Modular satellite structure based on open type grid framework and final assembly method thereof

Abstract

The invention provides a modular satellite structure based on an open type grid framework and a final assembly method thereof, and belongs to the technical field of satellite structures. The problems that according to an existing method, the defects of blind operation and adhesive fixation are not fundamentally eliminated, the cable laying efficiency is low, and the weight of an outer plate is too large are solved. The thermal control protection structure comprises an open type main bearing grid framework and a plurality of thermal control protection outer plates, the open type main force bearing grid framework is a hexahedral cage-shaped framework formed by connecting six plate-shaped grid frameworks in a butt joint mode. The thermal control protection outer plates are arranged on at least one outer side face of the open type main force bearing grid framework. The plate-shaped grid frame is used for installing one side plane of the thermal control protection outer plate, and a force bearing structure of the plate-shaped grid frame is recessed inwards. The method is mainly used in the aerospace field.

Description

Technical Field

[0001] This invention belongs to the field of satellite structure technology, and in particular relates to a modular satellite structure based on an open grid skeleton and its assembly method. Background Technology

[0002] With the development of aerospace technology, small and medium-sized satellites, especially standard hexahedral satellites, are increasingly widely used in remote sensing, communication, scientific research, and other fields. Their development model is also evolving towards mass production, high reliability, and low cost. However, the traditional satellite structure and assembly process that support this evolutionary trend are gradually becoming bottlenecks restricting development.

[0003] Currently, small and medium-sized hexahedral satellites generally adopt a structure based on honeycomb sandwich panels. The satellite body is assembled and fastened from six pre-manufactured aluminum honeycomb or composite honeycomb panels during the final assembly stage, forming a closed box. Metal embedded parts for installing various individual pieces of equipment are pre-installed inside these structural panels. This integrated skin-frame design allows the structural panels to simultaneously bear multiple functions, including main load-bearing, equipment installation, thermal control radiation surface, and micrometeoroid protection. During final assembly, operators must complete the installation of equipment, the laying and connection of cables within a closed or semi-closed cabin space, and finally close the various panels.

[0004] The aforementioned traditional technical solutions have revealed many inherent defects in practical engineering applications, which can be mainly summarized in the following three aspects: First, the final assembly process presents significant risks of blind operation, severely impacting the reliability of the final product. During the final assembly, adjacent honeycomb panels completely enclose the internal space, completely obstructing the operator's view. At the moment of assembly, it's impossible to visually assess whether protruding connectors and cable bundles within the module interfere with or are compressed by adjacent structural panels. Such interference and cable compression issues are often only discovered after assembly or even during subsequent testing. Rework at this point requires disassembling the already secured modules, an extremely difficult operation that not only delays progress but also risks secondary damage to already installed precision equipment, becoming one of the main sources of risk affecting the satellite's on-orbit reliability.

[0005] Secondly, the cable network laying process is cumbersome, inefficient, and carries long-term reliability risks. To avoid the risk of wire compression caused by blind operations, the design of the cable network is forced to be conservative, requiring the pre-planning of complex three-dimensional cable routing paths for wall and panel installations, which inevitably increases the length and weight of the cables. In terms of laying process, adhesive cable clips are commonly used to fix the cables to the surface of the structural panel. This process has multiple drawbacks: after each batch of cable clips is pasted, it is necessary to wait for the adhesive to fully cure, which usually takes more than 24 hours. During this period, subsequent binding and sorting work cannot be carried out, which seriously slows down the pace of mass production; the pasting process itself has stringent cleanliness requirements, making it difficult to ensure process consistency; more importantly, after the satellite experiences harsh environments such as launch vibration, on-orbit high and low temperature cycles, vacuum, and particle radiation, the adhesive is at risk of aging, performance degradation, and even debonding, which may lead to cable fixation failure and catastrophic consequences such as short circuits.

[0006] Furthermore, the integrated structural-thermal design creates a dilemma between weight optimization and performance improvement. Traditional honeycomb panels, as the main load-bearing structure, require numerous embedded metal components to house equipment, which inherently creates thermal short circuits and increases weight. Simultaneously, to meet thermal control requirements, thermal control coatings must be applied or sprayed onto the surface, and heat pipes and other devices may be embedded internally. This multi-functional coupled design forces the structural panel to make difficult compromises between load-bearing stiffness, equipment installation strength, thermal control performance, and weight. For example, even with optimization, a 1m x 1m satellite side panel often has a thickness exceeding 15mm and a single panel weight of 10-20kg, making it difficult to achieve the ultimate lightweight goal. Thermal control design thus becomes a passive adaptation to structural design rather than an active optimization.

