Satellite design information hierarchical expression and phased management method and system

Abstract

The application provides a satellite design information hierarchical expression and phased management method and system, in a satellite structure cabin plate design stage, a satellite main control skeleton three-dimensional model and each subsystem single machine equipment mechanical interface three-dimensional model are created and controlled, satellite subsystem skeleton hierarchical design is carried out, a subsystem detailed interface skeleton model is formed, structure subsystem completes satellite structure cabin plate three-dimensional model design and is controlled for satellite cabin plate assembly production. In a satellite assembly design stage, based on the single machine equipment mechanical interface three-dimensional model, hierarchical single machine model components are established, single machine installation requirement related information is increased, and a three-dimensional model is created; based on each subsystem three-dimensional design model, hierarchical subsystem model components are established, assembly design requirement related contents are increased, and each subsystem assembly three-dimensional model is formed; synchronous three-dimensional models are collected, and an integral satellite assembly three-dimensional model is formed, which is used for satellite single machine equipment installation process and integral satellite assembly test process preparation.

Description

Technical Field

[0001] This invention relates to the technical field of spacecraft aerospace systems, specifically to a method and system for hierarchical expression and phased management of satellite design information. Background Technology

[0002] Satellite development is a complex systems engineering project, typically comprising multiple subsystems such as payload and structure, thermal control, overall circuitry, attitude and orbit control, propulsion, integrated electronics, and data transmission. The development process covers design (including single-unit design, overall design, and subsystem design), manufacturing (including product manufacturing and satellite assembly), and integration testing, characterized by its broad scope, high integration, and numerous states. Currently, Chinese satellite development companies can largely achieve overall digital engineering design for satellites. Compared to traditional two-dimensional drawings, this significantly improves design quality and efficiency, and also provides a complete 3D digital prototype of the mechanically related satellite with comprehensive design information. However, from the perspective of the entire development process, while existing digital 3D models express structured mechanical interface information, they do not yet reflect more electrical and thermal interface information and overall assembly design elements. This type of information is just as important as mechanical interface information for satellite developers. In addition, due to the repeated iterations in the satellite development process and the increasingly shorter satellite development cycle, the basic design of individual satellite units, subsystems, and overall design are required to be carried out simultaneously. This also poses new requirements for the phased management of satellite unit design information from the same source.

[0003] "Digital Cross-Unit Remote Parallel Collaborative Design and Integration Application of Satellites Based on 3D Models," *Cyberspace Military-Civilian Integration*, No. 7, 2020. This paper constructs a digital solution from the aspects of design environment, working mode, and development system, building a digital working environment for cross-domain parallel collaborative development in the satellite field, and fully realizing cross-domain collaborative parallel development of satellite design and manufacturing. This method mainly solves the interaction and collaboration of satellite design data information between cross-domain design units through the extended deployment of PDM platform and IDS software. This invention, however, achieves the same source control of satellite unit design information through the phased management of 3D models defined by hierarchical design information, thereby enabling designers of various subsystems and assembly processes to use the same original design model for their respective detailed designs.

[0004] "Digital Application of Small Satellites Based on MBD," *Aerospace Manufacturing Technology*, No. 21, 2015. This article mainly introduces the key issues that need to be addressed in the current digital design and manufacturing of small satellites: overall collaborative design and 3D factory prototyping. Through exploration and practice during the model development process, a preliminary set of fully 3D digital design and manufacturing methods has been formed, thereby realizing paperless design and manufacturing of small satellites. This method mainly utilizes MBD technology to transform 2D drawings into 3D models, forming a complete digital prototype of the satellite. While this method does not address the issue that 3D models can only reflect mechanical interfaces, it adds electrical and thermal interfaces and single-unit assembly design information to the skeleton model based on the original MBD, thus expanding the content and scope of collaborative design among various subsystems of the satellite.

[0005] "Research on Intelligent Development Methods for Commercial Satellites," Military and Civilian Dual-Use Technologies and Products, No. 5, 2019. This paper, aiming to meet the low-cost, mass production needs of commercial satellites, promotes a standardized and regulated approach to intelligent development. It introduces industrial information technology to connect various development stages, including design, manufacturing, testing, and integration. Based on data aggregation and information security, it utilizes data analysis, simulation modeling, and artificial intelligence technologies to improve the automation and intelligence of the development process, thus meeting the requirements for mass production of commercial satellites. The paper also points out that while aerospace companies currently use 3D graphics-assisted design, the design process lacks a foundation for efficient collaboration and continuous communication. This method, through hierarchical and phased management of design information from 3D models, achieves the same source distribution of design information among multiple satellite subsystems and manufacturing and testing departments, enabling efficient collaboration.

