An intelligent digital satellite design scheduling system, method and medium

Abstract

The embodiment of the application discloses a kind of intelligent digital satellite design scheduling system, method and medium;The design scheduling system includes: for realizing satellite whole satellite design stage satellite design research and development system and as the resource database of bottom support;Wherein, the satellite design research and development system includes: whole satellite design module, the component design module corresponding to each subsystem of satellite;Resource database includes: whole satellite and the model database and archive database of satellite component, design resource database, process resource database.

Description

Technical Field

[0001] This invention relates to the field of digital satellite design technology, and in particular to an intelligent digital satellite design and scheduling system, method and medium. Background Technology

[0002] Currently, traditional satellite overall design schemes typically begin by setting an overall satellite specification based on specific satellite requirements. Subsequently, designers of various subsystems divide tasks and subsystem specifications according to the overall specification. Each subsystem has its internal selection logic and internal specification references. Designers in each subsystem department determine the preliminary selection version of each component model based on their respective focus on the specifications and through calculations. Subsequently, parameter transmission between different departments and subsystems is generally in document form or verbally, providing a parameter value. For example, the attitude and orbit control calculates a parameter and provides it to the power supply. If the power supply's calculation result does not meet the overall satellite power supply specifications, further communication and iteration with the attitude and orbit control subsystem design team are necessary. During the overall satellite component selection process, different subsystems are interconnected and iteratively linked. Simultaneously, during the preliminary design phase of the overall satellite, there are also interdependencies and sequential waiting processes among the various departments. For instance, without the output parameters from the attitude and orbit control, the power supply's work related to those parameters cannot proceed.

[0003] Therefore, the current satellite design process suffers from drawbacks such as sequential waiting, long design cycles, and low design efficiency. Summary of the Invention

[0004] In view of this, embodiments of the present invention aim to provide an intelligent digital satellite design and scheduling system, method, and medium; which can avoid serial waiting during the satellite design process, reduce the design cycle, and improve design efficiency.

[0005] The technical solution of this invention is implemented as follows:

[0006] In a first aspect, embodiments of the present invention provide an intelligent digital satellite design and scheduling system, the design and scheduling system comprising: a satellite design and development system for realizing the overall satellite design stage and a resource database as underlying support; wherein, the satellite design and development system comprises: an overall satellite design module and component design modules corresponding to each subsystem of the satellite; the resource database comprises: a model database and an archive database of the overall satellite and satellite components, a design resource database, and a process resource database;

[0007] The satellite design module is configured to query the satellite model database for a suitable satellite model based on the overall design requirements of the satellite to be manufactured; if so, the suitable satellite model and the corresponding archive data in the satellite archive database are transmitted to the satellite manufacturing system for manufacturing; otherwise, the overall requirements are broken down to obtain the target components of the satellite to be manufactured and distributed to the component design module accordingly.

[0008] The component design module is configured to combine other component model data and archive data related to the target component corresponding to this module in the component model database and archive database to perform subsystem design for the target component corresponding to this module, so as to obtain the target component model data and archive data corresponding to this module, and update the component model database and archive database.

[0009] The satellite design module is further configured to dynamically adjust the target component model data and archive data obtained from the design modules of each component according to the parameters of the whole satellite, so as to generate model data and archive data of the satellite to be manufactured; and to transmit the model data and archive data of the satellite to be manufactured to the satellite manufacturing system for manufacturing, and update the whole satellite model database and archive database.

[0010] Secondly, embodiments of the present invention provide an intelligent digital satellite design and scheduling method, the method comprising:

[0011] The satellite design module queries the satellite model database to see if a suitable satellite model exists, based on the overall design requirements of the satellite to be manufactured.

[0012] If so, the adapted whole satellite model and the corresponding archive data in the whole satellite archive database will be transmitted to the satellite manufacturing system for production.

[0013] Otherwise, the overall requirements are broken down to obtain the target components of the satellite to be produced and then distributed to the component design module accordingly;

[0014] The component design module combines the component model database and the archive database with other component model data and archive data related to the target component corresponding to this module to design the subsystem of the target component corresponding to this module, so as to obtain the target component model data and archive data corresponding to this module, and update the component model database and the archive database.

[0015] The overall satellite design module dynamically adjusts the target component model data and archive data obtained from the design modules of each component according to the parameters of the entire satellite, in order to generate model data and archive data of the satellite to be produced.

[0016] The model data and archive data of the satellite to be manufactured are transferred to the satellite manufacturing system for production, and the whole satellite model database and archive database are updated.

[0017] Thirdly, embodiments of the present invention provide a computer storage medium storing an intelligent digital satellite design and scheduling program. When the intelligent digital satellite design and scheduling program is executed by at least one processor, it implements the functions configured in each component of the intelligent digital satellite design and scheduling system described in the first aspect.

