellite structures, in particular to a cable centralized management structure suitable for a hexahedral configuration satellite and an assembling method thereof. The application solves the problems of the prior art, such as a large cable allowance, a long time cost of cable binding, and a large deviation between an actual centroid of a satellite and a theoretical centroid. The structure comprises a bearing frame and at least one hub cabin. The central hub type satellite structure and the assembling method thereof are suitable for the cable centralized management of the hexahedral configuration satellite.

Description

Technical Field

[0001] This invention relates to the field of satellite structure technology, and in particular to a centralized cable management structure and its assembly method suitable for hexahedral satellites. Background Technology

[0002] Traditional simple hexahedral satellites have individual equipment directly installed on the inner wall of the satellite compartment, with cables laid flat along the surface of the compartment and tied and fixed on the compartment.

[0003] For non-mass-produced satellites, cable length is difficult to measure accurately using a 3D model, often resulting in a large cable slack. This requires changing the predetermined cable routing path or binding points to connect with the single-unit terminal, and the cable binding takes a long time.

[0004] In addition, the satellite's structural design cannot take into account the impact of the weight of the cables that are dispersed and fixed on each panel on the actual position of the satellite's center of mass, which often results in a large deviation between the actual center of mass and the theoretical center of mass. Summary of the Invention

[0005] This invention proposes a central hub-type satellite structure and its assembly method, which solves the problems of existing technologies, such as the large cable allowance requiring changes to the predetermined cable routing path or binding points for interlocking with the single-unit terminal, the long cable binding time, and the large deviation between the actual and theoretical centroids of the satellite.

[0006] The present invention provides a central hub-type satellite module structure, the structure comprising: a load-bearing frame and at least one hub module; The load-bearing frame includes a bottom plate, a top plate, four side plates, and corner boxes; The at least one cable hub is located inside the load-bearing frame. It is a columnar structure with open top and bottom, and its sides are provided with evenly arranged cable penetration holes and cable binding holes. The top plate and bottom plate are respectively provided with top plate cable outlet holes and bottom plate cable outlet holes corresponding to the upper and lower opening positions of the cable hub. The cable management compartment is fixedly connected to the bottom plate and the top plate via corner boxes; The four side plates are arranged from most to least in terms of the number of units per machine, and are designated as the first to fourth side plates. All of them are detachably connected to the base plate.

[0007] Furthermore, a preferred embodiment is provided in which the hub compartment is a cuboid structure with open top and bottom.

[0008] Furthermore, a preferred embodiment is provided in which the hub compartment is a cylindrical structure with open top and bottom.

[0009] Furthermore, in a preferred embodiment, the size of the cable binding hole is larger than the size of the cable penetration hole; The cable binding hole spacing is set at a given distance; Multiple cable penetration holes are arranged in a matrix between the cable binding holes.

[0010] Furthermore, a preferred embodiment is provided in which the position and number of the hub compartments are adjusted according to the layout of the satellite unit to ensure that the suspended cable length meets the process requirements.

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

[0012] Furthermore, a preferred embodiment is provided in which the diameter of the cable binding hole is determined according to the diameter of the cable harness inside the hub.

[0013] The present invention also proposes a central hub satellite structure, the structure comprising: a central hub satellite module structure as described in any of the preceding claims and a single unit device; The single-unit equipment includes external single-unit equipment and internal single-unit equipment; The external unit is connected to the cable management compartment via cable outlet holes on the bottom plate and the top plate. The individual units inside the cabin are distributed in descending order of quantity on the first to fourth side panels, and are connected to the cables in the hub cabin through the cable penetration holes.

[0014] This invention also proposes an assembly method for a central hub-and-spoke satellite structure, the method comprising the following steps: Step S1, pre-integration of the hub compartment: Cables are pre-laid inside the hub compartment, so that cables connecting individual units inside the compartment are led out through the cable penetration holes, and cables connecting individual units outside the compartment are led out through the upper and lower openings of the hub compartment, with the cables temporarily fixed at the openings. Step S2, base plate assembly: The cable hub is fixed to the base plate via a corner box, allowing the open cable to pass through the cable outlet hole on the base plate and then plug into the external unit on the outside of the base plate. Step S3, First side panel assembly: The individual units inside the cabin are installed on the first to fourth side panels in descending order of quantity; The cable leading out of the cable through the cable passage hole is inserted into the cabin unit on the first side plate which has the most cabin units installed, and the first side plate is assembled to the bottom plate. Step S4, Second side panel assembly: The cable leading out of the cable passage hole is inserted into the single unit inside the cabin on the second side plate, and the second side plate is assembled to the bottom plate; Step S5, assembly of the third side panel: The cable leading out of the cable passage hole is inserted into the single unit inside the cabin on the third side plate, and the third side plate is assembled to the bottom plate; Step S6, cable fixing: Secure the cables that have been plugged into the hub compartment by binding them through the cable binding holes; Step S7, Fourth side panel assembly: The cables leading out of the cable passage holes are plugged into the single unit inside the cabin on the fourth side plate, and the fourth side plate is assembled to the bottom plate to complete the assembly of the entire satellite.