[0007] In recent years, to improve assembly efficiency, some modular satellite design concepts have emerged, such as dividing the satellite into several functional unit modules, assembling them independently first, and then connecting them. However, such solutions mostly focus on the standardization and rapid disassembly / reassembly of the overall mechanical interfaces, and the internal structure of each individual module is usually still a closed or semi-closed box structure. Equipment installation and cable laying are still completed in confined spaces, and the drawbacks of blind operation and adhesive fixing have not been fundamentally eliminated. Core technological challenges such as low cable laying efficiency and excessive weight of the outer panel still exist. Summary of the Invention

[0008] In view of this, the present invention aims to propose a modular satellite structure based on an open grid skeleton and its assembly method, so as to solve the problems of existing methods not fundamentally eliminating the drawbacks of blind operation and adhesive fixing, low cable laying efficiency and excessive weight of the outer plate.

[0009] To achieve the above objectives, the present invention adopts the following technical solution: a modular satellite structure based on an open grid framework, the satellite structure comprising: An open-type main load-bearing grid skeleton and multiple thermal control and protective outer plates; the open-type main load-bearing grid skeleton is composed of six plate-shaped grid frames connected to each other to form a hexahedral cage-like skeleton; the thermal control and protective outer plates are respectively disposed on at least one outer side of the open-type main load-bearing grid skeleton; The plate-shaped mesh frame is used to install one side plane of the thermal control and protection outer plate, and its load-bearing structure is recessed inward.

[0010] Furthermore, a preferred embodiment is proposed in which the satellite structure further includes a trihedral corner box, and the six plate-shaped grid frames are fixedly connected at the corners where their edges meet through the trihedral corner box.

[0011] Furthermore, a preferred embodiment is proposed, wherein the trihedral box has three mutually perpendicular connecting surfaces, and the three connecting surfaces are respectively fixedly connected to three adjacent plate-shaped grid frames.

[0012] Furthermore, a preferred embodiment is proposed, wherein the plate-like grid frame is a non-uniform grid structure formed by the interlacing connection of longitudinal beams and transverse beams.

[0013] Furthermore, a preferred embodiment is proposed in which an in-cabin unit is installed on the plate-shaped grid frame, and the installation interface of the in-cabin unit is directly fixed to the longitudinal beams, transverse beams, or their intersection nodes of the plate-shaped grid frame.

[0014] Furthermore, a preferred embodiment is proposed, wherein the thermal control and protection outer panel is composed of multiple panels spliced ​​together, and flexible thermally conductive silicone strips are filled at the adjacent splicing seams. The thermal control and protection outer panel is provided with an outer panel opening, and the bracket of the external unit passes through the outer panel opening and is fixed on the plate-shaped grid frame.

[0015] Based on the same inventive concept, this invention also proposes a modular satellite assembly method based on an open grid skeleton, applied to the satellite structure described in any one of the above-mentioned methods, the method comprising: Individual cabin units are installed and cables are laid on their respective independent and open plate-like grid frames; Multiple plate-shaped grid frames, each containing an internal unit, are joined together to form an open, internally visible main load-bearing grid skeleton. A thermal control and protective outer panel is installed on the outside of the open main load-bearing grid skeleton.

[0016] Furthermore, a preferred embodiment is proposed in which the connecting cables between devices on adjacent plate-shaped mesh frames are laid inside the open main load-bearing mesh skeleton along a straight or approximately straight spatial path between the device interfaces.

[0017] Furthermore, a preferred embodiment is proposed in which the cable is fixed to the load-bearing structure of the plate-shaped mesh frame by cable ties, and the cable and cable ties are located below the inwardly recessed plane of the plate-shaped mesh frame.

[0018] Furthermore, a preferred embodiment is proposed in which the plurality of plate-shaped mesh frames are fixedly connected at the corner points where their edges meet using three-sided corner boxes; and the thermal control protection outer plate is fixed to the corresponding plate-shaped mesh frame with screws.