[0018] This invention provides an intelligent digital satellite design and scheduling system, method, and medium. By linking the underlying databases, it enables resource interaction and information sharing in the design process, thereby achieving intelligent and digital satellite design. This avoids serial waiting in certain subsystem design parts during the satellite design process, reduces the design cycle, and improves design efficiency. Attached Figure Description

[0019] Figure 1 A schematic diagram illustrating the composition of an intelligent digital satellite design and scheduling system provided in an embodiment of the present invention;

[0020] Figure 2 A schematic diagram of the architecture of the resource database provided in an embodiment of the present invention;

[0021] Figure 3 A schematic diagram illustrating another intelligent digital satellite design and scheduling system provided in an embodiment of the present invention;

[0022] Figure 4 A schematic diagram of the business logic of the power design module provided in an embodiment of the present invention;

[0023] Figure 5 This is a schematic diagram of the business logic of the attitude and trajectory control design module provided in an embodiment of the present invention;

[0024] Figure 6 This is a schematic diagram of the business logic of the structural thermal control design module provided in an embodiment of the present invention;

[0025] Figure 7 A detailed business logic flowchart of the intelligent digital satellite design and scheduling system provided in this embodiment of the invention;

[0026] Figure 8 A schematic diagram illustrating the composition of yet another intelligent digital satellite design and scheduling system provided in this embodiment of the invention;

[0027] Figure 9 This is a schematic diagram of an intelligent digital satellite design and scheduling method provided in an embodiment of the present invention. Detailed Implementation

[0028] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention.

[0029] Since the design process of each subsystem is an iterative network, in order to reduce the occurrence of serial waiting, this embodiment of the invention aims to achieve intelligent and digital satellite design by establishing connections between underlying databases to facilitate resource interaction and information sharing during the design process. This avoids serial waiting in certain subsystem design parts, reduces the design cycle, and improves design efficiency. Based on this, see [link to related documentation]. Figure 1 The present invention illustrates an intelligent digital satellite design and scheduling system 10 provided by an embodiment of the present invention. The design and scheduling system 10 includes: a satellite design and development system 11 for realizing the satellite whole-satellite design stage and a resource database 12 as the underlying support.

[0030] See also Figure 1 The satellite design and development system 11 includes: a whole satellite design module 111 and component design modules 112 corresponding to each subsystem of the satellite;

[0031] Resource database 12 includes: model database and archive database of the whole satellite and satellite components, design resource database, and process resource database;

[0032] The satellite design module 111 is configured to query the satellite model database for a suitable satellite model based on the overall design requirements of the satellite to be manufactured; if so, the suitable satellite model and the corresponding archive data in the satellite archive database are transmitted to the satellite manufacturing system for manufacturing; otherwise, the overall requirements are broken down to obtain the target components of the satellite to be manufactured and distributed to the component design module accordingly.

[0033] The component design module 112 is configured to combine other component model data and archive data related to the target component corresponding to this module in the component model database and archive database to perform subsystem design of the target component corresponding to this module, so as to obtain the target component model data and archive data corresponding to this module, and update the component model database and archive database.

[0034] The satellite design module 111 is further configured to dynamically adjust the target component model data and archive data obtained by each component design module according to the parameters of the whole satellite, so as to generate model data and archive data of the satellite to be manufactured; and to transmit the model data and archive data of the satellite to be manufactured to the satellite manufacturing system for manufacturing, and update the whole satellite model database and archive database.

[0035] For the aforementioned intelligent digital satellite design and scheduling system 10, combined with Figure 1 In some examples, resource database 12 includes: a model database and archive database of the whole satellite and satellite components, a design resource database, a process resource database, and in the specific implementation process, it may also include a protocol resource database and a test resource database.

[0036] Specifically, each component model or whole star model in the component model database or whole star model database is assigned an attribute set consisting of multiple feature attribute values. Each attribute in the attribute set describes a characteristic of the model. It should be noted that all data or information related to the model can be part of the model, and this data or information can be relatively complex and diverse in its forms. To maximize the inclusion of this model-related data and information and to facilitate its digitization, this embodiment of the invention sets each model (component model or whole star model) to have multiple attributes, each attribute value describing a characteristic of the model. Based on this, the attribute set formed by multiple attribute values ​​can provide a detailed and complete description of the specific model.

[0037] The component archive database or whole-star archive database is primarily used to store archival information derived from models and applicable to procurement and production. Therefore, the archival information in the component archive database or whole-star archive database corresponds to each component model or whole-star model in the component model database or whole-star model database. In some examples, the archival information corresponding to each component model or whole-star model in the component archive database or whole-star archive database can specifically include manufacturer information, pricing information, process information, and other content related to finance, supply chain, and manufacturing, in addition to the corresponding model information.

