Spacecraft assembly design state integrated construction system and method based on three-dimensional model

Abstract

This application provides a spacecraft assembly design status integration construction system and method based on a 3D model, belonging to the field of spacecraft design and manufacturing technology, aiming to solve the problems of information silos and collaborative difficulties in spacecraft assembly design. The system includes an assembly status integration display module and a component technical requirement planning and definition module. The assembly status integration display module, based on a professional design architecture, aggregates, lightweights, and integrates multi-disciplinary layout components into a unified architecture, and parses and manages design information. The component technical requirement planning and definition module, within the whole-vehicle model environment, provides structured definitions and management of assembly technical requirements. This application breaks down information barriers, improves collaborative efficiency, and lays the foundation for digital manufacturing by constructing a unified and information-complete digital prototype.

Description

Technical Field

[0001] This application relates to the field of spacecraft design and manufacturing technology, and in particular to a spacecraft assembly design state integration construction system and method based on a three-dimensional model. Background Technology

[0002] Spacecraft assembly is a complex systems engineering project that transforms design blueprints into physical products, involving multiple professional fields such as structure, electrical systems, and thermal control. During the development of spacecraft, the accurate and efficient transmission and integration of design information directly affects the development cycle and final quality of the spacecraft.

[0003] In existing technologies, the design information transmitted from the design department to the final assembly and manufacturing department typically takes various forms, including traditional two-dimensional drawings, technical documents, and three-dimensional models. Some solutions attempt to integrate design information from multiple disciplines such as mechanical, electrical, and thermal control to build a unified digital prototype for final assembly. However, this model still has significant drawbacks. First, the problem of information silos is severe. Three-dimensional models often only contain geometric information, while key electrical attributes (such as node connection relationships) and thermal control attributes (such as thermal control parameters) and other non-geometric information still need to be manually linked through separate documents or tables, failing to form a unified data flow, resulting in information fragmentation and low collaboration efficiency. Second, there is a lack of systematic top-level planning and integration. The design of each subsystem (such as single-unit product layout, cable routing, and thermal control product layout) is carried out in its own independent model environment, making cross-disciplinary product interference checks and spatial coordination at the overall design level extremely difficult. Problems are often only discovered in the later stages of final assembly, causing a large amount of rework and delays. Finally, the management of final assembly technical requirements is chaotic. The assembly technical requirements for each unit and subsystem product (such as torque, cleanliness, assembly sequence, etc.) are scattered in different technical documents in an unstructured form. Assembly personnel need to spend a lot of manpower to collect, extract and organize them, which is not only inefficient but also prone to errors and makes it difficult to achieve standardized and intelligent management. Summary of the Invention

[0004] The purpose of this application is to provide a spacecraft assembly design state integration construction system and method based on a three-dimensional model, in order to solve the technical problems in the prior art where spacecraft assembly design information exists independently in multiple forms and from multiple sources, lacking a unified data source and structured management, resulting in information silos, difficulties in cross-disciplinary collaboration, and low efficiency in design and manufacturing iteration.

[0005] To achieve the above objectives, this application provides a spacecraft assembly design status integration and construction system based on a three-dimensional model, comprising: an assembly status integration display module, configured to aggregate layout elements in the overall spacecraft architecture model based on multiple preset professional design architectures, perform lightweight processing on the layout elements, and integrate the processed layout elements into a unified overall assembly architecture, while parsing and uniformly managing the design information contained in the source design model; and a component technical requirement planning and definition module, configured to inherit, extract, and define product matching information and assembly technical requirements in the whole spacecraft model environment based on the assembly technical requirement information of each component of the spacecraft.

[0006] Optionally, the multiple professional design architectures include: overall configuration layout architecture, structural assembly architecture, cable laying architecture, and thermal control design architecture.

[0007] Optionally, the overall configuration layout architecture includes at least one of the following: overall architecture design information, single-unit equipment layout design information, general assembly direct component design information, and single-unit installation fastener information; the structural assembly architecture includes at least one of the following: frame assembly design information, cabin panel assembly design information, and structural fastening design information.

[0008] Optionally, the cable laying architecture includes at least one of the following: cable harness assembly, clamp bracket assembly, electrical connector assembly, and node data connection relationship; the thermal control design architecture includes at least one of the following: layout design information of heat pipe, heater, coating, thermistor, multilayer, and thermocouple.

[0009] Optionally, the method by which the assembly status integrated display module performs lightweight processing on the layout elements includes: simplifying the geometric shape of the layout elements by adopting a layout component shrinking envelope, while retaining their key engineering attributes.

[0010] Optionally, the key engineering attributes include at least one of the mounting base surface of the layout element, the connector coordinate system, or the pin definition.