[0015] Furthermore, in a preferred embodiment, during step S7, the fourth side panel is assembled as follows: The cable leading out of the cable passage hole and plugged into the single unit inside the compartment on the fourth side plate has a slack. The slack is tied to the root of the branch point with a binding wire inside the cable hub. The two ends of the binding wire protrude from the upper and lower openings of the cable hub; After installing the fourth side panel, use the binding wire to pull the excess part into the cable tray and secure it.

[0016] The present invention has the following beneficial effects: 1. The central hub type satellite module structure described in this invention uses a hub (or cable hub) which serves as both an integrated cable and a load-bearing structure for the entire satellite.

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

[0018] 3. The central hub-type satellite module structure of the present invention adopts a hub-type hub to lead out radially arranged neat wire bundles. The wire bundles lead out to the single-unit interface without excess wire length, which shortens the cable length between single units in the module, reduces power loss, reduces cable processing costs, and shortens the processing cycle.

[0019] 4. The central hub type satellite module structure described in this invention allows the hub (or cable compartment) to be used as a modular structure during satellite mass production. Cables can be pre-installed and fixed inside the cable compartment, and cables that need to be led out can be pre-exited through the corresponding through-holes, thus achieving pre-integration of the hub compartment body and reducing the final assembly time.

[0020] 5. The centrally mounted satellite module structure of the present invention uses cable slack for centralized fixing to avoid vibration of the entire satellite caused by untied cables.

[0021] The present invention discloses a central hub-type satellite structure and its assembly method, which is applicable to the centralized management of cables for hexahedral satellites. Attached Figure Description

[0022] To more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0023] Figure 1 A front view of a centrally located satellite structure according to one embodiment of the present invention; Figure 2 An exploded view of a centrally located satellite structure according to one embodiment of the present invention; Figure label: 1. Base plate; 2. Top plate; 3. Cable management compartment; 4. Corner box; 5. First side plate; 6. Second side plate; 7. Third side plate; 8. Fourth side plate; 9. Base plate cable outlet hole; 10. Top plate cable outlet hole; 11. Cable penetration hole; 12. Cable binding hole. Detailed Implementation

[0024] To make the technical solutions and advantages of the present invention clearer, the specific embodiments of the present invention will be described in further detail and completely below with reference to the accompanying drawings. The various embodiments described below are only some preferred embodiments of the present invention, and not all of them; the various embodiments described below are intended to explain the present invention and should not be construed as limiting the present invention; reasonable combinations of the technical features defined in the various embodiments of the present invention, as well as all other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort, are all within the scope of protection of the present invention.

[0025] Implementation method 1: A central hub type satellite module structure is provided, the structure includes: a load-bearing frame and at least one hub module 3; The load-bearing frame includes a base plate 1, a top plate 2, four side plates, and corner boxes 4; The at least one cable hub 3 is located inside the load-bearing frame. It is a columnar structure with open top and bottom, and its side is provided with evenly arranged cable penetration holes 11 and cable binding holes 12. The top plate 2 and the bottom plate 1 are respectively provided with a top plate cable outlet hole 10 and a bottom plate cable outlet hole 9 corresponding to the upper and lower opening positions of the cable collection compartment 3. The cable management compartment 3 is fixedly connected to the bottom plate 1 and the top plate 2 via the corner box 4; The four side plates are arranged from most to least in terms of the number of individual units, and are designated as the first to fourth side plates. All of them are detachably connected to the base plate 1.

[0026] In addition, in this embodiment, the hub compartment 3 is a cuboid structure with open top and bottom.

[0027] In addition, in this embodiment, the hub 3 is a cylindrical structure with open top and bottom.

[0028] In addition, in this embodiment, 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 set at given intervals; Multiple cable penetration holes 11 are arranged in a matrix between the cable binding holes 12.

[0029] In this embodiment, by reserving cable binding holes for cables inside the hub at given intervals, the cables inside the hub can be directly bound and fixed to the hub.

[0030] In addition, in this embodiment, the position and number of the hub compartments 3 are adjusted according to the layout of the satellite unit to ensure that the suspended cable length meets the process requirements.