[0006] Therefore, in order to achieve unified management and control of design information elements of various disciplines such as the mechanical, electrical, and thermal interfaces of the satellite unit and the final assembly, and to enable the process designers of each subsystem and the final assembly to use the same set of original design models for their detailed designs, so as to make the design requirements more refined, sufficient and standardized, a new technical solution needs to be proposed. Summary of the Invention

[0007] To address the shortcomings of existing technologies, the purpose of this invention is to provide a method and system for hierarchical expression and phased management of satellite design information.

[0008] According to the present invention, a method for hierarchical expression and phased management of satellite design information is provided. The method includes a satellite structural panel design step and a satellite assembly design step. The satellite structural panel design step involves putting structural panel components into production, and the satellite assembly design step involves installing individual satellite equipment and compiling the process for whole-satellite assembly and testing.

[0009] Preferably, the satellite structural panel design steps include the following steps:

[0010] Step 1: Based on the overall satellite configuration, create and control a 3D model of the satellite's main control skeleton;

[0011] Step 2: Simultaneously with Step 1, create and control the 3D models of the mechanical interfaces of each subsystem's individual equipment;

[0012] Step 3: Conduct layered design of the satellite subsystem skeleton;

[0013] Step 4: Overall layout and professional design of each subsystem: Collaborative design using the skeleton models of each subsystem to form subsystem interface skeleton models and control them;

[0014] Step 5: Using the above-mentioned mechanical interface design model, complete the three-dimensional model of the satellite structural panel for production and use it in a controlled manner for the production of satellite panel components.

[0015] Preferably, step three involves creating a three-dimensional model of the satellite layout, structure, thermal control, cable network, and propulsion subsystem skeleton based on the main control skeleton;

[0016] The hierarchical design of the satellite subsystem skeleton refers to establishing hierarchical interfaces for the main control skeleton, overall layout skeleton, thermal control subsystem skeleton, overall circuit subsystem skeleton, propulsion subsystem skeleton, and structural subsystem skeleton based on the satellite main control skeleton model through replication and derivation, so that each subsystem can communicate via interfaces.

[0017] Preferably, the subsystems in step four include thermal control, cable network, and propulsion system;

[0018] The collaborative design of each subsystem in a hierarchical manner refers to the overall layout, thermal control subsystem, overall circuit subsystem, propulsion subsystem and structural subsystem obtaining the corresponding interface information of each unit from the product data management system as needed, carrying out satellite collaborative development work, and completing the production of structural products.

[0019] Preferably, the satellite assembly design steps include the following steps:

[0020] Step 1: Based on the 3D model of the mechanical interface of a single machine, establish a hierarchical single-machine model component;

[0021] Step 2: Based on the 3D design models of each subsystem, use the 3D model of the single-machine equipment installation requirements created in Step 1 to establish hierarchical subsystem model components;

[0022] Step 3: Collect the three-dimensional models of the above subsystems to form the three-dimensional model of the whole satellite assembly, and use it as the basis for compiling the installation process of satellite single equipment and the whole satellite assembly and integration process.

[0023] Preferably, step 1 involves adding information related to single-unit installation requirements to the component, creating a three-dimensional model of the single-unit equipment installation requirements, and subjecting it to control.

[0024] Preferably, the hierarchical single-machine model component in step 1 refers to the creation of a physical model within the satellite single-machine model component to store and express the mechanical interface information of the model.

[0025] Preferably, step 2 involves adding relevant content on the overall assembly design requirements to the components, forming a controlled three-dimensional model of the satellite layout, thermal control, cable network, and propulsion system assembly.

[0026] Preferably, the hierarchical subsystem model component in step 2 refers to the overall layout creation layout interface skeleton model. Each subsystem uses the hierarchical single-machine model component and layout interface skeleton model to obtain the overall layout and subsystem hierarchical design model containing the overall assembly design information, as well as the overall circuit, propulsion and structure.

