General satellite platform digitization design method and device

Abstract

The application discloses a general satellite platform digital design method and device, and belongs to the technical field of spaceflight. The method comprises the following steps: obtaining a design requirement text, analyzing the design requirement text, determining a subsystem corresponding to the design requirement text and requirement indexes of each subsystem, matching the requirement indexes of the subsystem with a type spectrum library corresponding to the subsystem for each subsystem corresponding to the design requirement text, obtaining a single machine selection result of the subsystem, integrating the single machine selection results of each subsystem corresponding to the design requirement text, obtaining one or more satellite platform design schemes, simulating the one or more satellite platform design schemes, and outputting the satellite platform design schemes passing the simulation. The method can adapt to the adaptation requirements of various types of loads, reduce the satellite design cost, shorten the satellite design cycle, adapt to the requirements of large-scale production, and provide technical support for the deployment of large-scale constellations.

Description

Technical Field

[0001] This application belongs to the field of aerospace technology, specifically relating to a digital design method and apparatus for a general-purpose satellite platform. Background Technology

[0002] With the development of aerospace technology, the trend of large-scale, systematic and low-cost development of satellite constellation construction is becoming increasingly prominent. With the arrival of the "singularity" of the explosion of giant constellations, how to break through the customization barrier and carry out satellite digital rapid design technology based on the standardization of the interfaces of various satellite single system has become a research hotspot.

[0003] The traditional satellite design process involves the overall designer breaking down technical specifications based on user requirements, initially determining the satellite design and the technical specifications of its subsystems. Subsystem designers then conduct simulation verification, revision, readjustment, and re-simulation. Each subsystem designer's design relies on the overall designer's specification breakdown, and each subsystem designs collaboratively based on its own area of ​​expertise. Subsystem designers are required to perform preliminary simulations and specification satisfaction tests on each subsystem's design. However, due to the coupling relationships between subsystems, a change in one key parameter often leads to significant adjustments to other related specifications, necessitating a redesign of the subsystem. The collaborative iterative updates of subsystem technical specifications are inefficient, and each subsystem lacks the ability to make independent design decisions. This results in a long satellite design iteration cycle, slow specification optimization, and low efficiency, failing to meet the demands of modern satellite development with its high integration and short development cycles. Summary of the Invention

[0004] To solve the above-mentioned technical problems, or at least partially solve them, embodiments of this application provide a digital design method and apparatus for a general satellite platform.

[0005] In a first aspect, embodiments of this application provide a general satellite platform digital design method, including: Obtain the design requirement text, parse the design requirement text, and determine the subsystems corresponding to the design requirement text and the requirement indicators of each subsystem; For each subsystem corresponding to the design requirement text, the requirement indicators of the subsystem are matched with the corresponding model library to obtain the single-unit selection result of the subsystem; the model library includes one or more of the following: product size information, envelope information, interface information, data interface performance indicators, reliability information, and cost information; By integrating the single-unit selection results of each subsystem corresponding to the design requirements text, one or more satellite platform design schemes are obtained; Simulations are performed on the design schemes of the one or more satellite platforms to optimize them. Output the satellite platform design scheme obtained through the simulation.

[0006] Optionally, parsing the design requirement text to determine the subsystems corresponding to the design requirement text and the requirement indicators of each subsystem includes: parsing the design requirement text to determine load requirement indicators, wherein the load requirement indicators include one or more of the following: load type, load operating mode, power consumption, weight, and data volume; and parsing the load requirement indicators according to the subsystem performance indicators to determine the subsystems corresponding to the design requirement text and the requirement indicators of each subsystem.

[0007] Optionally, the method further includes: for each subsystem, determining whether the requirement indicators of the subsystem meet the corresponding rationality requirements; if the requirement indicators of the subsystem do not meet the corresponding rationality requirements, re-parseing the design requirement text to determine the requirement indicators of the subsystem.