[0011] Optionally, the component technical requirements planning and definition module is further configured to: process the final assembly technical requirements information into structured data and establish data association with the component elements in the overall final assembly architecture.

[0012] Optionally, the system is further configured to: visualize the component elements associated with structured data on a client device to provide assembly personnel with digital work instructions corresponding to the component elements.

[0013] Optionally, the design information is non-geometric attribute information, and the non-geometric attribute information includes at least one of the cable node data connection relationship and thermal control component number information.

[0014] To achieve the above objectives, this application also provides a method for integrating and constructing the overall design state of a spacecraft based on a three-dimensional model, comprising the following steps: based on multiple preset professional design architectures, aggregating layout elements in the overall spacecraft architecture model; performing lightweight processing on the layout elements; integrating the processed layout elements into a unified overall assembly architecture, while parsing and uniformly managing the design information contained in the source design model; and inheriting, extracting, and defining product matching information and assembly technical requirements in the whole spacecraft model environment based on the assembly technical requirements information of each component of the spacecraft.

[0015] Compared with existing technologies, the technical solution provided in this application has the following beneficial effects: By conducting top-level planning based on a unified professional design architecture and aggregating the design results, non-geometric attributes, and supporting information of various subsystems using a 3D model as a unified source, information barriers between disciplines are broken down, and a unified design status view is constructed. This allows cross-disciplinary interference checks and status coordination to be carried out in the early stages of design, significantly improving the collaborative efficiency of design and manufacturing departments and reducing iteration costs during the development process. Furthermore, by unifying and structuring the assembly requirements information of various spacecraft components and directly associating it with 3D model elements, the inefficient work mode that previously relied on manually reviewing a large number of documents is changed, effectively saving labor costs. At the same time, this structured model and data provides the necessary model carrier and data foundation for further intelligent management of spacecraft assembly, integration, and testing, laying a solid foundation for realizing digital and intelligent manufacturing. Attached Figure Description

[0016] 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:

[0017] Figure 1 A schematic diagram of a spacecraft assembly design state integration and construction system based on a three-dimensional model is provided for embodiments of this application; Figure 2 A schematic diagram of the system workflow provided in the embodiments of this application; Figure 3 A detailed flowchart of a spacecraft assembly design state integration construction method based on a three-dimensional model, provided for embodiments of this application; Figure 4 This is a timing diagram of the signaling interactions between different parts of the system in one embodiment of this application; Figure 5 This is a schematic diagram of the system hardware deployment provided in an embodiment of this application. Detailed Implementation

[0018] 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.

[0019] like Figure 1 As shown, the spacecraft assembly design status integration construction system based on a three-dimensional model provided by the present invention includes an assembly status integration display module and a component technical requirement planning and definition module.

[0020] The overall assembly status integrated display module is planned based on four major spacecraft architectures: overall configuration layout architecture, structural assembly architecture, cable laying architecture, and thermal control design architecture. It aggregates the layout components at the assembly level of the overall spacecraft architecture model and uses a layout component shrink envelope form for lightweight processing. It is then released and integrated into the overall assembly model system architecture. At the same time, it parses the design information contained in the source design model for unified management. The component technical requirements planning and definition module is based on the overall assembly technical requirements information of each component, structure, cable, and thermal control of the spacecraft. It can inherit, extract, and define product matching information and overall assembly technical requirements from the perspective of the entire spacecraft.

[0021] like Figure 2 As shown, the application process of this invention is as follows: First, based on the overall spacecraft architecture, the overall designer derives the final assembly design status architecture, and then derives four major spacecraft architectures: overall layout, structural assembly, cable laying, and thermal control design. The layout components at the assembly level of the overall spacecraft architecture are integrated, and a lightweighting process is implemented using a layout component shrinking envelope approach. This information is then published and integrated into the final assembly model architecture, while simultaneously parsing and managing the design information contained in the source design model. Next, each subsystem designer integrates their respective subsystem design information based on the overall layout, structural assembly, cable laying, and thermal control design architectures. Finally, the overall designer integrates the design information of the four major architectures and publishes it to the integrated final assembly design status display module and the integrated component technical planning definition module, providing design information for subsequent spacecraft development processes.

[0022] The overall configuration layout architecture includes overall vehicle architecture design information, individual equipment layout design information, assembly direct component design information, and individual installation fastener information. The overall vehicle architecture design information, referencing the overall spacecraft layout design plan, includes structural design information for the vehicle-section-panel architecture (including truss architecture). Assembly information under each architecture can be synchronized in real time, and after synchronization, the architecture at that level can inherit the design information of the previous level's components. The structural assembly architecture includes truss assembly design information, panel component design information, structural fastening design information, and panel component codes. The cable laying architecture includes cable harness assembly, clamp bracket assembly, electrical connector assembly, direct component layout, and node data connection relationships. The thermal control design architecture includes heat pipe, heater, coating, thermistor, multilayer, and thermocouple layout design information, as well as thermal control component numbering information.