[0038] The design resource database is primarily used to integrate design resources used in the component and overall satellite design phases, such as images, CAD documents, and 3D model files. These design resources can exist in document format. As satellite design, production, and manufacturing continue, the resources in the database can be continuously expanded to accelerate the design efficiency of satellite components and the entire satellite system.

[0039] The process resource database includes the various process requirements that must be followed when processing and testing various parts during the manufacturing process. These process requirements can be stored in the form of various process documents and process specification texts.

[0040] The protocol resource database includes information on various protocols contained in or used by satellite components. This protocol information exists in text form and forms the basis for intra-satellite and inter-satellite communication.

[0041] The test resource database includes all test cases and test methods for components or the entire satellite during the production and testing phases. As satellite design, production, and manufacturing continue, the content of this test resource database can be continuously modified and enriched, accelerating satellite production efficiency and improving overall satellite reliability.

[0042] Based on the aforementioned types of resource databases 12, underlying data support can be provided for the satellite design process. Therefore, in some examples, the information flow and interaction between the databases demonstrate the architecture of resource database 12, such as... Figure 2 As shown in the diagram, specifically, the protocol resource database is designed to provide communication protocol information support for each component model in the component model database; the component model database and the whole satellite model database are designed to provide the data foundation for the archive information of the corresponding models in the component archive database and the whole satellite archive database, respectively; the design resource database is designed to provide support for the design resources involved in the models in the component model database and the whole satellite model database; and the process resource database and the test resource database are designed to provide support for the process information and test information involved in the component archive database and the whole satellite archive database, respectively.

[0043] Combining the composition and architecture of the resource database 12 described above, it provides underlying database support for resource interaction and information sharing in the satellite design process. Based on this support, during the satellite design and development system 11, by continuously updating the data in the corresponding database, designers can obtain the latest version of model data and archive data of relevant components and the entire satellite in a timely manner, thus eliminating the need for sequential waiting and connecting the entire process of satellite subsystem design and overall satellite design, thereby improving design efficiency.

[0044] Regarding the satellite design and development system 11, it should be noted that the whole satellite design module 111 is used to design the whole satellite model and generate relevant archive data. In the process of designing the whole satellite model, designers of each subsystem usually need to design the corresponding subsystem according to the different index information of the whole satellite. After the subsystem design is completed, the data is then summarized to form the whole satellite design model.

[0045] Therefore, based on the common types of on-board subsystems on a satellite, see [link to relevant documentation]. Figure 3The component design module 112 may include at least: a power design module 112-1 for the power supply subsystem, an attitude and trajectory control design module 112-2 for the attitude and trajectory control subsystem, a structural thermal control design module 112-3 for the structural thermal control subsystem, an integrated electronic design module 112-4 for the integrated electronic subsystem, and other component design modules 112-5 for other subsystems. Understandably, the design modules for different subsystems are used to design the selection of component models for their respective subsystems, and the specific design depends on the internal business of each subsystem design department.

[0046] for Figure 3 In some examples, the power supply design module 112-1 shown is configured as follows:

[0047] Based on the overall requirements decomposition, the satellite power parameters obtained, the satellite orbit parameters of the attitude and orbit control subsystem, and the structural and thermal parameters obtained from the structural thermal control design module, the power supply design calculation tools are used to perform simulation calculations to obtain the power supply component selection results, and power supply components that meet the selection results are selected from the component model library.

[0048] If the selected power supply component does not meet the overall satellite power parameter specifications, the selected power supply component parameters will be fed back to the structural thermal control design module to redesign the structural information and thermal parameter information, and iterative simulation calculations will continue to be performed in combination with the overall satellite power parameter specifications and satellite orbit parameter information until the final power supply component selection result meets the overall satellite power parameter specifications.

[0049] If the selected power supply component meets the overall satellite power parameters, the power supply component model is finalized based on the selected power supply component, and corresponding power supply component file data is generated. The component model database and file database are also updated. The finalized power supply component model and file data are then combined with the process information in the process resource library and sent to the Business Process Management (BPM) system for production. Finally, the required software requirements and communication protocols are transmitted to the onboard software design section based on the finalized power supply component model for onboard software design.

[0050] In the above example, specifically for the power supply subsystem design department, simulation calculations are performed using the computational toolset required for power supply component design based on the overall satellite power supply parameter indicators. The power supply design module 112-1 calculates some independent power supply parameter information, as well as power supply parameter information corresponding to tasks that are not interdependent with other subsystem departments. After the calculation is completed, it is determined whether the calculation results meet the overall satellite power supply parameter indicators. If they do, a power supply report can be directly generated. If not, iteration and adjustments are required based on the actual situation. More specifically, if the design and selection of power supply components depends on parameter information from other departments, designers in the power supply subsystem design department can consult the component selection and design results of other departments. They can directly obtain the necessary power supply result information through the underlying database and the corresponding design modules of other subsystem design departments before performing calculations. This eliminates the need for document-based or verbal information transfer. The interaction and iteration of parameter information with other subsystem design departments also rely on the underlying database and the corresponding design modules of other subsystem design departments, achieving information sharing. For example, a power supply designer can view the design results of the attitude and orbit control subsystem design department and ultimately determine the selection parameters and component model of the output power supply.