[0008] Optionally, the subsystems corresponding to the design requirements text include one or more of the following: structural mechanism subsystem, attitude and orbit control subsystem, power supply subsystem, integrated electronic subsystem, measurement and control data transmission subsystem, thermal control subsystem, and propulsion subsystem; For each subsystem corresponding to the design requirement text, the requirement indicators of the subsystem are matched with the corresponding model library to obtain the single-machine selection result of the subsystem, including: In response to the subsystems corresponding to the design requirements text, including the attitude and orbit control subsystem, integrated electronic subsystem, measurement and control data transmission subsystem, and / or propulsion subsystem, the requirement indicators of the attitude and orbit control subsystem, integrated electronic subsystem, measurement and control data transmission subsystem, and / or propulsion subsystem are matched with the corresponding type library to obtain the single-unit selection results of the attitude and orbit control subsystem, integrated electronic subsystem, measurement and control data transmission subsystem, and / or propulsion subsystem; In response to the subsystems corresponding to the design requirements text, including the power supply subsystem, the single-unit selection results of the attitude and orbit control subsystem, integrated electronic subsystem, measurement and control data transmission subsystem and / or propulsion subsystem, as well as the requirements indicators of the power supply subsystem, are determined from the type library corresponding to the power supply subsystem. In response to the subsystems corresponding to the design requirements text, including the structural mechanism subsystem and / or thermal control subsystem, the individual unit selection results of the structural mechanism subsystem and / or thermal control subsystem are determined from the model library corresponding to the structural mechanism subsystem and / or thermal control subsystem based on the unit selection results of the attitude and orbit control subsystem, integrated electronic subsystem, measurement and control data transmission subsystem, propulsion subsystem and / or power supply subsystem.

[0009] Optionally, the unit selection results of each subsystem corresponding to the design requirements text can be integrated to obtain one or more satellite platform design schemes, including: determining the frame structure selection results of the satellite platform based on the satellite unit layout design requirements of the largest installation contact surface; and obtaining one or more satellite platform design schemes based on the frame structure selection results of the satellite platform, the unit selection results of each subsystem corresponding to the design requirements text, and a multi-objective genetic algorithm.

[0010] Optionally, before simulating the one or more satellite platform design schemes, the method further includes: performing an overall verification on the one or more satellite platform design schemes; if the overall verification of the one or more satellite platform design schemes fails, re-selecting subsystems in the one or more satellite platform design schemes that do not meet the overall verification requirements, until the one or more satellite platform design schemes pass the overall verification.

[0011] Optionally, the simulation of the one or more satellite platform design schemes includes: for each satellite platform design scheme, performing satellite mechanical response simulation based on load mechanical response conditions; if the result of the satellite mechanical response simulation of the satellite platform design scheme meets a first requirement, performing satellite thermal analysis simulation of the satellite platform design scheme; and if the result of the satellite thermal analysis simulation of the satellite platform design scheme meets a second condition, performing combined mechanical and thermal simulation of the satellite platform design scheme.

[0012] Optionally, the simulation of the one or more satellite platform design schemes includes: If the simulation results of the satellite mechanical response of the satellite platform design scheme do not meet the first requirement, the structural mechanism subsystem of the satellite platform design scheme shall be optimized according to the preset first optimization strategy; or, If the satellite thermal analysis simulation results of the satellite platform design scheme do not meet the second condition, the thermal control subsystem of the satellite platform design scheme shall be optimized according to the preset second optimization strategy; or, If the results of the combined mechanical and thermal simulation of the satellite platform design scheme do not meet the third condition, the structural mechanism subsystem and thermal control subsystem of the satellite platform design scheme are jointly optimized according to the preset third optimization strategy.

[0013] Optionally, the method further includes: constructing a knowledge base, the knowledge base including one or more of the following: a parsing model, a matching model, a rationality verification model, an overall verification model, and an optimization model; The analytical model is used to parse the design requirement text and determine the subsystems corresponding to the design requirement text and the requirement indicators of each subsystem. The matching model is used to match the requirement indicators of the subsystem with the model library corresponding to the subsystem to obtain the single-unit selection result of the subsystem; The rationality verification model is used to determine whether the demand indicators of the subsystem meet the rationality requirements corresponding to the subsystem. The overall verification model is used to perform an overall verification of the satellite platform design scheme obtained after the individual selection results of each subsystem corresponding to the integrated design requirements text. The optimization model includes multiple optimization strategies for optimizing satellite platform design schemes where simulation results do not meet requirements.

[0014] Secondly, embodiments of this application provide a digital design apparatus for a general-purpose satellite platform, comprising: The parsing module is used to obtain the design requirement text, parse the design requirement text, and determine the subsystems corresponding to the design requirement text and the requirement indicators of each subsystem. The matching module is used to match the requirement indicators of each subsystem corresponding to the design requirement text with the model library corresponding to the subsystem to obtain the single-unit selection result of the subsystem; the model library includes one or more of the following: product size information, envelope information, interface information, data interface performance indicators, reliability information and cost information; The integration module is used to integrate the single-unit selection results of each subsystem corresponding to the design requirements text to obtain one or more satellite platform design schemes. The simulation module is used to simulate the design schemes of the one or more satellite platforms in order to optimize the design schemes of the one or more satellite platforms. The output module is used to output the satellite platform design scheme obtained through the simulation.