[0027] The hierarchical expression and phased management of satellite design information refers to the hierarchical integration of satellite unit mechanical interface information, thermal interface information, electrical interface information and final assembly information into a single model component, and the controlled management of each layer of information in the product data management system according to the satellite development progress.

[0028] The present invention also provides a satellite design information hierarchical expression and phased management system, the system including a satellite structural panel design module and a satellite assembly design module. The satellite structural panel design module is responsible for the production of structural panel components, and the satellite assembly design module is responsible for the installation of individual satellite equipment and the compilation of whole satellite assembly and testing processes.

[0029] The satellite structural panel design module includes the following modules:

[0030] Module 1: Based on the overall satellite configuration, create and control a 3D model of the satellite's main control skeleton;

[0031] Module 2: Synchronously create and control the 3D models of the mechanical interfaces of individual devices in each subsystem, in conjunction with Module 1;

[0032] Module 3: Perform layered design of the satellite subsystem skeleton;

[0033] Module Four: Overall Layout and Specialization of Subsystems. Utilizing the skeleton models of each subsystem, collaborative design is carried out to form subsystem interface skeleton models and ensure their control.

[0034] Module 5: Using the above-mentioned mechanical interface design model, complete the 3D model of the satellite structural panel for production and use it in a controlled manner for the production of satellite panel components;

[0035] The satellite assembly design module includes the following modules:

[0036] Module 1: Based on the 3D model of the mechanical interface of a single machine, establish a hierarchical single-machine model component;

[0037] Module 2: Based on the 3D design models of each subsystem, use the 3D model of the single-machine equipment installation requirements created in Module 1 to establish hierarchical subsystem model components;

[0038] Module 3: Collect the three-dimensional models of the above subsystems to form the three-dimensional model of the whole satellite assembly, and use it as the basis for compiling the installation process of satellite single equipment and the whole satellite assembly and integration process.

[0039] Compared with the prior art, the present invention has the following beneficial effects:

[0040] 1. This invention utilizes stand-alone design model components containing more professional information and three-dimensional skeleton interface models of each subsystem to achieve more in-depth collaborative design of satellite subsystems, thereby avoiding design errors from the source and improving work efficiency;

[0041] 2. Currently, manufacturing and assembly design requirements are not standardized, with most requirements consisting of textual descriptions or, in some cases, tabular descriptions. This hinders the automated transmission of final assembly design data, making subsequent digital information work impossible. Compared to current model development methods, this approach allows the requirements of each subsystem of a single satellite unit to be expressed through the same model component, enabling structured design requirements for individual satellite units. This facilitates fine-grained and precise expression of requirements and subsequent comparison and tracking.

[0042] 3. This invention utilizes the hierarchical expression and phased control characteristics of single-unit design information to achieve simultaneous development of basic satellite unit design, subsystem design, and overall design. The relevant design information of the single unit can be controlled in stages according to the development progress, which is more adaptable to the actual situation of scientific research and production. It can reduce the cost of design communication and iteration, shorten the design cycle, and adapt to the satellite development needs under the new situation. Attached Figure Description

[0043] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0044] Figure 1 A flowchart for hierarchical information representation and phased management of satellite designs;

[0045] Figure 2 A schematic diagram illustrating the hierarchical representation of information for a single satellite unit;

[0046] Figure 3 A schematic diagram illustrating the main control framework for creating a satellite;

[0047] Figure 4 This is a schematic diagram of the subsystem skeleton derived from the main control skeleton;

[0048] Figure 5 This is a schematic diagram of the collaborative design of subsystems;

[0049] Figure 6 This is a schematic diagram of the cabin panel assembly design using the subsystem skeleton for the structural subsystem. Detailed Implementation

[0050] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0051] This invention relates to a method for hierarchical expression and phased control of satellite design information. This method can be widely used in the development process of satellite products. Through this invention, design information elements from various disciplines, such as mechanical, electrical, and thermal interfaces and final assembly, can be managed and controlled from the same source, making design requirements more refined, comprehensive, and standardized. Simultaneously, design information elements that cannot be determined in the short term can be controlled in stages through model design information, ensuring that all design information is controlled within the product information management system. This achieves refined management of satellite unit information, linkage between satellite process, manufacturing, and design, reduces the probability of errors, and improves development efficiency.