[0023] The assembly status integrated display module has the following functions: 1) It can complete the assembly of the overall layout, structure, cable and thermal control design models of the spacecraft; 2) The model assembly hierarchy is combined according to the overall vehicle architecture hierarchy; 3) The assembly components of the model are indexed by model type, including equipment layout, truss, panel assembly, cable, clamp, electrical connector, heat pipe, heater, coating, thermistor, thermocouple, multilayer and direct components of each subsystem; 4) The model can synchronously integrate the design information of each subsystem, including the fastening design, node data, thermal control number, and integrated design information under each architecture.

[0024] The component technical requirements planning and definition module can be used for the AIT standardization design and related information definition, browsing and extraction of spacecraft assembly. It can inherit, extract and define the product matching information and assembly technical requirements information of each component, structure, cable and thermal control of the spacecraft.

[0025] Example 1 This embodiment provides a specific implementation scheme for a spacecraft assembly design state integration construction system based on a 3D model. This embodiment will elaborate on how the system, based on a unified top-level architecture plan, aggregates multi-disciplinary design models, performs lightweight processing and information integration, and associates structured assembly technical requirements, ultimately constructing an information-complete, lightweight, and efficient digital prototype for spacecraft assembly.

[0026] Reference Figure 5The system described in this embodiment can be deployed in a typical client / server hardware environment. This environment includes one or more central servers 100 as the core, internally configured with high-performance processors, large-capacity memory, and storage arrays for storing massive amounts of models and data. Core system software and an enterprise-level database 110, such as Oracle or SQL Server, run on the central server 100 to persistently store all design data, model data, technical requirement data, and process data of the spacecraft. It should be noted that this database 110 constitutes the data hub of the entire system. Multiple designer workstations 130 and workshop tablet terminals 140 deployed in the final assembly workshop are connected to the central server 100 via a high-speed, stable internal network 120 (e.g., gigabit Ethernet). The designer workstations 130 are the main client devices for designers of various specialties (such as general designers, structural designers, electrical designers, thermal control designers, etc.) to perform 3D modeling, design, and interact with the system; while the workshop tablet terminals 140 are mobile client devices for final assembly process personnel and on-site assembly technicians to view digital instructions and receive feedback on assembly process data.

[0027] From a software architecture perspective, and referring to Figure 1 The system provided in this application is logically composed of two core functional modules: the final assembly status integrated display module 10 and the component technical requirements planning and definition module 20. The two work together to form the core of the technical solution of this application.

[0028] The core function of the assembly status integrated display module 10 is to integrate multi-disciplinary design information. Specifically, this module performs top-level planning and data organization based on multiple preset professional design architectures. In this embodiment, these professional design architectures are specifically embodied in four major system architectures: overall layout architecture 11, structural assembly architecture 12, cable laying architecture 13, and thermal control design architecture 14. These four architectures act like a predefined, hierarchical directory tree or data template, providing a unified organizational and attribution framework for design data from different disciplines and sources. After each professional designer completes their part of the design, they upload their respective professional design models (i.e., layout elements) to the system. Upon receiving these models, the assembly status integrated display module 10 performs a series of processes. This module can aggregate layout elements from different assembly levels in the overall spacecraft architecture model, such as the panel assembly model uploaded by the structural designer, the cable bundle model uploaded by the cable designer, and the multi-layer wrapping model uploaded by the thermal control designer. Furthermore, to address the issue of excessive data volume in large-scale spacecraft models after integration, which can lead to display lag or even crashes, this module performs lightweight processing on the received layout components. After processing, these lightweight models, along with their associated design information, are published and integrated into a unified overall assembly architecture. This overall assembly architecture is a virtual and complete digital prototype of the spacecraft, containing design results from all disciplines. Crucially, the assembly status integration display module 10, while integrating the geometric model, also parses and uniformly manages various design information contained in the source design model, particularly non-geometric attributes such as cable node connections, power consumption parameters of individual devices, and optical parameters of thermal control coatings. In this way, the final digital prototype not only possesses a "form" but also rich "content," truly breaking down information silos.