[0015] Optionally, the parsing module is further configured to: parse the design requirement text to determine load requirement indicators, wherein the load requirement indicators include one or more of the following: load type, load operating mode, power consumption, weight, and data volume; and parse the load requirement indicators according to the subsystem performance indicators to determine the subsystems corresponding to the design requirement text and the requirement indicators of each subsystem.

[0016] Optionally, the device further includes a first verification module, configured to: for each subsystem, determine whether the requirement indicators of the subsystem meet the corresponding rationality requirements of the subsystem; the matching module is further configured to, when the requirement indicators of the subsystem do not meet the corresponding rationality requirements of the subsystem, re-parse the design requirement text to determine the requirement indicators of the subsystem.

[0017] Optionally, the subsystems corresponding to the design requirements text include one or more of the following: structural mechanism subsystem, attitude and orbit control subsystem, power supply subsystem, integrated electronic subsystem, measurement and control data transmission subsystem, thermal control subsystem, and propulsion subsystem; The matching module is further configured to: in response to the subsystems corresponding to the design requirement text including an attitude and orbit control subsystem, an integrated electronic subsystem, a measurement and control data transmission subsystem, and / or a propulsion subsystem, match the requirement indicators of the attitude and orbit control subsystem, the integrated electronic subsystem, the measurement and control data transmission subsystem, and / or the propulsion subsystem with the corresponding model library to obtain the single-unit selection results of the attitude and orbit control subsystem, the integrated electronic subsystem, the measurement and control data transmission subsystem, and / or the propulsion subsystem; and in response to the subsystems corresponding to the design requirement text including a power supply subsystem, match the requirement indicators of the attitude and orbit control subsystem, the integrated electronic subsystem, the measurement and control data transmission subsystem, and / or the propulsion subsystem with the corresponding model library to obtain the single-unit selection results of the attitude and orbit control subsystem, the integrated electronic subsystem, the measurement and control data transmission subsystem, and / or the propulsion subsystem. Based on the unit selection results of the transmission subsystem and / or propulsion subsystem and the requirement indicators of the power supply subsystem, the unit selection results of the power supply subsystem are determined from the type library corresponding to the power supply subsystem; in response to the subsystems corresponding to the design requirement text, including the structural mechanism subsystem and / or thermal control subsystem, based on the unit selection results of the attitude and orbit control subsystem, integrated electronic subsystem, telemetry and data transmission subsystem, propulsion subsystem and / or power supply subsystem, the unit selection results of the structural mechanism subsystem and / or thermal control subsystem are determined from the type library corresponding to the structural mechanism subsystem and / or thermal control subsystem.

[0018] Optionally, the integration module is further configured to: determine the satellite platform frame structure selection result based on the satellite single-unit layout design requirements of the largest installation contact surface; and obtain one or more satellite platform design schemes based on the satellite platform frame structure selection result, the single-unit selection results of each subsystem corresponding to the design requirement text, and a multi-objective genetic algorithm.

[0019] Optionally, the device further includes a second verification module, used to: perform an overall verification of the one or more satellite platform design schemes; the matching module is also used to, if the overall verification of the one or more satellite platform design schemes fails, reselect subsystems in the one or more satellite platform design schemes that do not meet the overall verification requirements, until the one or more satellite platform design schemes pass the overall verification.

[0020] Optionally, the simulation module is further configured to: perform satellite mechanical response simulation on each satellite platform design scheme according to the load mechanical response conditions; perform satellite thermal analysis simulation on the satellite platform design scheme if the result of the satellite mechanical response simulation of the satellite platform design scheme meets the first requirement; and perform mechanical-thermal joint simulation on the satellite platform design scheme if the result of the satellite thermal analysis simulation of the satellite platform design scheme meets the second condition.

[0021] Optionally, the device further includes an optimization module for: If the simulation results of the satellite mechanical response of the satellite platform design scheme do not meet the first requirement, the structural mechanism subsystem of the satellite platform design scheme shall be optimized according to the preset first optimization strategy; or, If the satellite thermal analysis simulation results of the satellite platform design scheme do not meet the second condition, the thermal control subsystem of the satellite platform design scheme shall be optimized according to the preset second optimization strategy; or, If the results of the combined mechanical and thermal simulation of the satellite platform design scheme do not meet the third condition, the structural mechanism subsystem and thermal control subsystem of the satellite platform design scheme are jointly optimized according to the preset third optimization strategy.