[0051] Based on the above specific content, combined with Figure 4 As shown, the business logic of power supply design module 112-1 includes:

[0052] First, we obtain the power parameters of the entire satellite. In fact, the required parameters of the entire satellite have already been imported into the satellite model library.

[0053] Next, the power supply department uses the satellite's overall power specifications and the satellite orbital parameters provided by the attitude and orbit control subsystem design department as input parameters to perform simulation calculations using the power supply design module 112-1. In addition, the input calculation parameters also need to include some structural information and thermal parameter information provided by the structural thermal control subsystem design department, such as the number and size of solar panels, solar cell array, thermal parameters, and overall satellite mass.

[0054] Then, the power supply design module 112-1 combines the calculation toolset formed by the calculation methods required for power supply design to finally obtain the selection results of power supply components;

[0055] If the calculation results do not meet the corresponding overall satellite power specifications, the parameters between different departments can be iterated to ultimately determine the component model information of the power supply. The power supply designer selects the power supply component model from the component model library, connects the underlying libraries, and sends the finalized power supply component model and archive data, along with the process information in the process resource library, to the Business Process Management (BPM) system to guide the ordering and production of the power supply components. At the same time, reports can be generated, and the software requirements and communication protocols needed for the selection results can be transmitted to the onboard software department.

[0056] for Figure 3 In some examples, the attitude and trajectory control design module 112-2 shown in the design module is configured as follows:

[0057] Based on the attitude and orbit control parameters and accuracy information of the entire satellite, and combined with the structural parameters of the entire satellite obtained by the structural thermal control design module, simulation calculations are performed using a calculation toolset adapted to attitude and orbit control design to obtain the selection results of attitude and orbit control components, and attitude and orbit control components that meet the selection results are selected from the component model library.

[0058] The selected attitude and orbit control components are simulated to determine whether they meet the attitude and orbit control parameters of the entire satellite.

[0059] If not, the system feeds back to the structural thermal control design module to redesign the overall satellite structural parameters and re-performs the simulation calculations until the final selection results of the attitude and orbit control components meet the attitude and orbit control parameter indicators of the entire satellite.

[0060] If the conditions are met, the finalized attitude and trajectory control component model and archive data will be updated in the component's model database and archive database; and, combined with the process information in the process resource library, the process information will be sent to the Business Process Management (BPM) system for production, and a report on the attitude and trajectory control model will be output.

[0061] For the example above, combined Figure 5 The design logic flow shown includes the business logic of attitude and trajectory control design module 112-2, which includes:

[0062] First, the attitude and orbit control designers used the attitude and orbit control design module 112-2 to perform simulation calculations based on the overall satellite's parameter information and accuracy information, as well as the design results from the structural thermal control subsystem design department, mainly including mass, matrix, and other parameter information, through a calculation toolset adapted to the attitude and orbit control design; and initially determined the component model information selected by the attitude and orbit control department.

[0063] Then, component simulation is performed on the selected component model. If the attitude and orbit control parameters set for the whole satellite are not met, the model is iterated and modified again with other subsystem design departments until the parameters are met. After that, the component selection is determined, and the process information in the process resource library is sent to the Business Process Management (BPM) system for production, and a report on the attitude and orbit control model is output.

[0064] for Figure 3 In some examples of the design modules shown, the structural thermal control design module 112-3 is configured as follows:

[0065] Based on the structural indicators of the entire satellite, the components in the component model library are laid out as a whole.

[0066] Based on the overall layout results, specific structural components are designed using design resources in the design resource database, material information in the material database, and a set of calculation tools adapted to structural component design.

[0067] The designed structural components are subjected to mechanical simulation, and the structural components are finalized after the simulation.

[0068] Qualitative structural components are used as the structural design results, and specific component BOMs, engineering drawings, structural component model data, and overall satellite structural parameters are output based on the structural design results. Among them, the component BOMs and engineering drawings are provided to the BPM system; the overall satellite structural parameters are used to provide to the attitude and orbit control design module for the design of attitude and orbit control components.

[0069] Thermal simulation and thermal experiments were conducted using structural model data and satellite orbital parameter information of the attitude and orbit control subsystem obtained from the design.

[0070] The experimental results are compared with the actual operating data of the satellite in orbit. If the experimental results meet the thermal parameter indicators, the design results of the thermal control components are output as process documents and production drawings and provided to the BPM system, and a design report of the thermal control components is generated.