[0029] Correspondingly, the component technical requirements planning and definition module 20 focuses on solving the management and application problems of final assembly process information. In the traditional model, final assembly technical requirements are scattered among a large number of two-dimensional drawings, process documents, and technical specifications, which are not only inconsistent in form but also difficult to find. This module is configured to operate based on the final assembly technical requirements information of various components of the spacecraft (including but not limited to single-unit equipment, structural parts, cables, thermal control products, etc.). It provides an interactive interface that allows process designers to intuitively inherit, extract, and define product matching information and final assembly technical requirements in the overall model environment, that is, in the unified three-dimensional view constructed by the final assembly status integrated display module 10. For example, a process designer can select a specific bolt in the three-dimensional model and then define a structured tightening torque requirement for it; or select a connector and define a mating force and cleanliness requirement for it. These originally unstructured text requirements are transformed into computer-readable structured data that is precisely associated with specific three-dimensional components through this module.

[0030] The following will combine Figure 2 , Figure 3 and Figure 4 The workflow and methods of the system in this embodiment are described in detail.

[0031] Specifically, the workflow can be summarized as follows: Figure 2 The three main stages are shown. First, the derivation of the four major spacecraft architectures is carried out. At the beginning of the project, the overall designer or system administrator will create a new spacecraft model project in the system. The system will automatically generate the data structure of the project in database 110 based on the preset template, and this structure corresponds to... Figure 1 The diagram shows the overall layout architecture 11, structural assembly architecture 12, cable laying architecture 13, and thermal control design architecture 14. This lays the foundation for subsequent parallel design work by various disciplines and the integration of data into a unified framework.

[0032] Subsequently, the process enters a parallel, ongoing design and data integration phase, namely the step of setting detailed design information and final assembly requirements. This macro-level step includes a series of steps such as... Figure 3 The more detailed sub-steps are shown below. Using the work of a structural designer as an example, and referring to... Figure 4 The sequence diagram shows that after structural designer 200 completes the 3D design of a certain panel component on his local designer workstation 130, he uploads the model to the system server 300 through client software.

[0033] Upon receiving the professional design model (step S100), such as a STEP or CATIA native format file, the system server 300 automatically triggers the shrink envelope lightweighting process (step S110). An internal engine of the assembly status integrated display module 10 processes this detailed cabin model. Understandably, if the model is extremely complex, containing numerous internal details, small chamfers, small holes, etc., the lightweighting engine will use a shrink envelope algorithm to generate a simplified model with a similar shape but a significantly reduced number of facets. This process aims to ensure that even when the final star model integrates tens of thousands of parts, scaling, translation, and rotation operations can still be performed smoothly.

[0034] During or after the lightweighting process, the system performs non-geometric information parsing (step S120). The assembly status integrated display module 10 parses the attribute information embedded in the source model file or the metadata file uploaded with the model. For example, it can extract non-geometric attributes such as the material grade, supplier information, design version number, and quality of the panel assembly, and associate this information with the lightweighted model entity in the database 110.

[0035] Meanwhile, or after the design has reached a certain level of maturity, the final assembly process engineer can begin defining the technical requirements. Through the interface of the component technical requirements planning and definition module 20, the engineer loads the already-stored compartment model in the integrated view, selects the reserved threaded hole on the model used to install a specific piece of equipment, and then performs the association operation for the final assembly technical requirements (step S130). A dialog box pops up where the process engineer enters the bolt tightening torque requirement corresponding to the threaded hole during assembly, such as "5 ± 0.2 Nm," and specifies the cleanliness level as "Grade A." This information is processed into structured data by the component technical requirements planning and definition module 20 and stored in the database 110, precisely associated with the geometric entity of the threaded hole.

[0036] Finally, the system performs integration into the unified model (step S140). The processed panel assembly model, along with its associated non-geometric information and assembly technical requirements, is formally released into the overall assembly architecture, becoming part of the entire spacecraft digital prototype. For example... Figure 4 As shown, the system server 300 writes the processed and associated data into the database 400 (logically corresponding to the database 110) and returns a message of successful processing to the structural designer 200.

[0037] When other professionals (such as cable designers) need to design cable routes, they can retrieve the integrated model containing the aforementioned panels from the system, perform the wiring design in that 3D environment, and then upload the cable model. The system will repeat steps S100 to S140 to integrate the cable model as well.

[0038] The final stage of the process is integration and deployment. Once all professional design information has been integrated according to the above process, the system forms a unified, complete, and lightweight final assembly design status model. Any authorized user, whether a design review expert, final assembly process engineer, or project manager, can query and review the integrated model at any time through a client (such as Designer Workstation 130). During design review meetings, reviewers can simultaneously view structural panels and cable bundles in a single view and, through the system's interference check function, instantly identify instances where cables are too close to the edge of the panel, posing a risk of wear. Simultaneously, clicking on any screw on the model displays the previously defined torque requirements in its properties window, thus achieving seamless integration and visualization of design geometric and non-geometric attributes and process information.