[0022] The general satellite platform digital design method provided in this application parses the design requirement text, determines the subsystems corresponding to the design requirement text and the requirement indicators of each subsystem, matches the requirement indicators of each subsystem with the corresponding type library for each subsystem to obtain the single-unit selection results of the subsystem, integrates the single-unit selection results of each subsystem corresponding to the design requirement text to obtain one or more satellite platform design schemes, simulates one or more satellite platform design schemes to optimize them, and outputs a satellite platform design scheme that passes the simulation. This method can adapt to the adaptation requirements of various types of payloads, conducts selection based on a unified standardized type library, automatically selects reasonable subsystem products, and autonomously conducts automated simulation and verification. Through digital methods, it achieves rapid verification of the feasibility and indicator compliance of the design scheme, obtains the optimal solution that meets the limit constraints, reduces satellite design costs, shortens the satellite design cycle, adapts to the requirements of large-scale production, and provides technical support for the deployment of large-scale constellations. Attached Figure Description

[0023] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the accompanying drawings used in the description of the embodiments or the prior art will be briefly introduced below.

[0024] Figure 1A flowchart illustrating a general satellite platform digital design method according to an embodiment of this application is shown; Figure 2 A sub-flowchart of the satellite platform digital design method according to an embodiment of this application is shown; Figure 3 A flowchart illustrating a digital design method for a general-purpose satellite platform according to yet another embodiment of this application is shown; Figure 4 A flowchart illustrating a further embodiment of the digital design method for a general-purpose satellite platform according to this application is shown. Figure 5 A block diagram of a general satellite platform digital design apparatus according to an embodiment of this application is shown. Detailed Implementation

[0025] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0026] The terms "first," "second," etc., used in the specification and claims of this application are used to distinguish similar objects and not to describe a specific order or sequence. It should be understood that such terms can be used interchangeably where appropriate so that embodiments of this application can be implemented in orders other than those illustrated or described herein. Furthermore, in the specification and claims, "and / or" indicates at least one of the connected objects, and the character " / " generally indicates that the preceding and following objects are in an "or" relationship.

[0027] Figure 1 A flowchart illustrating a general satellite platform digital design method according to an embodiment of this application is provided. Figure 1 As shown, the method includes: Step S101: Obtain the design requirement text, parse the design requirement text, and determine the subsystems corresponding to the design requirement text and the requirement indicators of each subsystem.

[0028] The design requirements document describes the functions to be performed by the satellite platform, the requirements or conditions to be followed, and the specific standards to be met. Optionally, the design requirements document can be proposed by the satellite payload provider and may include multiple dimensions such as functional requirements, performance requirements, interface requirements (e.g., mechanical interfaces, electrical interfaces, data interfaces, etc.), and technical constraints.

[0029] Optionally, embodiments of this application can parse the design requirement text based on a preset parsing model to determine the subsystems corresponding to the design requirement text and the requirement indicators of each subsystem. The preset parsing model can be, for example, a Large Language Model (LLM) or a Bidirectional Encoder Representations from Transformers (BERT). As an optional example, the design requirement text can be input into the LLM, and a specified prompt can be input to guide the LLM in parsing the design requirement text. The prompt is an instruction or description that guides the LLM to generate specific outputs. For example, the prompt in this embodiment includes: "You are now a platform designer, and your core task is to perform structured deep parsing of the design requirement text I provide to determine the requirement indicators of each subsystem."