[0071] Regarding the above example, it should be noted that structural thermal control design involves not only thermal and mechanical simulations but also the information processing of 3D models and drawings. Therefore, the design logic of this subsystem is more complex than... Figure 4 and Figure 5 Slightly more complex, such as Figure 6 The design logic flow shown includes the business logic of the structural thermal control design module 112-3, which includes:

[0072] First, obtain the relevant structural information of the entire satellite, and then make a reasonable layout.

[0073] After the overall layout is in place, the next step is to design the specific structural components. In designing the structural components, it is necessary to obtain specific information from the material library and the design resource library. However, based on the aforementioned content, the databases have been connected, so the required information can be obtained directly.

[0074] Next, mechanical simulation is performed. Once the simulation meets the requirements, the structural components can be finalized. Specifically, during the finalization of structural components, the following can be output: Bill of Materials (BOM), engineering drawings (part drawings, 3D model drawings, whole-plane assembly drawings, etc.), structural model files, and whole-plane parameters (mass, inertia, installation matrix, etc.). It is worth noting that the obtained whole-plane parameter information can be provided to the attitude and orbit control system for calculation.

[0075] Simultaneously, thermal simulation and thermal experiments were conducted using structural model data and satellite orbital parameter information of the attitude and orbit control subsystem obtained from the design.

[0076] Finally, the experimental results are compared with the actual operating data of the satellite in orbit. If the experimental results meet the thermal parameter indicators, the design results of the thermal control components are output as process documents and production drawings and provided to the BPM system, and a design report of the thermal control components is generated.

[0077] for Figure 3 In some examples, the electronic design module 112-4 and other component design modules 112-5 shown in the design modules are configured as follows:

[0078] Based on the overall satellite's specifications for electronic components and other components, as well as the design results of other related components, simulation calculations are performed using the corresponding computing tools to design and obtain the corresponding electronic components and other components.

[0079] If the design results do not meet the target parameters, the simulation calculation is repeated through iterative adjustments until the target parameters are met.

[0080] When the design results meet the target parameters, the finalized electronic components and other component models, as well as the archival data, will be updated in the component model database and archival database.

[0081] Specifically, in the above example, based on the detailed description of the example above, the business logic of the electronic design module 112-4 related to the comprehensive electronic subsystem and the other component design modules 112-5 corresponding to the satellite subsystem can be that designers from different departments can make preliminary component model selections based on their respective subsystem analyses.

[0082] Understandably, the aforementioned component design modules 112 can support real-time operation by multiple people in multiple locations. Designers from different departments can perform preliminary component model selection operations through the design modules corresponding to their respective subsystems to prepare for the design of the entire satellite.

[0083] It should be noted that after completing the component selection design of each subsystem using the component design module 112 in the above example, the designers use the whole satellite design module 111 to perform whole satellite modeling using the selection results of each subsystem, and calculate the whole satellite attribute parameters based on the attribute information of each subsystem component model. If the parameters do not meet the overall design requirements, the reasons for the discrepancy can be fed back to the design section of each subsystem, and adjustments can be made to the component selection and design through the corresponding component design module.

[0084] In conjunction with the aforementioned technical solutions, during the specific implementation process, based on Figure 1 as well as Figure 3 The detailed business logic flow of the design scheduling system 10 shown is as follows: Figure 7 As shown, it includes:

[0085] After receiving the satellite production task, the whole satellite design module 111 uses the overall design requirements of the satellite to be produced to query the whole satellite model database in the satellite resource database 12 to see if there is a suitable whole satellite model.

[0086] If found, the corresponding satellite model and archive data will be used to generate component archive data and satellite archive data for the satellite to be manufactured, and then transmitted to the satellite manufacturing system. Understandably, the archive data may include the product's bill of materials (BOM) and process information, so that the satellite manufacturing system can produce and assemble the satellite based on the received archive data.

[0087] If not, the overall design requirements will be broken down to obtain the components that fulfill the overall design requirements of the entire satellite, such as... Figure 7 As shown in the dashed box, the components that can be disassembled include the attitude and orbit control subsystem, the power supply subsystem, the structural components, the thermal control subsystem, and the integrated electronic subsystem. These disassembled components are distributed to various design departments for corresponding design. In detail, each design department can use the aforementioned corresponding component design module 112 to perform parameter calculations on the corresponding components based on the calculation software toolset adapted to its own design, and complete the selection of each component based on the aforementioned technical solution, thus clarifying the required component information.