[0019] Compared with the prior art, the beneficial effects of the present invention are: The satellite structure proposed in this invention features a completely open main load-bearing grid framework. Throughout the entire process of equipment installation, cable laying, and final assembly to form the complete satellite frame, the operator's line of sight remains unobstructed. This allows for real-time, all-around observation of the status of all internal equipment, connectors, and cable bundles. This enables any potential equipment damage or cable interference issues to be immediately detected and corrected during installation, avoiding the difficult rework caused by discovering problems only after the traditional method of sealing and assembling the module. It eliminates such assembly hazards at the source, improving the quality and on-orbit reliability of the final product.

[0020] The satellite structure proposed in this invention allows for the connection of cables between devices via an open, visualized space, using the shortest path that approximates a straight line in space. Compared to the traditional method of laying cables along complex, pre-defined paths close to the wall, this reduces cable usage by 10%-20%, directly achieving weight reduction. Secondly, cables can be directly bundled to the load-bearing beams of the grid framework using cable ties, completely eliminating the reliance on adhesive cable clips. This not only eliminates the long waiting time required for adhesive curing, greatly improving assembly efficiency and adapting to mass production rhythms, but more importantly, it completely eliminates the long-term risk of adhesive aging and delamination in the hot, vacuum environment of space, leading to cable fixation failure, thus enhancing the space environment adaptability of the cable network system.

[0021] By separating the primary load-bearing function from the thermal control / protection function, the thermal control and protection outer plate in this invention no longer needs to bear structural loads or install equipment. Therefore, its material selection and thickness can be determined entirely and uniquely based on the on-orbit thermal environment requirements of the satellite surface. For example, the solar-facing side can use high thermal conductivity materials and increase its thickness to enhance heat dissipation, while the solar-repellent side can use extremely thin panels or even multi-layer thermal insulation components to achieve extreme weight reduction. The side facades can also be designed differently according to heat flux density. This functional separation design concept transforms the thermal control system from passively adapting to structural constraints to actively optimizing to meet the optimal thermal environment requirements of the payload, improving the overall thermal control efficiency and accuracy of the satellite. Furthermore, the primary load-bearing grid skeleton is designed non-uniformly through topology optimization, with materials concentrated at equipment installation points and along the main force transmission path, achieving efficient material utilization and extremely high specific stiffness. At the same time, the lightweight thermal control outer plate, freed from load-bearing functions, also significantly reduces the weight of non-load-bearing parts. Attached Figure Description

[0022] The accompanying drawings, which form part of this invention, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings: Figure 1 This is a schematic diagram of the open mesh skeleton described in this invention; Figure 2 This is an exploded view of the satellite structure described in this invention; Figure 3 This is a schematic diagram of the trihedral box described in this invention.

[0023] In the picture: 1-Plate-shaped grid frame, 2-Indoor unit, 3-Outdoor unit, 4-Three-sided corner box, 5-Thermal control and protection outer panel, 6-Outer panel opening. Detailed Implementation

[0024] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. It should be noted that, unless otherwise specified, the embodiments and features in the embodiments of the present invention can be combined with each other, and the described embodiments are only some embodiments of the present invention, not all embodiments.

[0025] Implementation Method 1, see [link] Figure 1 , Figure 2 and Figure 3 This embodiment describes a modular satellite structure based on an open grid framework. Addressing the shortcomings of existing methods, such as the failure to fundamentally eliminate blind operation and adhesive fixing, low cable laying efficiency, and excessive weight of the outer plate, this embodiment proposes such a modular satellite structure. The satellite structure includes: An open main load-bearing grid skeleton and multiple thermal control and protective outer plates 5; the open main load-bearing grid skeleton is composed of six plate-shaped grid frames 1 connected to each other to form a hexahedral cage-like skeleton; the thermal control and protective outer plates 5 are respectively disposed on at least one outer side of the open main load-bearing grid skeleton; The plate-shaped mesh frame 1 is used to install the thermal control protection outer plate 5 on one side plane, and its load-bearing structure is recessed inward. In practical applications, except for the edges around the perimeter, the longitudinal and transverse beams used to install the single unit on the side plane of the plate-shaped mesh frame 1 are recessed inward by a preset depth D, for example, 3mm. When laying cables, the cables can be directly and securely tied to the load-bearing beams using cable ties. Since all cable ties are constrained within the groove depth D, and their highest point does not exceed the mounting surface of the outer plate of the frame, the risk of the thermal control protection outer plate 5 being damaged by pressure is fundamentally eliminated during subsequent installation.