[0030] The satellite platform subsystem is the core service support system of the satellite platform, excluding the payload, and is the modular framework for the satellite platform to achieve its missions. Optionally, in this embodiment, the satellite platform subsystem includes, but is not limited to: structural mechanism subsystem, attitude and orbit control subsystem, power supply subsystem, integrated electronic subsystem, telemetry, tracking, and command (TT&C) and data transmission subsystem, and propulsion subsystem. The structural mechanism subsystem is responsible for maintaining the satellite configuration, supporting the payload, and withstanding extreme environments such as space radiation and micrometeorite impacts. The attitude and orbit control subsystem standardizes the specifications of satellite attitude control and orbit control components, maintaining the satellite in its predetermined orbit and ensuring stable attitude pointing, providing fundamental support for normal satellite operation. The power supply subsystem provides stable power to all satellite equipment and manages energy, and consists of, for example, solar panels (solar wings), batteries, and a power controller. The solar wings convert solar energy into electrical energy, the batteries store and discharge energy in the shadow area, and the power controller distributes the energy. The integrated electronic subsystem is responsible for unified scheduling and management of satellite data, processing internal information, and also for mission scheduling, health management, and fault handling. It standardizes the satellite's interface standards, ensuring the coordinated operation of all subsystems, and includes an onboard computer and bus interface modules. The telemetry, tracking, and command (TT&C) subsystem standardizes the specifications of satellite TT&C communication modules, responsible for data transmission and command reception between the satellite and ground stations, and enabling monitoring and control throughout the satellite's entire lifecycle. The thermal control subsystem maintains all onboard equipment within a suitable operating temperature range, for example, through passive thermal control (insulation, heat dissipation coatings) and active thermal control (heat pipes, extendable radiators) to balance equipment heat generation with the low-temperature environment of space. The propulsion subsystem provides the power required for orbit correction and attitude adjustment. Optionally, the propulsion subsystem can also be classified under the attitude and orbit control subsystem. Optionally, the required indicators for each subsystem in this application embodiment are as follows: the required indicators for the structural mechanism subsystem include, but are not limited to, the overall satellite base frequency, mechanical response envelope, and material thermal properties; the required indicators for the attitude and orbit control subsystem include, but are not limited to, orbit holding accuracy, attitude pointing accuracy, attitude stability, actuators, and lifespan; the required indicators for the power supply subsystem include, but are not limited to, output power, battery performance, and power attenuation rate; the required indicators for the integrated electronics subsystem include, but are not limited to, data storage capacity, number of interfaces, power consumption, data processing capability, and data processing reliability; the required indicators for the telemetry, tracking, and command (TT&C) and data transmission subsystem include, but are not limited to, data transmission rate, transmit power, and antenna gain; and the required indicators for the propulsion subsystem include, but are not limited to, thrust accuracy and propellant ratio.

[0031] Step S102: For each subsystem corresponding to the design requirement text, match the requirement indicators of the subsystem with the corresponding model library to obtain the single-machine selection result of the subsystem.

[0032] Optionally, the model library includes subsystem products of different models used to build satellite platforms, in order to quickly match the needs of different satellite platforms. For example, the model library includes, but is not limited to, the following information: product size information, envelope information (envelope refers to the set of constraints that limit the spatial boundaries and operating range of equipment / systems), interface information, data interface performance indicators, reliability information, and cost information. As an optional example, the model library in this application embodiment includes, but is not limited to: structural mechanism subsystem model library, attitude and orbit control subsystem model library, power supply subsystem model library, integrated electronic subsystem model library, telemetry, tracking and command data transmission subsystem model library, and propulsion subsystem model library. Among them, the structural mechanism subsystem model library includes standardized parameters, material selection, and mechanical property indicators of the body structure, module design, connection mechanism, and deployment mechanism (such as solar panel deployment mechanism) of satellites of different sizes, covering different configuration requirements from microsatellites to large satellites. The attitude and orbit control subsystem specification library includes standardized parameters for sensors (such as gyroscopes), actuators (thrusters, reaction wheels, etc.), and control processor algorithms for different control accuracy requirements, matching the attitude and orbit control needs of satellites in different orbits (low Earth orbit / high Earth orbit / geostationary orbit). The power supply subsystem specification library includes specifications, conversion efficiencies, and operating temperature ranges for solar arrays, energy storage batteries, and power control management units at different power levels, adapting to satellite products with different lifespans and power consumption. The integrated electronics subsystem specification library includes standardized configurations for onboard computers, data processing modules, bus interfaces, and satellite management software with different computing power requirements, covering standardized solutions for core functions such as data processing, task scheduling, and health management. The telemetry, tracking, and command (TT&C) and data transmission subsystem specification library includes parameter standards for TT&C transceivers, data transmission modules, and antennas in different frequency bands, covering telemetry data downlink and ground command uplink requirements at different rates, ensuring reliable and stable satellite-to-ground communication. The thermal control subsystem library includes thermal control units, components, and materials (such as thermal control coatings, multi-layer insulation components, heat pipes, electric heaters, fluid circuits, etc.). The propulsion subsystem includes: propellant tanks (for storing propellant) and thrusters (for generating thrust), as well as propulsion piping, pressure regulating devices, control valves, etc.