[0088] After obtaining the required component information, for each component, a query is performed in satellite resource database 12 to determine if a matching component model exists:

[0089] If a compatible component model exists, it is transmitted to the chief designer, and it is further determined whether a corresponding complete satellite model exists. If a corresponding complete satellite model exists, the corresponding complete satellite model is updated according to the required component information, and the corresponding complete satellite file data is generated. Then, the file data corresponding to the compatible component model is transmitted to the satellite production and manufacturing subsystem 13 for production and assembly. Otherwise, a new complete satellite model is established.

[0090] If a suitable component model does not exist, the corresponding design department will construct the component model and generate the corresponding archive data based on the component information. Understandably, the design department can iteratively construct the component model and update the component model database and component archive database in resource database 12 with the constructed component model and corresponding archive data. It should be noted that during the iterative generation of the component model, the design resource library and process resource library will also be iteratively updated accordingly.

[0091] Once the chief designer has collected all component models for the entire satellite, an initial satellite model is constructed. Based on this initial satellite model, various design departments work together to iteratively update the model, ultimately generating a satellite model that meets the overall design requirements. Understandably, the final satellite model and its corresponding archive data will also be transmitted to the satellite manufacturing system for production and assembly, and can also be stored in the corresponding database in resource database 12. Furthermore, the design resource library and process resource library will be iteratively updated during the generation of the satellite model.

[0092] Based on the aforementioned technical solutions and examples, see some implementation methods. Figure 8 The design scheduling system 10 also includes a digital twin display system 13, which is configured as follows:

[0093] The system utilizes a component model database to present the finalized design of subsystem components in 3D and displays the generated complete satellite model; and,

[0094] The components in the displayed subsystems that do not meet the corresponding index parameters of the overall design requirements will be marked to prompt the designers of the corresponding subsystems to redesign the components.

[0095] Based on the above technical solutions, it should be noted that as the whole satellite model library and whole satellite archive are continuously updated and accumulated, when it is necessary to design similar satellite models in the future, the archives of all component model information used in the previously designed satellites can be retrieved. By modifying some models, a new satellite design scheme can be formed. After retrieving the whole satellite archive data, the supply chain library information of all models used and the component entity library information of the assembly center can be obtained, realizing the dynamic modeling and reuse of satellite archive information. This will greatly improve the efficiency of batch satellite design, guide satellite production and manufacturing, shorten the satellite design cycle, and improve the efficiency of batch satellite design.

[0096] Based on the design of the underlying whole satellite model database and archive database, each satellite launched or designed is used as an organizational process asset. When designing a new similar satellite, it can be selected from the satellite model library and archive database, which simplifies the satellite design process and shortens the satellite design period. This is especially true for batch satellite design, which saves even more time. If there is no similar satellite, it can be redesigned according to the aforementioned scheme and saved and updated in the resource database, thus forming an organizational accumulation process, which also includes the accumulation of experience and processes.

[0097] Understandably, the components in this embodiment can be integrated into one processing unit, or each unit can exist physically separately, or two or more units can be integrated into one unit. The integrated unit can be implemented in hardware or as a software functional module.

[0098] If the integrated unit is implemented as a software functional module and not sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of this embodiment, in essence, or the part that contributes to the prior art, or all or part of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) or processor to execute all or part of the steps of the method described in this embodiment. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, or optical disks.

[0099] Therefore, this embodiment provides a computer storage medium storing an intelligent digital satellite design and scheduling program. When the intelligent digital satellite design and scheduling program is executed by at least one processor, it implements the functions configured in each component of the intelligent digital satellite design and scheduling system described in the foregoing technical solution.

[0100] Based on the same inventive concept as the aforementioned technical solution, see [link to inventive concept]. Figure 9 This illustrates an intelligent digital satellite design and scheduling method provided by an embodiment of the present invention. This method can be applied to the aforementioned intelligent digital satellite design and scheduling system 10, and may include:

[0101] S901: The whole satellite design module queries the whole satellite model database to see if there is a suitable whole satellite model based on the overall design requirements of the satellite to be produced;

[0102] S902: If so, the adapted whole satellite model and the corresponding archive data in the whole satellite archive database will be transmitted to the satellite manufacturing system for production.

[0103] S903: Otherwise, the overall requirements are broken down to obtain the target components of the satellite to be produced and then distributed to the component design module accordingly;

[0104] S904: The component design module combines the component model database and the archive database with other component model data and archive data related to the target component corresponding to this module to design the subsystem of the target component corresponding to this module, so as to obtain the target component model data and archive data corresponding to this module, and update the component model database and the archive database.

[0105] S905: The overall satellite design module dynamically adjusts the target component model data and archive data obtained from the design modules of each component according to the parameters of the entire satellite to generate model data and archive data of the satellite to be produced.

[0106] S906: Transmits the model data and archive data of the satellite to be manufactured to the satellite manufacturing system for manufacturing, and updates the whole satellite model database and archive database.