[0031] In this embodiment, the location, size, and number of the hub compartments are determined based on the layout of individual satellite units and the overall configuration of the satellite. This avoids the overhead portion of the cables leading from the hub compartment to the individual unit interface on the side panel exceeding the cable laying process requirements, and avoids excessive design lengths of individual cables between adjacent units in order to fix them to the hub compartment.

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

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

[0034] In this embodiment, the cable management compartment is a metal enclosure within the satellite module that centrally manages the cables and serves both load-bearing and cable fixing functions.

[0035] In this embodiment, the cable penetration hole is an opening in the side wall of the hub compartment for the cable connecting the unit to pass through. The diameter of the hole is customized according to the connector size.

[0036] In this embodiment, the cable binding hole is an opening in the side wall of the cable hub for fixing the cable bundle, and the hole diameter is determined according to the diameter of the cable bundle.

[0037] In this embodiment, the corner box (or connecting corner box) is an L-shaped metal connector that mechanically fixes the hub compartment to the compartment panel.

[0038] In this embodiment, the cable allowance is: to accommodate the extra cable length reserved for assembly, which is eventually gathered in the cable management compartment.

[0039] In this embodiment, the satellite (cabinet) structure adopts a tree-like hierarchical design: Overall frame: It consists of a base plate, a top plate, and four side plates connected by corner boxes to form a hexahedral load-bearing structure.

[0040] Core components: Cable management compartment: A rectangular (or cylindrical) metal compartment with open top and bottom ends, and matrix-style cable penetration holes and spaced cable binding holes on the sides.

[0041] Corner box: an L-shaped metal connector that fixes the upper and lower ends of the cable management compartment to the bottom plate and top plate, respectively.

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

[0043] Implementation Method 2: A specific embodiment of a central hub-type satellite module structure is provided: A central hub-type satellite module structure includes a bottom plate 1, a top plate 2, a hub compartment 3, a corner box 4, and four side plates; the four side plates are divided into a first side plate 5, a second side plate 6, a third side plate 7, and a fourth side plate 8 according to the number of single units inside the module from most to least.

[0044] In this embodiment, there is one hub compartment 3, located in the center of the compartment. In the actual satellite structure design stage, the number of hub compartments 3 is increased or decreased, and their positions in the compartment are adjusted according to the characteristics of the satellite structure, the size and layout of individual units in the compartment.

[0045] In this embodiment, the bottom plate 1 has a bottom plate cable outlet hole 9, and the top plate 2 has a top plate cable outlet hole 10; the bottom plate cable outlet hole 9 and the top plate cable outlet hole 10 correspond to the openings of the cable collection compartment 3.

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

[0047] In this embodiment, the hub 3 has a cuboid structure, and the contact portion between the cuboid structure and the bottom plate 1 and the top plate 2 is open.

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

[0049] Implementation method 3: A central hub satellite structure is provided, the structure including: a central hub satellite module structure as described in any of the above implementation methods and a single unit device; The single-unit equipment includes external single-unit equipment and internal single-unit equipment; The external unit is connected to the cable management compartment 3 via cable outlet holes 9 on the bottom plate and 10 on the top plate. The individual units inside the cabin are distributed in descending order of quantity on the first to fourth side panels, and are connected to the cable hub 3 via cable penetration holes 11.

[0050] Implementation Method 4: A method for assembling a central hub-and-spoke satellite structure is provided, the method comprising the following steps: Step S1, pre-integration of the hub compartment: Cables are pre-laid in the hub compartment 3, so that the cables connecting the single units inside the compartment are led out from the cable passage hole 11, and the cables connecting the single units outside the compartment are passed out from the upper and lower openings of the hub compartment 3, and the cables are temporarily fixed at the openings. Step S2, base plate assembly: The cable hub 3 is fixed to the base plate 1 via the corner box 4, so that the open cable passes through the cable outlet hole 9 on the base plate and is plugged into the external unit on the outside of the base plate 1. Step S3, First side panel assembly: The individual units inside the cabin are installed on the first to fourth side panels in descending order of quantity; The cable leading out of the cable through the cable compartment hole 11 is inserted into the compartment unit on the first side plate 5, which has the most compartment units installed, and the first side plate 5 is assembled to the bottom plate 1. Step S4, Second side panel assembly: The cable leading out of the cable through the cable compartment hole 11 is inserted into the compartment unit on the second side plate 6, and the second side plate 6 is assembled to the bottom plate 1. Step S5, assembly of the third side panel: The cable leading out of the cable through the cable compartment hole 11 is inserted into the compartment unit on the third side plate 7, and the third side plate 7 is assembled to the bottom plate 1. Step S6, cable fixing: The cables that have been plugged into each other in the hub compartment 3 are bound and fixed through the cable binding hole 12; Step S7, Fourth side panel assembly: The cable leading out of the cable through the cabin hole 11 is inserted into the cabin unit on the fourth side plate 8, and the fourth side plate 8 is assembled to the bottom plate 1 to complete the assembly of the entire satellite.