[0033] In this embodiment, by matching the subsystem requirement indicators corresponding to the design requirement text with the model library of each subsystem, rapid modular development of the satellite platform can be supported, reducing development costs. For example, the model library of the attitude and orbit control subsystem can support rapid selection of satellite control schemes, and the model library of the telemetry, tracking, and command (TT&C) and data transmission subsystem can support rapid interoperability of communication protocols between subsystems.

[0034] Optionally, for each subsystem, the subsystem requirement indicators can be solved using the corresponding analytical calculation formula and program to determine the single-unit selection results for each subsystem. Alternatively, when selecting subsystems, the requirement indicators of the subsystems can be matched with a model library based on requirements such as high reliability, low cost, and batch processing.

[0035] In this embodiment of the application, the selection process (step S102) for the structural mechanism subsystem, attitude and orbit control subsystem, power supply subsystem, integrated electronic subsystem, measurement and control data transmission subsystem, and propulsion subsystem includes: In response to the subsystems corresponding to the design requirements text, including the attitude and orbit control subsystem, integrated electronic subsystem, measurement and control data transmission subsystem, and / or propulsion subsystem, the requirement indicators of the attitude and orbit control subsystem, integrated electronic subsystem, measurement and control data transmission subsystem, and / or propulsion subsystem are matched with the corresponding type library to obtain the single-unit selection results of the attitude and orbit control subsystem, integrated electronic subsystem, measurement and control data transmission subsystem, and / or propulsion subsystem. In response to the subsystems corresponding to the design requirements text, including the power supply subsystem, the single-unit selection results of the attitude and orbit control subsystem, integrated electronic subsystem, measurement and control data transmission subsystem and / or propulsion subsystem, as well as the requirements of the power supply subsystem, are determined from the type library corresponding to the power supply subsystem. In response to the subsystems corresponding to the design requirements text, including the structural mechanism subsystem and / or thermal control subsystem, the individual unit selection results of the attitude and orbit control subsystem, integrated electronic subsystem, measurement and control data transmission subsystem, propulsion subsystem and / or power supply subsystem are determined from the model library corresponding to the structural mechanism subsystem and / or thermal control subsystem.

[0036] In this embodiment, the requirement indicators of the attitude and orbit control subsystem, integrated electronic subsystem, telemetry and data transmission subsystem, and propulsion subsystem are input into the corresponding model library. The model library solves the subsystem requirement indicators according to the built-in analytical calculation formulas and programs to determine the single-unit selection results of each subsystem. After obtaining the single-unit selection results of the attitude and orbit control subsystem, integrated electronic subsystem, telemetry and data transmission subsystem, and propulsion subsystem, the selection results of the power supply subsystem are comprehensively determined based on the power requirements of the single-unit selection results of the attitude and orbit control subsystem, integrated electronic subsystem, telemetry and data transmission subsystem, and propulsion subsystem, as well as the requirement indicators of the power supply subsystem. Subsequently, based on the weight, power consumption, structural envelope, layout constraints, and other conditions of each subsystem of the attitude and orbit control subsystem, integrated electronic subsystem, telemetry and data transmission subsystem, propulsion subsystem, and power supply subsystem, as well as the requirement indicators of the structural mechanism subsystem and thermal control subsystem, the selection results of the structural mechanism subsystem and thermal control subsystem are determined.

[0037] Step S103: Integrate the single-unit selection results of each subsystem corresponding to the design requirements text to obtain one or more satellite platform design schemes.

[0038] For example, based on the basic parameters such as the center of mass, envelope, weight, and moment of inertia provided by the payload provider, the various subsystems of the satellite platform are connected through a unified and compatible mechanical interface to form a unified whole, resulting in one or more preliminary design schemes for the satellite platform.

[0039] In an optional embodiment, the satellite platform frame structure selection result can be determined based on the satellite unit layout design requirements for the largest installation contact surface. Based on the satellite platform frame structure selection result and the unit selection results of each subsystem corresponding to the design requirements text, a multi-objective genetic algorithm is used to obtain one or more satellite platform design schemes. The multi-objective genetic algorithm (MOGA) is an optimization method that simulates biological evolution and is specifically designed to solve multi-objective conflict problems, outputting a set of Pareto optimal solutions rather than a single optimal solution. In this embodiment, based on the satellite platform frame structure selection result, the functions and performance parameters of each subsystem (e.g., the heat generated during operation of each subsystem) can be used as optimization objectives for iterative iteration, thereby obtaining one or more satellite platform design schemes.

[0040] Step S104: Simulate one or more satellite platform design schemes to optimize one or more satellite platform design schemes.