[0026] Furthermore, the satellite structure also includes a trihedral corner box 4, and the six plate-shaped grid frames 1 are fixedly connected at the corners where their edges meet through the trihedral corner box 4.

[0027] Furthermore, the trihedral box 4 has three mutually perpendicular connecting surfaces, which are respectively fixedly connected to three adjacent plate-shaped grid frames 1.

[0028] In this embodiment, the trihedral corner box 4 is an internal reinforcing component with three mutually perpendicular connecting surfaces. When the satellite is assembled, it is placed inside the corner formed by three adjacent plate-like grid frames 1, and is fastened to the three frames by bolts, expanding the point connection into a surface connection, which greatly enhances the torsional stiffness and connection reliability of the overall satellite structure.

[0029] In this embodiment, the plate-like grid frame 1 is a non-uniform grid structure formed by the interlacing of longitudinal and transverse beams. The grid division is not equal, but rather a customized topology design based on the layout, size, and installation interface positions of the internal and external single-unit devices 2 and 3 to be installed on the panel. This ensures that the mounting feet of each single-unit device can be directly and precisely fixed to the longitudinal or transverse beams, or fixed at the nodes formed by their intersection. The frame as a whole is integrally processed or spliced ​​from metal or composite materials, and can have extremely high specific stiffness.

[0030] In this embodiment, an in-cabin unit 2 is installed on the plate-shaped grid frame 1, and the installation interface of the in-cabin unit 2 is directly fixed to the longitudinal beams, transverse beams or their intersection nodes of the plate-shaped grid frame 1.

[0031] Furthermore, the thermal control protective outer panel 5 is composed of multiple panels spliced ​​together, and flexible thermally conductive silicone strips are filled at the adjacent splicing seams. The thermal control protective outer panel 5 is provided with an outer panel opening 6, and the bracket of the external unit 3 passes through the outer panel opening 6 and is fixed on the plate-shaped grid frame 1.

[0032] The lightweight, non-load-bearing thermal protection outer panel 5 described in this embodiment is an additional component independent of the main load-bearing frame. It is typically a thin aluminum honeycomb panel or composite material panel, fixed from the outside to the periphery or the longitudinal and transverse beams within the plate-like grid frame 1 using a small number of screws. The main function of the thermal protection outer panel 5 is thermal radiation control and micrometeoroid protection. Because it is non-load-bearing and does not require embedded installation equipment, it can be made very thin and light. The thickness of the thermal protection outer panel 5 on each side can be independently designed according to the thermal environment of that side; for example, a thicker panel on the sun-facing side to enhance heat dissipation, and a thinner panel on the shaded side, or the use of multi-layered insulation materials.

[0033] To accommodate the installation of extravehicular equipment, the thermal control and protective outer panel 5 can be designed as a series of panels joined together. Alternatively, openings 6 can be provided at the locations where extravehicular equipment needs to be installed. Aerospace-grade flexible thermally conductive silicone strips can be filled at the joints between adjacent thermal control and protective outer panels 5 to ensure continuous heat flow.

[0034] Compared to existing technologies that rely on a closed enclosure composed of multiple thick honeycomb panels as the overall load-bearing structure, with equipment mounted on the internal panels and the structure, thermal control, and protection functions highly coupled, the satellite structure proposed in this embodiment deconstructs the satellite body into a three-dimensional cage-like skeleton composed of open grids as the sole main load-bearing structure. The external thermal control and protection functions are then separated and handled by independent, lightweight outer panels. The core difference lies in transforming the traditional surface-bearing and surface-mounting mode into a beam-frame load-bearing and node / beam-system direct mounting mode. The equipment is directly mounted on the beams or nodes of the skeleton, resulting in a more direct and efficient force transmission path.

[0035] Compared to existing technologies where assembly is a blind or semi-blind operation conducted in a gradually enclosed space, this implementation method restructures the assembly process into three stages: fully open assembly, visualized closure, and final encapsulation. Utilizing the fully transparent nature of the mesh framework, the entire internal space of the satellite is completely exposed to the operator's view before final encapsulation, transforming the assembly process from blind to transparent. This is not merely a technological improvement, but a fundamental shift based on design-driven quality assurance.