[0051] In addition, in this embodiment, during step S7, the fourth side plate is assembled: The cable leading out from the cable passage hole 11 and plugged into the single unit inside the compartment on the fourth side plate 8 has a reserved slack. The slack part is tied to the root of the branch point with a binding wire in the cable collection compartment 3. The two ends of the binding wire pass through the upper and lower openings of the cable collection compartment 3; After installing the fourth side plate 8, the excess portion is pulled into the cable tray 3 and secured with binding wire.

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

[0053] In this embodiment, step S1, pre-integration of the hub compartment: Cables are pre-laid inside the hub compartment 3. According to the cable design drawings, the corresponding cables (cables connecting the single units inside the compartment) are led out from the corresponding cable passage holes 11. The single unit cables outside the compartment extend from the open ends of the hub compartment 3 and are temporarily fixed.

[0054] In this embodiment, step S2, base plate assembly: Fix the base plate 1, fix the cable hub 3 to the base plate 1 through the corner box 4, and the cable extending from one end (lower opening) of the cable hub 3 passes through the base plate cable outlet hole 9 on the base plate 1 and plugs into the external single unit of the base plate 1.

[0055] In this embodiment, step S3 involves assembling the first side plate: First, assemble the first side plate 5, which contains the most individual units in the cabin, with the bottom plate 1. Then, connect the cable leading out from the cable through hole 11 of the hub 3 to the (cabin-inside) individual unit end on the first side plate 5.

[0056] In this embodiment, step S4 involves assembling the second side plate: Lead out the cable and plug it into the single unit on the second side plate 6 and install the second side plate 6.

[0057] In this embodiment, step S5 involves assembling the third side plate: Lead out the cable and plug it into the single unit on the third side plate 7 and install the third side plate 7.

[0058] In this embodiment, step S6, cable fixing: The cables inside the cable hub are secured to the hub using the cable binding hole 12.

[0059] In this embodiment, step S7 involves assembling the fourth side plate: The cable is led out and plugged into the single unit on the fourth side plate 8; From the initial design stage, a certain margin was reserved for the length of the cable that would be plugged into the single unit on the fourth side plate 8, so as to facilitate the plugging and unplugging of the cable on the compartment plate into the single unit end; For the slack length of the cable that is plugged into the single unit on the fourth side plate 8, the cable is tied to the slack length at the root of the branch point of the cable in the hub compartment 3 beforehand with binding wire, and the binding wire is thrown out from the open ends of the hub compartment 3. After the fourth side plate 8 is installed, the cable slack is pulled into the hub compartment 3 by the thrown binding wire and tied and fixed in an appropriate position, so that the cable slack is concentrated in the hub compartment 3, avoiding the impact of the cable slack not being tied and fixed in the compartment on the vibration of the whole satellite.

[0060] in: At the root of the branch point of the cable: This refers to the key node where the cable bundle branches off from the main body of the hub compartment to form a single cable. It is located inside the hub compartment 3, near the inner entrance of the cable penetration hole 11. This point is the dividing point between the main cable bundle (in the bundled state) and the single cable (in the unbundled state) inside the compartment. The reserved extra cable length is coiled into a loop at this node and temporarily fixed with a binding wire.

[0061] Cable binding path: The cable binding extends from the upper opening (connecting to the top plate cable outlet 10) and the lower opening (connecting to the bottom plate cable outlet 9) of the cable hub; leading the cable binding from the opening ensures that the pulling direction is parallel to the axis of the cable hub, avoiding cable bending.

[0062] In this embodiment, the assembly method logical relationship is as follows: Time series relationship: Steps S1→S7 are executed strictly in sequence, and subsequent steps depend on the results of previous steps (e.g., steps S3-S5 need to be executed after the hub compartment is fixed in S2).

[0063] Functional collaboration relationships: Step S1 pre-integration and step S6 binding and fixing work together to achieve centralized cable management; Step S7, the excess material handling, works in conjunction with step S6, the binding wire operation, to prevent cable vibration.

[0064] Material transformation relationship: The cable slack reserved in step S7 is transformed into a fixed form inside the cable hub by physical pulling.