[0041] For example, embodiments of this application utilize one or more simulation tools to perform mechanical response simulation and thermal analysis simulation on each satellite platform design scheme to ensure the overall performance of the satellite platform and individual units, such as ensuring that heat dissipation efficiency meets technical requirements. Optionally, to meet the high reliability requirements of the satellite platform, the simulation of the satellite platform design scheme is sequential; for example, mechanical response simulation is performed on the satellite platform first, followed by thermal control simulation.

[0042] Figure 2 A schematic flowchart illustrating the simulation of a satellite platform design scheme according to an embodiment of this application is shown. Figure 2 As shown, the simulation of each satellite platform design scheme includes: Step S201: Based on the load mechanical response conditions, perform satellite mechanical response simulation on one or more satellite platform design schemes. Optionally, the load mechanical response conditions include the mechanical environment constraints and response index requirements that the satellite payload needs to meet throughout its launch and on-orbit life cycle. These may include quasi-static acceleration, random vibration, sinusoidal vibration, high-frequency impact, aerodynamic noise during launch, and load conditions under on-orbit operation and separation scenarios. The mechanical environment constraints indicated by the load mechanical response conditions are applied to the satellite platform and payload for simulation, and the simulation results are obtained. The simulation results are compared with the first requirement to determine whether the satellite platform meets the requirement. The first requirement may include, for example, the mechanical response requirements proposed by the payload provider, and may also include the response index requirements indicated by the load mechanical response conditions.

[0043] Step S202: Determine whether the simulation results of the satellite mechanical response of the satellite platform design scheme meet the first requirement. If the simulation results of the satellite mechanical response of the satellite platform design scheme meet the first requirement, proceed to step S203. If the simulation results of the satellite mechanical response of the satellite platform design scheme do not meet the first requirement, proceed to step S204.

[0044] Step S203: Perform satellite thermal analysis simulation on the satellite platform design scheme. This simulation is used to model the temperature distribution throughout the satellite's on-orbit lifecycle, ensuring stable operation of the platform and payload. In this embodiment, a thermal mathematical model is constructed based on the unit selection results of each subsystem of the satellite platform, such as the heat consumption of each subsystem, and simulation is performed according to the satellite platform's operating sequence. The simulation results are compared with the second requirement to determine whether the satellite platform meets the requirement. The second requirement may, for example, include the temperature distribution requirements for the satellite's on-orbit lifecycle proposed by the payload provider.

[0045] Step S204: Optimize the structural subsystem of the satellite platform design scheme according to the preset first optimization strategy.

[0046] Step S205: Determine whether the satellite thermal analysis simulation results of the satellite platform design scheme meet the second requirement. If the satellite thermal analysis simulation results of the satellite platform design scheme meet the second requirement, proceed to step S206. If the satellite thermal analysis simulation results of the satellite platform design scheme do not meet the second requirement, proceed to step S207.

[0047] Step S206: Perform mechanical and thermal joint simulation of the satellite platform design. After completing the mechanical and thermal simulations of the satellite platform, perform mechanical and thermal joint simulation to achieve full-process simulation verification and identify potential mechanical and thermal coupling failures in advance.

[0048] Step S207: Optimize the thermal control subsystem of the satellite platform design scheme according to the preset second optimization strategy.

[0049] Step S208: Determine whether the results of the force-thermal co-simulation of the satellite platform design scheme meet the third requirement. If the results of the force-thermal co-simulation of the satellite platform design scheme meet the third requirement, proceed to step S209. If the results of the force-thermal co-simulation of the satellite platform design scheme do not meet the third requirement, proceed to step S210.

[0050] Step S209: Output the satellite platform design scheme.

[0051] Step S210: Based on the preset third optimization strategy, jointly optimize the structural mechanism subsystem and thermal control subsystem of each satellite platform design scheme.

[0052] If the satellite mechanical response simulation results of the satellite platform design scheme do not meet the first requirement, or the satellite thermal analysis simulation results do not meet the second requirement, or the combined mechanical and thermal simulation results do not meet the third requirement, the structural mechanism subsystem and / or thermal control subsystem of the satellite platform design scheme shall be optimized (e.g., by modifying the parameters of the structural mechanism subsystem and / or thermal control subsystem or by reselecting the subsystem). Different optimization strategies can be set for subsystems with different functions. For example, optimization strategies for optimizing the structural mechanism subsystem and thermal control subsystem can be derived based on expert experience; alternatively, optimization models (e.g., expert systems) can be used to optimize the structural mechanism subsystem and thermal control subsystem.