[0052] To address the shortcomings of existing satellite digital development models, this invention aims to provide a method for hierarchical expression and phased control of satellite design information, which enables unified and controlled management of design information elements across various disciplines, including mechanical, electrical, and thermal interfaces of individual satellite units and overall assembly.

[0053] To achieve the above-mentioned objectives, this invention mainly implements hierarchical expression and phased management of satellite design information in the following two stages.

[0054] The satellite structural panel design phase, primarily for the production of structural panel components, mainly includes the following steps:

[0055] Step 1: Based on the overall satellite configuration, create and control a 3D model of the satellite's main control skeleton;

[0056] Step 2: Simultaneously with Step 1, create and control the 3D models of the mechanical interfaces of each subsystem's individual equipment;

[0057] Step 3: Conduct layered design of satellite subsystem skeletons, that is, based on the main control skeleton, create three-dimensional models of the skeletons of various subsystems such as satellite layout, structure, thermal control, cable network, and propulsion.

[0058] Step 4: Overall layout and professional design of each subsystem. Collaborative design is carried out using the skeleton models of each subsystem to form the interface skeleton model of the subsystem and make it under control. In this embodiment, each subsystem includes thermal control, cable network and propulsion, etc.

[0059] Step 5: Using the above-mentioned mechanical interface design model, complete the three-dimensional model of the satellite structural panel for production and use it in a controlled manner for the production of satellite panel components.

[0060] During the satellite assembly and design phase, the main focus is on developing installation processes for individual satellite components and overall satellite assembly and testing procedures. This process primarily includes the following steps:

[0061] Step 1: Based on the 3D model of the mechanical interface of a single machine, establish a hierarchical single machine model component, add relevant information on the installation requirements of the single machine to the component, and create a 3D model of the installation requirements of the single machine and control it.

[0062] Step 2: Based on the 3D design models of each subsystem, use the 3D model of the single-unit equipment installation requirements created in Step 1 to establish hierarchical subsystem model components. Add relevant content of the overall assembly design requirements to the components to form a controlled 3D model of the overall assembly of each subsystem, such as satellite layout, thermal control, cable network and propulsion.

[0063] Step 3: Collect the three-dimensional models of the above subsystems to form the three-dimensional model of the whole satellite assembly, and use it as the basis for compiling the installation process of satellite single equipment and the whole satellite assembly and integration process.

[0064] The hierarchical representation and phased management of satellite design information refers to the hierarchical integration of satellite unit mechanical interface information, thermal interface information, electrical interface information and overall assembly information into a single model component, and the relatively independent controlled management of each layer of information in the product data management system according to the satellite development progress.

[0065] The hierarchical design of satellite subsystem skeletons refers to establishing interfaces for each subsystem, such as the main control skeleton, overall layout skeleton, thermal control subsystem skeleton, overall circuit subsystem skeleton, propulsion subsystem skeleton, and structural subsystem skeleton, based on the satellite main control skeleton model and through replication and derivation methods. These interfaces are then used by each subsystem for interface transmission and detailed design.

[0066] The collaborative design of each subsystem in a hierarchical manner refers to the fact that during satellite collaborative design, the overall layout, thermal control, overall circuit, propulsion and structural subsystems can obtain the corresponding interface information of the individual units from the product data management system as needed and carry out satellite collaborative development work, and finally complete the production of structural and other products.

[0067] The hierarchical single-unit model component refers to the creation of a solid model within the satellite single-unit model component to store and express the model's mechanical interface information; and the creation of three skeleton models, one of which serves as the carrier of the single-unit electrical interface information, one as the carrier of thermal characteristic information, and the last as the carrier of the assembly interface information of the single unit at each stage of satellite assembly, testing, and experimentation.

[0068] The hierarchical subsystem model components refer to the overall layout creation of the layout interface skeleton model and detailed design, while each subsystem utilizes the hierarchical single-machine model components and layout interface skeleton model, and after detailed design, obtains the overall layout and hierarchical design model of thermal control, overall circuit, propulsion and structural subsystems containing assembly design information.

[0069] The following is a detailed description of the method for hierarchical expression and phased management of satellite design information according to an example of the present invention, with reference to the accompanying drawings.

[0070] According to the present invention, a method for hierarchical expression and phased management of satellite design information is applied to the development of various types of satellites based on three-dimensional model definitions.