[0039] This embodiment, through the aforementioned system and method, achieves automatic aggregation and lightweight display of multi-disciplinary design models, and directly associates process requirements with model components. It effectively solves the problems of information fragmentation and difficulty in collaboration in the prior art, significantly improves the efficiency of design review and problem discovery, and lays a solid data foundation for the efficient development of spacecraft.

[0040] Example 2 This embodiment, as a preferred implementation, elaborates on the detailed information managed within the four major spacecraft architectures upon which the assembly status integrated display module 10 is based, building upon Embodiment 1. Through a refined and structured definition of the architecture content, the technical solution of this application enables more in-depth and comprehensive management of spacecraft design information, thereby providing a precise data source for subsequent advanced applications such as automatic generation of bills of materials, cost accounting, and quality traceability.

[0041] In one specific embodiment of this application, Figure 1 The four main system architectures shown (overall layout architecture 11, structural assembly architecture 12, cable laying architecture 13, and thermal control design architecture 14) are designed as entities with specific data structures in database 110. Each architecture contains a series of subcategories for organizing and storing specific professional design information.

[0042] Specifically, the overall layout architecture 11 is primarily responsible for managing the layout and configuration information at the overall spacecraft level. As a specific implementation, this architecture can include the following types of information: 1. Overall spacecraft architecture design information: This part defines the overall framework of the spacecraft, including the overall coordinate system, outer envelope dimensions, division of major functional modules, and theoretical values ​​of mass characteristics (such as center of mass and moment of inertia), serving as the foundation and constraint for all other design work. 2. Individual equipment layout design information: This part precisely records the installation position and attitude of each individual product on the spacecraft (such as star sensors, transponders, various controllers, etc.). In other words, the system stores the six degrees of freedom (X, Y, Z translation and rotation angles around the three axes) of each individual equipment model in the coordinate system of its higher-level assembly (such as a certain panel), as well as the equipment's unique identifier, name, power consumption, weight, and other key attributes. 3. Assembly Direct Component Design Information: This section manages individual components that are not part of a specific unit or subsystem but need to be directly installed onto the overall satellite structure during the assembly phase, such as waveguides, special brackets, and identification plates. The system records the model and spatial location of these direct components. 4. Unit Installation Fastener Information: To achieve precise management of assembly details, this architecture also manages the fastener information used to install each unit. For example, when a layout designer places a star sensor in the model, the system guides the association with the four M5 titanium bolts used to secure the device. The database establishes an association between the star sensor and these four bolt instances, recording information such as the bolt's part number and batch number.

[0043] The core task of the structural assembly architecture 12 is to manage all load-bearing and non-load-bearing structural components of the spacecraft. As a specific implementation, this architecture may include: 1. Frame assembly design information: This part manages the main load-bearing structures that constitute the spacecraft's skeleton, such as the central load-bearing tube, truss structure, and frame beams. The system organizes these members and node models in the form of assemblies and manages the connections between them. 2. Cabin panel assembly design information: This part manages all wall panels of the spacecraft, including equipment mounting panels, outer side panels, and honeycomb sandwich panels. Each cabinet panel assembly may itself be a complex assembly, containing panels, embedded inserts, and stiffeners. The system assigns a unique code to each cabinet panel assembly and manages its detailed 3D model and material information. 3. Structural fastening design information: This part specifically manages various structural fasteners used to connect the aforementioned frames and cabinet panels, such as high-strength bolts, rivets, and adhesive joints. The system not only records the location and type of these fasteners but also associates their assembly process requirements within this architecture.

[0044] The cable laying architecture 13 is used to manage the intricate cable network inside the spacecraft. As a specific implementation, this architecture may include: 1. Cable harness assembly: This section, presented as a 3D model, precisely represents the routing, path, bending radius, and diameter of each cable harness within the spacecraft. 2. Clamp and bracket assembly: This section records the location, type, and installation method of all clamps, brackets, and binding tapes used to secure the cable harnesses. 3. Electrical connector assembly: This section manages the models of all electrical connectors at both ends of the cables and on equipment interfaces, including their type, specifications, installation location, and mating direction. 4. Node data connection relationships: This is crucial non-geometric information in the cable laying architecture. It clearly defines the logical relationships of electrical connections in the form of structured data; for example, it records that "pin 5 of connector A1 is connected to pin 12 of connector B3 via wire W007." This information is fundamental to the correct functioning of the electrical system and serves as the basis for electrical testing.