[0036] Compared to existing technologies that require complex two-dimensional / three-dimensional cable routing paths pre-planned on the structural plate surface and secured with adhesive clips to prevent cable jamming during compartment assembly, the satellite structure designed in this embodiment creates a safe, lower-than-installation space for the cables by setting recessed binding areas on the main load-bearing beam, eliminating the possibility of cable jamming. Secondly, based on an open and visible environment, the principle of cable laying shifts to pursuing the optimal path for functional connections, allowing cables to connect between equipment along the shortest spatial path (approximately straight) and be directly fixed to the load-bearing frame, eliminating the root cause of the risk.

[0037] Compared to existing technologies where structural panels must simultaneously meet requirements for load-bearing capacity, installation, thermal control, and protection, and where thermal control design must be carried out under structural constraints, the thermal control and protection outer panel proposed in this embodiment is purified to solely handle heat exchange and space protection. This allows its design to fully comply with thermodynamic and space environment requirements, enabling single-objective optimal design. The outer panels on different sides can be independently and differentiated for extreme optimization in terms of materials, thickness, and coatings based on the thermal flow environment they face, achieving decoupling between thermal control design and structural design.

[0038] Implementation Method Two: This implementation method is a complete embodiment of the modular satellite structure based on an open grid framework described in Implementation Method One, including: A modular satellite structure with an open grid framework, which deconstructs the satellite body into two functionally independent and physically separated components: an open main load-bearing grid framework and a lightweight non-load-bearing thermal control and protection outer panel.

[0039] The open-type main load-bearing mesh framework consists of multiple plate-shaped mesh frames. The mesh of these plate-shaped mesh frames is designed non-uniformly according to the individual unit layout. Specifically, the design of the non-uniform mesh frame follows the principle of topology optimization. Using the installation points of individual equipment and the main load transmission path as constraints, the optimal beam distribution is determined through finite element analysis. This ensures that the longitudinal and transverse beams are mainly distributed at the equipment mounting feet and along the main load-bearing path of the satellite launch active segment. In non-critical areas, the optimal material distribution is achieved by increasing the mesh size. The frame is composed of crisscrossing beams, ensuring that each individual unit can be directly and stably mounted on the beams or nodes.

[0040] The outer panel of the mesh frame is recessed inward by 3mm. This recessed depth is optimized to match the standard nylon cable ties (2.5mm-3.6mm wide, approximately 2mm thick when tightened), ensuring that the bundled cables and ties are completely below the frame plane, physically eliminating the risk of cable compression. Simultaneously, this design synergizes with the visual assembly process: because the cables are strictly confined within the recessed depth, operators can be assured of no interference without inspection during outer panel installation, extending the visual value to the final encapsulation stage. Finally, multiple frames are assembled into a high-rigidity cage-like skeleton using screws and reinforcing corner boxes.

[0041] The lightweight, non-load-bearing thermal protection outer panels serve only to control thermal radiation, protect against micrometeoroids, and maintain the satellite's external aerodynamic shape; they do not participate in the main load-bearing function. Each outer panel can be discretely fixed to its corresponding plate-like grid frame using a small number of screws. The thickness and material of the outer panels can be differentiated according to the on-orbit heat flux density of the surface on which they are located. For example, the solar-facing side can use a high thermal conductivity metal-based composite material with an appropriately increased thickness to enhance heat dissipation; the solar-repellent side can use thin aluminum honeycomb panels or even multi-layer thermal insulation components to achieve extreme weight reduction; the side panels can use medium-thickness composite material panels coated with a thermal control coating with a medium absorptivity. Since the outer panels do not participate in load-bearing and have no embedded parts required, their material selection and thickness can completely conform to thermal control performance requirements, achieving fundamental freedom in thermal control design.

[0042] To accommodate the installation of external equipment (such as antennas and sensors), the outer panels can be designed as multi-piece splices, with openings or partial clearances at the equipment supports, allowing the equipment to be directly mounted on the main load-bearing grid frame. This design makes the outer panels themselves regular in shape and easy to manufacture. Aerospace-grade flexible thermally conductive silicone strips are used to fill the gaps between adjacent outer panels to establish an effective heat conduction path, compensate for installation gaps, and absorb some thermal deformation stress.

[0043] Implementation Method 3: This implementation method proposes a modular satellite assembly method based on an open grid framework, applicable to the satellite structure described in any one of Implementation Methods 1 to 2. The method includes: Install the individual cabin units 2 and lay cables on the independent and open plate-shaped grid frames 1; Multiple plate-shaped grid frames 1, each containing an internal unit 2, are joined together to form an open main load-bearing grid skeleton with an internally visible structure. A thermal control and protective outer plate 5 is installed on the outside of the open main load-bearing grid skeleton.