[0071] In the initial stage of satellite design, the satellite development unit establishes a design environment with the Product Data Management (PDM) system as the product data platform and the Model-Based Collaborative Design (MBD) system as the tool. In this embodiment, MBD refers to model-based definition.

[0072] During the satellite's conceptual or prototype design phase, each subsystem or unit development unit sets up its individual unit model. Initially, this involves setting the mechanical interfaces, electrical interfaces, thermal characteristics, and overall assembly requirements for each unit. Taking Pro / E Wildfire 5.0 software as an example... Figure 2 As shown, the above four aspects of information are placed in the models *_body, *_d, *_r, and *_a, respectively. The mechanical interface information model *_body is a part model, while the other three models are skeleton models. Once the model components are set up, they can be uploaded to the PDM system for review and approval, and then used for the detailed design of subsequent satellite subsystems. Generally, the mechanical interfaces, electrical interfaces, and thermal characteristics of a single satellite unit can be fully determined in the early stages of design, while assembly requirements, including disassembly and assembly information and participation in testing, may be continuously updated and generally need to be fully determined in the later stages. Therefore, the model components can be managed in stages: the *_body, *_d, and *_r models are uploaded to the PDM system first for detailed satellite design and structural panel production, while the *_a model is managed later for the development of installation processes for single-unit equipment and overall satellite assembly and testing processes during the satellite assembly stage.

[0073] At the same time, refer to Figure 3The satellite's overall design department creates a main skeleton model of the satellite based on its overall configuration. This model is then reviewed and approved within the PDM (Projected Design Model) and is under control. This skeleton model serves as the primary design carrier for the satellite's top-down digital design and a unified benchmark for three-dimensional collaboration during the detailed design phase. Subsequent refinements to the satellite's main control skeleton model, including the definition of design benchmark information such as layout benchmark coordinates, interface skeleton benchmark coordinates, and front panel dimensions, provide a basis for subsequent collaborative design and design reuse.

[0074] The satellite architecture is based on the satellite master control framework. Relevant content is effectively transferred to subsystems through subsystem derivation tools, and modular component filtering and cancellation of releases for specified nodes are supported, thereby deriving subsystem skeleton models, as shown below. Figure 4 As shown. According to existing data transmission rules, it is necessary to supplement the "satellite reference coordinate system" and "additional reference" in the overall satellite skeleton, add the "satellite reference coordinate system" in the modules and intermediate node components, and add the "satellite reference coordinate system," "additional reference," "layout environment," "interface skeleton environment," and "packet overlap area" in the panel component model. Through this step, the final three-dimensional skeleton models of each subsystem, including layout, structure, thermal control, cable network, and propulsion, are obtained.

[0075] Reference Figure 5 The overall layout is based on the controlled single-machine model, generating an overall layout interface skeleton. Subsystems such as thermal control, overall circuitry, and propulsion are designed collaboratively in layers, utilizing the overall layout interface skeleton in conjunction with subsystem design schemes to obtain detailed subsystem structural skeletons. Finally, the overall layout and each subsystem undergo interference checks and iterative design using their respective interface skeletons. The finalized subsystem interface skeletons are then uploaded to the PDM system and placed under control.

[0076] Reference Figure 6 The structural subsystem utilizes the aforementioned layout, thermal control, cable network, and propulsion subsystem interface model skeleton to complete the design and control of the three-dimensional model for the production of satellite structural panels, which is then used for the production of satellite panel components.

[0077] During the satellite's final assembly and testing phase, as mentioned earlier, each research and development unit refines the individual unit model components and controls them in the PDM system so that they can be used for the overall satellite assembly design during the final assembly phase.

[0078] Based on the previous three-dimensional design models of the subsystems, each subsystem uses phased controlled satellite unit models to establish hierarchical subsystem model components. The components include relevant content on the overall assembly design technical requirements, forming a controlled three-dimensional assembly model of each subsystem such as satellite layout, thermal control, cable network and propulsion.

[0079] The satellite as a whole collects and synchronizes the three-dimensional models of the above subsystems to form a three-dimensional model of the whole satellite assembly, which is then under control. This facilitates the satellite assembly process designers in developing the installation process of individual satellite equipment and the assembly and testing process of the whole satellite.