[0065] The above description of several specific embodiments further details the technical solution provided by the present invention in order to highlight the advantages and benefits of the technical solution provided by the present invention. However, the above-described specific embodiments are not intended to limit the present invention. Any reasonable modifications and improvements to the present invention, reasonable combinations of embodiments, and equivalent substitutions based on the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A method for assembling a centrally located satellite structure, characterized in that, The structure includes a load-bearing frame, at least one hub compartment (3), and a single unit; The cable hub (3) is located inside the load-bearing frame, and its side is provided with evenly arranged cable through holes (11). The top plate (2) and bottom plate (1) of the load-bearing frame are respectively provided with top plate cable outlet holes (10) and bottom plate cable outlet holes (9). The four side plates of the load-bearing frame are arranged in descending order of the number of single units as the first to fourth side plates (5,6,7,8). The single-unit equipment includes external single-unit equipment and internal single-unit equipment; The external unit is connected to the cable management compartment (3) via cable outlet holes (9) on the bottom plate and cable outlet holes (10) on the top plate; The individual units inside the cabin are distributed in order of decreasing quantity on the first to fourth side panels (5, 6, 7, 8), and are connected to the cable hub (3) via cable through the cable through-cabin hole (11); The method includes the following steps: Step S1, pre-integration of the hub compartment: Cables are pre-laid in the hub compartment (3), so that the cables connecting the single units inside the compartment are led out from the cable passage hole (11), and the cables connecting the single units outside the compartment are passed through the upper and lower openings of the hub compartment (3), and the cables at the openings are temporarily fixed. Step S2, base plate assembly: The cable hub (3) is fixed to the base plate (1) through the corner box (4), so that the lower open cable passes through the cable outlet hole (9) of the base plate and is plugged into the external unit on the outside of the base plate (1); Step S3, First side panel assembly: The individual units inside the cabin are installed on the first to fourth side panels (5, 6, 7, 8) in descending order of quantity. The cable leading out from the cable through the cable compartment hole (11) is inserted into the cabin unit on the first side plate (5) which has the most cabin units installed, and the first side plate (5) is assembled to the bottom plate (1). Step S4, Second side panel assembly: The cable leading out from the cable through the hatch (11) is inserted into the single unit inside the hatch on the second side plate (6), and the second side plate (6) is assembled to the bottom plate (1). Step S5, assembly of the third side panel: The cable leading out from the cable through the hatch (11) is inserted into the single unit inside the hatch on the third side plate (7), and the third side plate (7) is assembled to the bottom plate (1). Step S6, cable fixing: The cables that have been plugged into the hub (3) are secured by binding through the cable binding hole (12); Step S7, Fourth side panel assembly: The cable leading out from the cable through the cabin hole (11) is inserted into the cabin unit on the fourth side plate (8), and the fourth side plate (8) is assembled to the bottom plate (1) to complete the assembly of the entire satellite.

2. The assembly method according to claim 1, characterized in that, The load-bearing frame also includes corner boxes (4). The at least one hub compartment (3) is a columnar structure with open top and bottom, and its side is also provided with evenly arranged cable binding holes (12). The top plate (2) and the bottom plate (1) are respectively provided with a top plate cable outlet hole (10) and a bottom plate cable outlet hole (9) corresponding to the upper and lower opening positions of the cable collection compartment (3). The hub compartment (3) is fixedly connected to the bottom plate (1) and the top plate (2) via corner boxes (4); All four side plates are detachably connected to the base plate (1).

3. The assembly method according to claim 1, characterized in that, The hub compartment (3) is a rectangular structure with open top and bottom.

4. The assembly method according to claim 1, characterized in that, The hub compartment (3) is a cylindrical structure with open top and bottom.

5. The assembly method according to claim 1, characterized in that, The size of the cable binding hole (12) is larger than the size of the cable through hole (11); The cable binding holes (12) are set at given intervals; Multiple cable penetration holes (11) are arranged in a matrix between the cable binding holes (12).

6. The assembly method according to claim 1, characterized in that, The position and number of the hub compartments (3) are adjusted according to the layout of the satellite unit to ensure that the suspended cable length meets the process requirements.

7. The assembly method according to claim 1, characterized in that, The diameter of the cable through hole (11) is determined according to the cable end connector model.

8. The assembly method 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 inside the cable tray (3).

9. The assembly method according to claim 1, characterized in that, In step S7, the fourth side plate is being assembled: The cable leading out from the cable through the cable compartment hole (11) and plugged into the single unit inside the compartment on the fourth side plate (8) has a reserved slack. The slack part is tied to the root of the branch point with a binding wire in the cable collection compartment (3). The two ends of the binding line pass through the upper and lower openings of the cable collection compartment (3); After installing the fourth side plate (8), the excess portion is pulled into the cable tray (3) and secured with binding wire.

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