[0044] In this embodiment, the connecting cables between devices on adjacent plate-shaped mesh frames 1 are laid inside the open main load-bearing mesh skeleton along a straight or approximately straight path between the device interfaces.

[0045] In this embodiment, the cable is fixed to the load-bearing structure of the plate-shaped mesh frame 1 by cable ties, and the cable and cable ties are located below the inwardly recessed plane of the plate-shaped mesh frame 1.

[0046] In this embodiment, the plurality of plate-shaped mesh frames 1 are fixedly connected at the corners where their edges meet by a three-sided corner box 4; the thermal control protection outer plate 5 is fixed to the corresponding plate-shaped mesh frame 1 by screws.

[0047] The specific embodiments of the present invention disclosed above are merely illustrative of the invention. These embodiments do not exhaustively describe all details, nor do they limit the invention to the specific embodiments described. Many modifications and variations can be made based on the content of this specification. This specification selects and specifically describes these embodiments to better explain the principles and practical applications of the invention, thereby enabling those skilled in the art to better understand and utilize the invention.

Claims

1. A modular satellite structure based on an open grid framework, characterized in that, The satellite structure includes: An open main load-bearing grid skeleton and multiple thermal control protective outer plates (5); the open main load-bearing grid skeleton is composed of six plate-shaped grid frames (1) connected to each other to form a hexahedral cage-like skeleton; the thermal control protective outer plates (5) are respectively disposed on at least one outer side of the open main load-bearing grid skeleton; The plate-shaped mesh frame (1) is used to install one side plane of the thermal control protection outer plate (5), and its load-bearing structure is recessed inward.

2. The modular satellite structure based on an open grid framework according to claim 1, characterized in that, The satellite structure also includes a trihedral corner box (4), and the six plate-shaped grid frames (1) are fixedly connected at the corners where their edges meet through the trihedral corner box (4).

3. A modular satellite structure based on an open grid framework according to claim 2, characterized in that, The trihedral box (4) has three mutually perpendicular connecting surfaces, which are respectively fixedly connected to three adjacent plate-shaped grid frames (1).

4. A modular satellite structure based on an open grid framework according to claim 1, characterized in that, The plate-shaped grid frame (1) is a non-uniform grid structure formed by the interlacing of longitudinal beams and transverse beams.

5. A modular satellite structure based on an open grid framework according to claim 1, characterized in that, The plate-shaped grid frame (1) is equipped with an in-cabin unit (2), and the installation interface of the in-cabin unit (2) is directly fixed to the longitudinal beams, transverse beams or their intersection nodes of the plate-shaped grid frame (1).

6. A modular satellite structure based on an open grid framework according to claim 1, characterized in that, The thermal control protective outer panel (5) is composed of multiple panels spliced ​​together, and flexible thermally conductive silicone strips are filled at the adjacent splicing seams. The thermal control protective outer panel (5) is provided with an outer panel opening (6). The bracket of the external unit (3) passes through the outer panel opening (6) and is fixed on the plate-shaped grid frame (1).

7. A modular satellite assembly method based on an open grid skeleton, characterized in that, Applied to the satellite structure of any one of claims 1-6, the method comprises: Install the individual cabin units (2) and lay cables on the independent and open plate-shaped grid frames (1); Multiple plate-shaped grid frames (1) on which the cabin unit (2) is installed are joined together to form an open main load-bearing grid skeleton with internal visibility. A thermal control protective outer plate (5) is installed on the outside of the open main load-bearing grid skeleton.

8. A modular satellite assembly method based on an open mesh skeleton according to claim 7, characterized in that, The connecting cables between devices on adjacent plate-shaped grid frames (1) are laid inside the open main load-bearing grid skeleton along a straight or approximately straight path between the device interfaces.

9. A modular satellite assembly method based on an open mesh skeleton according to claim 7, characterized in that, The cable is fixed to the load-bearing structure of the plate-shaped grid frame (1) by cable ties, and the cable and cable ties are located below the inwardly recessed plane of the plate-shaped grid frame (1).

10. A modular satellite assembly method based on an open mesh skeleton according to claim 7, characterized in that, The multiple plate-shaped mesh frames (1) are fixedly connected at the corners where the edges meet by three-sided corner boxes (4); the thermal control protection outer plate (5) is fixed to the corresponding plate-shaped mesh frame (1) by screws.

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