[0080] This invention also provides a system for hierarchical expression and phased management of satellite design information. The system includes a satellite structural panel design module and a satellite assembly design module. The satellite structural panel design module is responsible for the production of structural panel components, while the satellite assembly design module is responsible for the installation of individual satellite equipment and the development of overall satellite assembly and testing processes. The satellite structural panel design module includes the following modules:

[0081] Module 1: Based on the overall satellite configuration, create and control the 3D model of the satellite's main control skeleton; Module 2: Simultaneously create and control the 3D models of the mechanical interfaces of individual equipment in each subsystem; Module 3: Perform layered design of the satellite subsystem skeleton; Module 4: Collaborate on the overall layout and the professional design of each subsystem using the skeleton models of each subsystem to form the subsystem interface skeleton model; Module 5: Using the above mechanical interface design models, complete the 3D model of the satellite structural panel for production and control its use in the production of satellite panel components.

[0082] The satellite assembly and design module includes the following modules:

[0083] Module 1: Based on the 3D model of the mechanical interface of the single-unit equipment, establish a hierarchical single-unit model component; Module 2: Based on the 3D design model of each subsystem, use the 3D model of the installation requirements of the single-unit equipment created in Module 1 to establish a hierarchical subsystem model component; Module 3: Collect the 3D models of the overall assembly of the above subsystems to form the overall satellite assembly 3D model and control it as the basis for compiling the installation process of the satellite's single-unit equipment and the overall satellite assembly and integration process.

[0084] This invention utilizes single-unit design model components containing more specialized information and 3D skeleton interface models of various subsystems to achieve in-depth collaborative design of satellite subsystems, avoiding design errors from the outset and improving work efficiency. Currently, manufacturing and assembly design requirements are not standardized, with design requirements mostly described in text or, in some cases, in tables, making it impossible to automate the transmission of final assembly design data and hindering subsequent digital information work. Compared to current model development methods, this method allows the requirements of each subsystem of a single satellite unit to be expressed through the same model component, enabling structured design requirements for single satellite units, facilitating fine-grained and precise expression of requirements, and subsequent comparison and tracking. This invention leverages the hierarchical expression and phased control of single-unit design information to achieve simultaneous development of basic satellite unit, subsystem, and overall designs. Single-unit related design information can be controlled in stages according to the development progress, better adapting to the actual situation of scientific research and production, reducing design communication and iteration costs, and shortening the design cycle to meet the needs of satellite development under the new circumstances.

[0085] Those skilled in the art will understand that, besides implementing the system and its various devices, modules, and units provided by this invention in the form of purely computer-readable program code, the same functions can be achieved entirely through logical programming of the method steps, making the system and its various devices, modules, and units of this invention function in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers. Therefore, the system and its various devices, modules, and units provided by this invention can be considered as a hardware component, and the devices, modules, and units included therein for implementing various functions can also be considered as structures within the hardware component; alternatively, the devices, modules, and units for implementing various functions can be considered as both software modules implementing the method and structures within the hardware component.

[0086] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A method for hierarchical expression and phased management of satellite design information, characterized in that, The method includes satellite structural panel design steps and satellite assembly design steps. The satellite structural panel design steps involve putting structural panel components into production, while the satellite assembly design steps involve installing individual satellite equipment and developing processes for the overall satellite assembly and testing. The satellite assembly and design process includes the following steps: Step 1: Based on the 3D model of the mechanical interface of a single machine, establish a hierarchical single-machine model component; Step 2: Based on the 3D design models of each subsystem, use the 3D model of the single-machine equipment installation requirements created in Step 1 to establish hierarchical subsystem model components; Step 3: Collect the three-dimensional models of the above subsystems to form the three-dimensional model of the whole satellite assembly, and use it as the basis for compiling the installation process of satellite single equipment and the whole satellite assembly and integration process; The hierarchical subsystem model components in step 2 refer to the overall layout creation layout interface skeleton model. Each subsystem uses the hierarchical single-machine model components and layout interface skeleton model to obtain the overall layout and subsystem hierarchical design model containing the overall assembly design information, as well as the overall circuit, propulsion and structure. The hierarchical expression and phased management of satellite design information refers to the hierarchical integration of satellite unit mechanical interface information, thermal interface information, electrical interface information and final assembly information into a single model component, and the controlled management of each layer of information in the product data management system according to the satellite development progress. The hierarchical single-unit model component refers to the creation of a solid model within the satellite single-unit model component to store and express the model's mechanical interface information; and the creation of three skeleton models, one of which serves as the carrier of the single-unit electrical interface information, one as the carrier of thermal characteristic information, and the last as the carrier of the assembly interface information of the single unit at each stage of satellite assembly, testing, and experimentation.