[0045] Finally, the thermal control design architecture 14 manages all thermal control products and measures required to ensure the temperature environment necessary for the spacecraft to operate normally in orbit. As a specific implementation, this architecture can include layout design information for various thermal control products, such as: 1. Heat pipe and heater layout design information: recording the heat pipe's laying path, dimensions, and heat transfer capacity, as well as the heater patch's location, shape, power, and control loop number. 2. Coating and multilayer layout design information: recording the geometric areas sprayed or pasted with different thermal control coatings (such as OSR, conductive white paint, etc.), material properties (such as absorptivity, emissivity), and the coverage area, number of layers, and material specifications of multilayer thermal insulation components. 3. Thermistor and thermocouple layout design information: accurately recording the installation point location, temperature measurement range, and unique channel number in the telemetry system for each temperature sensor (such as thermistor and thermocouple), i.e., the thermal control element number information.

[0046] By meticulously managing the four main architectural components mentioned above, the system in this application not only integrates discrete geometric models but also constructs a structured digital prototype of the spacecraft, rich in engineering semantics. When it is necessary to generate a bill of materials for the entire satellite, the system can traverse these architectures and automatically calculate the required number of individual units, cable lengths, number of screws of specific types, etc., thereby greatly improving the accuracy and efficiency of the work.

[0047] Example 3 This embodiment focuses on a key technical feature of the integrated display module 10 for final assembly status—"lightweight processing using a layout component shrink envelope"—and elaborates on its intelligent implementation and preservation of engineering semantics. This approach is crucial for overcoming performance bottlenecks in large-scale complex assemblies, while avoiding the loss of critical information associated with traditional lightweighting methods.

[0048] In spacecraft assembly design, many components, especially purchased parts or standard parts from other professional designs, often have 3D models containing extremely rich geometric details. For example, a standard aerospace electrical connector model may consist of hundreds of parts, including the connector housing, insulator, dozens of precision pins and sockets, locking sleeves, and tail accessories. Its model file size can reach tens of megabytes, containing tens or even hundreds of thousands of triangular faces. When a spacecraft assembly model needs to integrate hundreds or thousands of such connectors and other equally complex equipment, directly loading all the original details of the model would result in a total data volume reaching GB or even TB levels. This poses a huge challenge to any graphics workstation, causing extreme lag in interactive operation and hindering effective design reviews and assembly simulations.

[0049] To address this issue, the assembly status integrated display module 10 in this embodiment integrates a "semantic lightweight engine." This engine executes... Figure 3 The shrinking envelope lightweighting step S110 shown does not involve indiscriminate geometric simplification, but rather employs an intelligent strategy that preserves key engineering attributes.

[0050] Specifically, the semantic lightweight engine works as follows: Internally, the engine has a user-defined rule base. These rules trigger different lightweight strategies based on the component's type or metadata attributes. For example, a rule could be defined as: "If a component's 'type' attribute is 'electrical connector,' then apply connector-specific lightweight rules"; "If the component type is 'standard fastener,' then apply fastener simplification rules"; "For 'structural beam,' then preserve its axis and cross-sectional information."

[0051] When the system receives a professional design model (step S100), such as the aforementioned complex electrical connector model, the semantic lightweight engine first identifies its type. The identification method can be by parsing the model's built-in attributes, or based on the filename, directory structure, or manual specification by the user.

[0052] After identifying it as an "electrical connector," the engine applies preset rules to perform lightweighting. This process specifically includes: Geometric simplification: The engine uses geometric algorithms such as shrinking envelope or shell to generate a single, closed, simplified geometry that tightly encloses all the external parts of the connector. The simplified geometry's outline closely resembles the original model, but all its internal complex structures (such as pins and threads) are "filled," reducing the number of triangular facets from hundreds of thousands to a few hundred, achieving a data compression of hundreds of times. Ultimately, this complex connector may appear as a simple cube or cylinder with a roughly defined shape in a 3D view.

[0053] Preservation and Remapping of Key Engineering Attributes: Unlike traditional lightweighting methods, this approach simplifies the geometry while extracting and retaining attribute information crucial for subsequent assembly, docking, and testing activities. This information is then added as new attributes to the simplified geometry. For the electrical connector example, the key engineering attributes to be retained include at least: – Mounting Surface: This is the plane on which the connector is used to secure itself to the equipment housing or panel. The engine precisely extracts the geometric definition of this plane (e.g., a plane equation or three points on the plane) and stores it as an attribute. Thus, during virtual assembly checks, the system can accurately determine whether the connector's mounting surface is perfectly aligned with the panel's mounting surface without relying on the lost detailed geometry.

[0054] – Connector Coordinate System: Each connector has its own local coordinate system, which defines its insertion / removal direction and rotation angle. This coordinate system is crucial for checking whether two connectors can mate correctly. The engine extracts this coordinate system (typically defined by an origin and three orthogonal axis vectors) and attaches it to the simplified model.