[0107] Understandably, the above-described exemplary technical solutions for intelligent digital satellite design and scheduling methods,

[0108] Since the technical solution of the aforementioned intelligent digital satellite design and scheduling system 10 belongs to the same concept, the details of the intelligent digital satellite design and scheduling method not described in detail above are omitted.

[0109] For details, please refer to the description of the technical solution of the aforementioned intelligent digital satellite design and scheduling system 10. This embodiment of the invention will not elaborate further.

[0110] It should be noted that the technical solutions described in the embodiments of the present invention can be combined arbitrarily without conflict.

[0111] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited to this.

[0112] Therefore, any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in this invention should be included within the protection scope of this invention. Thus, the protection scope of this invention should be determined by the scope of the claims.

Claims

1. An intelligent digital satellite design and scheduling system, characterized in that, The design and scheduling system includes: a satellite design and development system for realizing the overall satellite design phase and a resource database as underlying support; wherein, the satellite design and development system includes: an overall satellite design module and component design modules corresponding to each subsystem of the satellite; the resource database includes: a model database and archive database of the entire satellite and its components, a design resource database, a process resource database, a protocol resource database, and test resource data; the protocol resource database is used to provide communication protocol information support for each component model in the component model database; the component model database and the overall satellite model database provide the data foundation for the archive information of the corresponding models in the component archive database and the overall satellite archive database, respectively; the design resource database is used to support the design resources involved in the models in the component model database and the overall satellite model database; the process resource database and the test resource database provide support for the process information and test information involved in the component archive database and the overall satellite archive database, respectively; The satellite design module is configured to query the satellite model database for a suitable satellite model based on the overall design requirements of the satellite to be manufactured; if so, the suitable satellite model and the corresponding archive data in the satellite archive database are transmitted to the satellite manufacturing system for manufacturing; otherwise, the overall requirements are broken down to obtain the target components of the satellite to be manufactured and distributed to the component design module accordingly. The component design module is configured to, after obtaining the component information required by the target component corresponding to this module, query the resource database to see if there is a component model that matches the target component; if there is a matching component model, the matching component model is transmitted to the chief designer, and it is further determined whether there is a corresponding whole satellite model for the matching component model; if there is no matching component model, the subsystem design of the target component corresponding to this module is carried out by combining the component model database and the archive database with other component model data and archive data related to the target component corresponding to this module, so as to obtain the target component model data and archive data corresponding to this module, and update the component model database and the archive database. The satellite design module is further configured to determine whether a corresponding satellite model exists for the adapted component model; if the corresponding satellite model exists, the module updates the corresponding satellite model according to the component information required by the target component to generate model data and archive data for the satellite to be manufactured; if the corresponding satellite model does not exist, the module dynamically adjusts the target component model data and archive data obtained by each component design module according to the parameters of the satellite to generate model data and archive data for the satellite to be manufactured; and transmits the model data and archive data of the satellite to be manufactured to the satellite manufacturing system for manufacturing, and updates the satellite model database and archive database.

2. The design and scheduling system according to claim 1, characterized in that, The component design module includes at least: a power design module for the power supply subsystem, an attitude and trajectory control design module for the attitude and trajectory control subsystem, a structural thermal control design module for the structural thermal control subsystem, an integrated electronic design module for the integrated electronic subsystem, and other component design modules for other subsystems.

3. The design and scheduling system according to claim 2, characterized in that, The power supply design module is configured as follows: Based on the overall requirements decomposition, the satellite power parameters obtained, the satellite orbit parameters of the attitude and orbit control subsystem, and the structural and thermal parameters obtained from the structural thermal control design module, the power supply design calculation tools are used to perform simulation calculations to obtain the power supply component selection results, and power supply components that meet the selection results are selected from the component model library. If the selected power supply component does not meet the overall satellite power parameter specifications, the selected power supply component parameters will be fed back to the structural thermal control design module to redesign the structural information and thermal parameter information, and iterative simulation calculations will continue to be performed in combination with the overall satellite power parameter specifications and satellite orbit parameter information until the final power supply component selection result meets the overall satellite power parameter specifications. If the selected power supply component meets the overall satellite power parameters, the power supply component model is finalized based on the selected power supply component, and corresponding power supply component file data is generated. The component model database and file database are also updated. The finalized power supply component model and file data are then combined with the process information in the process resource library and sent to the Business Process Management (BPM) system for production. Finally, the required software requirements and communication protocols are transmitted to the onboard software design section based on the finalized power supply component model for onboard software design.