2. The method for hierarchical expression and phased management of satellite design information according to claim 1, characterized in that, The satellite structural panel design process includes the following steps: Step 1: Based on the overall satellite configuration, create and control a 3D model of the satellite's main control skeleton; Step 2: Simultaneously with Step 1, create and control the 3D models of the mechanical interfaces of each subsystem's individual equipment; Step 3: Conduct layered design of the satellite subsystem skeleton; Step 4: Overall layout and professional design of each subsystem: Collaborative design using the skeleton models of each subsystem to form a controlled interface skeleton model of the subsystem; Step 5: Using the above-mentioned mechanical interface design model, complete the three-dimensional model of the satellite structural panel for production and use it in a controlled manner for the production of satellite panel components.

3. The method for hierarchical expression and phased management of satellite design information according to claim 2, characterized in that, Step three involves creating three-dimensional models of the satellite layout, structure, thermal control, cable network, and propulsion subsystems based on the main control skeleton. The hierarchical design of the satellite subsystem skeleton refers to establishing hierarchical interfaces for the main control skeleton, overall layout skeleton, thermal control subsystem skeleton, overall circuit subsystem skeleton, propulsion subsystem skeleton, and structural subsystem skeleton based on the satellite main control skeleton model through replication and derivation, so that each subsystem can communicate via interfaces.

4. The method for hierarchical expression and phased management of satellite design information according to claim 2, characterized in that, The subsystems in step four include thermal control, cable network, and propulsion system. The collaborative design of each subsystem in a hierarchical manner refers to the overall layout, thermal control subsystem, overall circuit subsystem, propulsion subsystem and structural subsystem obtaining the corresponding interface information of each unit from the product data management system as needed, carrying out satellite collaborative development work, and completing the production of structural products.

5. The method for hierarchical expression and phased management of satellite design information according to claim 1, characterized in that, Step 1 involves adding information related to single-machine installation requirements to the component, creating a 3D model of the single-machine equipment installation requirements, and making it controllable.

6. The method for hierarchical expression and phased management of satellite design information according to claim 1, characterized in that, The hierarchical single-machine model component in step 1 refers to the creation of a physical model within the satellite single-machine model component, which stores and expresses the mechanical interface information of the model.

7. The method for hierarchical expression and phased management of satellite design information according to claim 1, characterized in that, Step 2 involves adding relevant content on the overall assembly design requirements to the components, forming a three-dimensional model of the satellite layout, thermal control, cable network, and propulsion system assembly, which is then under control.

8. A system for hierarchical representation and phased management of satellite design information, characterized in that, The satellite design information layered expression and phased management method according to any one of claims 1 to 7 is used. The system includes a satellite structural panel design module and a satellite assembly design module. The satellite structural panel design module is responsible for the production of structural panel components. The satellite assembly design module is responsible for the installation of individual satellite equipment and the compilation of whole-satellite assembly and testing processes. The satellite structural panel design module includes the following modules: Module 1: Based on the overall satellite configuration, create and control a 3D model of the satellite's main control skeleton; Module 2: Synchronously create and control the 3D models of the mechanical interfaces of individual devices in each subsystem, in conjunction with Module 1; Module 3: Perform layered design of the satellite subsystem skeleton; Module Four: Overall Layout and Specialization of Subsystems. Utilizing the skeleton models of each subsystem, collaborative design is carried out to form subsystem interface skeleton models and ensure their control. Module 5: Using the above-mentioned mechanical interface design model, complete the 3D model of the satellite structural panel for production and use it in a controlled manner for the production of satellite panel components; The satellite assembly design module includes the following modules: Module 1: Based on the 3D model of the mechanical interface of a single machine, establish a hierarchical single-machine model component; Module 2: Based on the 3D design models of each subsystem, use the 3D model of the single-machine equipment installation requirements created in Module 1 to establish hierarchical subsystem model components; Module 3: Collect the three-dimensional models of the above subsystems to form the three-dimensional model of the whole satellite assembly, and use it as the basis for compiling the installation process of satellite single equipment and the whole satellite assembly and integration process.

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