[0055] – Pin Definitions: This is typical non-geometric information, including the pin number, name, signal type, etc. This information is usually extracted and associated with the connector model in step S120, where non-geometric information is parsed. During the lightweighting process, this association is fully inherited and attached to the simplified model.

[0056] Through the steps described above, a large and complex electrical connector model is transformed into a "smart agent" with a very small data size but rich engineering semantics, including mounting surfaces, mating coordinate systems, and pin electrical definitions. When a user observes this simplified connector in the integrated assembly model, they can not only see its spatial location and approximate shape but also query all its key engineering attributes. Correspondingly, the system can also use these attributes for more advanced analyses, such as automatically determining mating compatibility and generating cable wiring diagrams.

[0057] This intelligent lightweight method, which simplifies the geometric shape by adopting a layout component shrinking envelope form while retaining its key engineering attributes, perfectly balances the contradiction between the smoothness of large-scale scene display and the integrity of engineering information. It solves the pain point of losing key design intent caused by traditional lightweight methods and is one of the key technologies for realizing efficient and reliable digital prototypes for spacecraft assembly.

[0058] Example 4 This embodiment details how the component technical requirements planning and definition module 20 achieves structured management of final assembly technical requirements, and how these structured requirements are applied to the actual final assembly process, thereby realizing a digital information closed loop from design to manufacturing. It demonstrates the significant beneficial effects of the technical solution of this application in improving the standardization and accuracy of final assembly and in constructing a spacecraft "digital twin."

[0059] Building upon Example 1, this example further refines the functions and application processes of the component technical requirements planning and definition module 20. It is understood that this module is not only a data definition tool, but also a bridge connecting the design and manufacturing ends.

[0060] Regarding the structured processing and correlation of final assembly technical requirements, when a final assembly process engineer needs to define technical requirements for a certain assembly task, he will use the component technical requirement planning and definition module 20. Suppose the task is to install a transponder device on a certain panel, the process engineer opens the integrated spacecraft final assembly model on the designer workstation 130 and locates the transponder and its installation position.

[0061] The process engineer first selects the installation interface for the transponder and the hatch panel. The system recognizes this as an area requiring surface treatment. The process engineer then calls the module's function to add a "cleaning" requirement. Instead of providing a simple text box, the system pops up a structured definition window containing the following fields: * Requirement ID: A unique identifier automatically generated by the system, such as "REQ-00781". * Associated Component ID: A unique identifier automatically filled in for the installation interface. * Requirement Type: Select from a preset list, such as "Surface Cleaning", "Torque", "Gap Measurement", "Resistance Measurement", "Adhesive Application", etc. Here, "Surface Cleaning" is selected. * Requirement Content: Associates a standard process specification document, such as the "General Procedure for Spacecraft Surface Cleaning GJB-CLEAN-01" linked on the document server. * Parameters: For cleaning requirements, there may be a "Cleanliness Level" field; select "Level A".

[0062] Next, the engineer selected the four mounting bolts used to secure the transponder. He selected these four bolts and added a "Torque" requirement for them in bulk. The Structured Definition window reappeared: * Requirement Type: Select "Torque". * Nominal Value: Enter "8.0". * Unit: Select "Nm" (Newton-meter). * Tolerance: Enter "±0.5". * Tool Requirement: Optional field, enter "Use a calibrated digital torque wrench".

[0063] In this way, unstructured information originally described in natural language on the process card, such as "wipe the installation surface clean with XXX cleaner" and "tighten the 4 M6 bolts to a torque of 8.0±0.5Nm", is transformed into structured data that can be understood and processed by the computer and is associated with specific components in the 3D model. This data is then stored in the database 110 of the central server 100.

[0064] In terms of the application and visualization of digital work instructions, these structured technical requirements truly demonstrate their value during the actual final assembly stage. An assembly technician is on-site in the workshop, holding a workshop tablet terminal 140. The technician logs into the system and receives the day's assembly tasks, such as "Install the transponder on panel A05." The system then downloads the relevant data from the central server 100.