4. The design and scheduling system according to claim 2, characterized in that, The attitude and trajectory control design module is configured as follows: Based on the attitude and orbit control parameters and accuracy information of the entire satellite, and combined with the structural parameters of the entire satellite obtained by the structural thermal control design module, simulation calculations are performed using a calculation toolset adapted to attitude and orbit control design to obtain the selection results of attitude and orbit control components, and attitude and orbit control components that meet the selection results are selected from the component model library. The selected attitude and orbit control components will be simulated to determine whether they meet the attitude and orbit control parameters of the entire satellite. If not, the system feeds back to the structural thermal control design module to redesign the overall satellite structural parameters and re-performs the simulation calculations until the final selection results of the attitude and orbit control components meet the attitude and orbit control parameter indicators of the entire satellite. If the conditions are met, the finalized attitude and trajectory control component model and archive data will be updated in the component's model database and archive database; and, combined with the process information in the process resource library, the process information will be sent to the Business Process Management (BPM) system for production, and a report on the attitude and trajectory control model will be output.

5. The design and scheduling system according to claim 2, characterized in that, The structural thermal control design module is configured as follows: Based on the structural indicators of the entire satellite, the components in the component model library are laid out as a whole. Based on the overall layout results, specific structural components are designed using design resources in the design resource database, material information in the material database, and a set of calculation tools adapted to structural component design. The designed structural components are subjected to mechanical simulation, and the structural components are finalized after the simulation. Qualitative structural components are used as the structural design results, and specific component BOMs, engineering drawings, structural component model data, and overall satellite structural parameters are output based on the structural design results. Among them, the component BOMs and engineering drawings are provided to the BPM system; the overall satellite structural parameters are used to provide to the attitude and orbit control design module for the design of attitude and orbit control components. Thermal simulation and thermal experiments were conducted using structural model data and satellite orbital parameter information of the attitude and orbit control subsystem obtained from the design. The experimental results are compared with the actual operating data of the satellite in orbit. If the experimental results meet the thermal parameter indicators, the design results of the thermal control components are output as process documents and production drawings and provided to the BPM system, and a design report of the thermal control components is generated.

6. The design and scheduling system according to claim 2, characterized in that, The electronic design module and other component design modules are all configured as follows: Based on the overall satellite's specifications for electronic components and other components, as well as the design results of other related components, simulation calculations are performed using the corresponding computing tools to design and obtain the corresponding electronic components and other components. If the design results do not meet the target parameters, the simulation calculation is repeated through iterative adjustments until the target parameters are met. When the design results meet the target parameters, the finalized electronic components and other component models, as well as the archival data, will be updated in the component model database and archival database.

7. The design and scheduling system according to claim 1, characterized in that, The entire satellite design module is further configured as follows: The entire satellite is modeled using the selection results of each subsystem, and the overall satellite attribute parameters are calculated based on the attribute information of each subsystem component model. If these parameters do not meet the overall design requirements, the reasons for the discrepancy can be fed back to the design sections of each subsystem, and adjustments to component selection and design can be made through the corresponding component design modules.

8. The design scheduling system according to any one of claims 1 to 7, characterized in that, The design scheduling system also includes: a digital twin display system, configured as follows: The system utilizes a component model database to present the finalized design of subsystem components in 3D and displays the generated complete satellite model; and, The components in the displayed subsystems that do not meet the corresponding index parameters of the overall design requirements will be marked to prompt the designers of the corresponding subsystems to redesign the components.

9. An intelligent digital satellite design and scheduling method, characterized in that, The method includes: The satellite design module queries the satellite model database to see if a suitable satellite model exists, based on the overall design requirements of the satellite to be manufactured. If so, the adapted whole satellite model and the corresponding archive data in the whole satellite archive database will be transmitted to the satellite manufacturing system for production. Otherwise, the overall requirements are broken down to obtain the target components of the satellite to be produced and then distributed to the component design module accordingly; After obtaining the component information required for the target component corresponding to this module, the component design module queries the resource database to see if there is a component model that matches the target component. If a matching component model exists, it is transmitted to the chief designer, and it is further determined whether the matching component model has a corresponding whole satellite model. If no matching component model exists, the module combines the component model database and the archive database with other component model data and archive data related to the target component corresponding to this module to perform subsystem design for the target component corresponding to this module, so as to obtain the target component model data and archive data corresponding to this module, and update the component model database and the archive database. The satellite design module determines whether a corresponding satellite model exists for each compatible component model. If a corresponding satellite model exists, the module updates the corresponding satellite model based on the component information required by the target component to generate model data and archive data for the satellite to be manufactured. If no corresponding satellite model exists, the module dynamically adjusts the target component model data and archive data obtained by each component design module according to the parameters of the satellite to generate model data and archive data for the satellite to be manufactured. The model data and archive data of the satellite to be manufactured are transferred to the satellite manufacturing system for production, and the whole satellite model database and archive database are updated.

10. A computer storage medium, characterized in that, The computer storage medium stores an intelligent digital satellite design and scheduling program, which, when executed by at least one processor, implements the functions configured in each component of the intelligent digital satellite design and scheduling system according to any one of claims 1 to 8.

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