[0065] On the screen of the workshop tablet terminal 140, the system is configured to visualize the components associated with structured data, providing corresponding digital work instructions to the assembly personnel. The specific display content and interaction process are as follows: 1. 3D Visualization Guidance: The screen highlights the A05 panel and the transponder model to be installed in 3D form, indicating their correct installation position and direction with animation or arrows. 2. Step-by-Step Instruction List: One side of the screen clearly lists the structured work steps automatically generated from the previously defined structured technical requirements: * Step 1: [Cleaning] Clean the installation surface. Click "Details" to directly open and read the document "General Procedure for Cleaning Spacecraft Surfaces GJB-CLEAN-01" on the tablet. After completion, the technician clicks the "Complete" button. * Step 2: [Installation] Install 4 M6 bolts (part number: HB-M6-20-Ti). The corresponding 4 bolts in the model will be highlighted and flashing. * Step 3: [Torque] Tighten the 4 M6 bolts. Requirement: 8.0 ± 0.5 Nm. 3. Data Acquisition and Closed Loop: For step 3, if the technician uses a smart digital torque wrench connected to the system, the actual applied torque value (e.g., "7.9 Nm") will be automatically transmitted to the tablet and recorded when tightening each bolt. If a regular wrench is used, the value must be entered manually. The technician confirms the tightening of each bolt by marking it on the corresponding entry. 4. Process Traceability and Quality Control: After completing all steps, the technician clicks "Task Completed." The system uploads all data from the entire operation, including the operator, start / end time, confirmation status of each step, and the collected actual torque value, back to the database 110 on the central server 100. This data constitutes part of the transponder's completion status, forming a valuable quality traceability record. If the tightening torque exceeds the tolerance, the system will immediately issue a warning and require the technician to confirm or report the anomaly, thus enabling real-time detection and handling of quality issues.

[0066] Through the process described in this embodiment, the technical solution of this application transforms abstract design and process requirements into digital work instructions that on-site assembly personnel can intuitively understand, accurately execute, and automatically record results. This not only greatly improves the standardization level and operational accuracy of assembly work, avoiding quality problems caused by misunderstanding or omission of technical requirements, but also provides an indispensable data foundation for constructing a spacecraft "digital twin" that precisely corresponds to the physical entity by collecting real manufacturing process data, providing historical evidence for subsequent on-orbit operation and maintenance, fault diagnosis, etc.

[0067] 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.

[0068] 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 spacecraft assembly design state integration construction system based on a three-dimensional model, characterized in that, include: The assembly status integrated display module is configured to aggregate layout elements from the spacecraft's overall architecture model based on multiple preset professional design architectures. It performs lightweight processing on these layout elements and integrates them into a unified overall assembly architecture. Simultaneously, it parses and uniformly manages the design information contained in the source design model. The component technical requirements planning and definition module is configured to inherit, extract and define product matching information and assembly technical requirements based on the overall assembly technical requirements information of each component of the spacecraft in the whole model environment.

2. The system according to claim 1, characterized in that, The multiple professional design architectures include: overall configuration layout architecture, structural assembly architecture, cable laying architecture, and thermal control design architecture.

3. The system according to claim 2, characterized in that: The overall configuration layout architecture includes at least one of the following: overall architecture design information, single-unit equipment layout design information, assembly direct component design information, and single-unit mounting fastener information; The structural assembly architecture includes at least one of the following: truss assembly design information, cabin panel assembly design information, and structural fastening design information.

4. The system according to claim 2, characterized in that: The cable laying structure includes at least one of the following: cable harness assembly, clamp bracket assembly, electrical connector assembly, and node data connection relationship; The thermal control design architecture includes at least one of the following: layout design information for heat pipes, heaters, coatings, thermistors, multilayers, and thermocouples.

5. The system according to claim 1, characterized in that, The method by which the integrated display module for final assembly status performs lightweight processing on the layout elements includes: simplifying the geometric shape of the layout elements by adopting a layout component shrinking envelope, while retaining their key engineering attributes.

6. The system according to claim 5, characterized in that, The key engineering attributes include at least one of the mounting base surface of the layout element, the connector coordinate system, or the pin definition.

7. The system according to claim 1, characterized in that, The component technical requirements planning and definition module is also configured to: process the final assembly technical requirements information into structured data and establish data association with the component elements in the overall final assembly architecture.

8. The system according to claim 7, characterized in that, The system is also configured to: visualize the component elements associated with structured data on a client device to provide assembly personnel with digital work instructions corresponding to the component elements.

9. The system according to claim 1, characterized in that, The design information is non-geometric attribute information, and the non-geometric attribute information includes at least one of the following: cable node data connection relationship and thermal control component number information.

10. A method for integrating and constructing the overall design state of a spacecraft based on a three-dimensional model, characterized in that, Includes the following steps: Based on multiple pre-defined professional design architectures, the layout elements in the overall spacecraft architecture model are aggregated; The layout elements are made lightweight; The processed layout elements are integrated into a unified overall assembly architecture, while the design information contained in the source design model is parsed and managed in a unified manner. Based on the assembly technical requirements of various components of the spacecraft, product matching information and assembly technical requirements are inherited, extracted and defined in the whole spacecraft model environment.

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