[0053] Step S105: Output the satellite platform design scheme that has passed the simulation. For example, output the satellite platform design scheme that has passed the simulation and its performance indicators, the single-unit selection results and performance indicators of each subsystem corresponding to the satellite platform design scheme, thereby completing the digital design process of the satellite platform.

[0054] The general satellite platform digital design method provided in this application parses the design requirement text, determines the subsystems corresponding to the design requirement text and the requirement indicators of each subsystem, matches the requirement indicators of each subsystem with the corresponding model library for each subsystem to obtain the single-unit selection results of the subsystem, integrates the single-unit selection results of each subsystem corresponding to the design requirement text to obtain one or more satellite platform design schemes, simulates one or more satellite platform design schemes to optimize one or more satellite platform design schemes, and outputs the satellite platform design scheme that passes the simulation. This method allows for targeted selection based on the specific indicators of each subsystem, perfectly matching the differentiated needs of different payloads. It avoids potential performance redundancy or shortcomings when directly determining products based on overall indicators. Furthermore, if a subsystem selection is unreasonable, it can be directly replaced, completing defect repair before integration. This avoids discovering core shortcomings only after the overall product development is completed, eliminating the need to redevelop the entire satellite and significantly reducing the risk of project failure. Moreover, the selection and verification of subsystems can be processed in parallel, shortening the development cycle. It enables autonomous automated simulation and verification, using digital methods to quickly verify the feasibility and compliance of design schemes, obtaining the optimal solution that meets the limit constraints, reducing satellite design costs, shortening the satellite design cycle, adapting to the requirements of large-scale production, and providing technical support for the deployment of large-scale constellations.

[0055] Figure 3 A flowchart illustrating a general satellite platform digital design method according to another embodiment of this application is provided. Figure 3 As shown, the method includes: Step S301: Parse the design requirement text to determine the load requirement indicators, which include one or more of the following: load type, load operating mode, power consumption, weight, and data volume.

[0056] Step S302: Analyze the load requirement indicators according to the subsystem performance indicators to determine the subsystems corresponding to the design requirement text and the requirement indicators of each subsystem.

[0057] For steps S301-S302, this embodiment of the application can progressively parse the design requirement text based on a preset analytical model. First, the load requirement indicators are determined, and then the requirement indicators for each subsystem are further determined based on the load requirement indicators. Load types include, for example, high-precision loads, high-stability loads, high-maneuverability loads, communication loads, navigation loads, and remote sensing loads. Load operating modes include, for example, optical loads and SAR (Synthetic Aperture Radar) loads. Taking the attitude and orbit control subsystem as an example, this illustrates that different types of loads correspond to subsystems with different requirement indicators. For high-precision loads, high-stability loads, and high-maneuverability loads, attitude control indicator requirements are determined, and corresponding single units are selected from the specific classifications in the type library.

[0058] Step S303: For each subsystem corresponding to the design requirement text, match the requirement indicators of the subsystem with the corresponding model library to obtain the single-machine selection result of the subsystem.

[0059] Step S304: For each subsystem, determine whether the subsystem's requirement indicators meet the corresponding rationality requirements. If the subsystem's requirement indicators do not meet the corresponding rationality requirements, proceed to step S305. If the subsystem's requirement indicators meet the corresponding rationality requirements, proceed to step S306.

[0060] Different satellite platform subsystems have different rationality requirements. Optionally, a database can be constructed to record and store the rationality requirements of each satellite platform subsystem, as well as the rules or strategies for verifying the rationality of the subsystems. For example, the database records expert experience and rationality requirements and rationality verification rules standardized based on expert experience. In an optional embodiment, the rationality of the satellite platform subsystem is verified based on aspects such as the rocket's launch weight, envelope, payload orbit, mode, long-term power consumption, accuracy, stability, and operating time of the payload. Optionally, embodiments of this application can also use a rationality verification model to determine whether the subsystem's requirement indicators meet the corresponding rationality requirements of the subsystem. This overall verification model can be a rule-based expert system or a deep learning-based network model. If the rationality verification model is a deep learning-based network model, it can be obtained from collected training samples, which may include, for example, the performance parameters and rationality labels of the subsystems included in different specifications of satellite platforms (the rationality labels are used to indicate whether the performance parameters of the satellite platform's subsystems are reasonable, and these rationality labels can be manually marked).

[0061] The embodiments of this application can re-analyze the design requirement text for requirement indicators that do not meet the requirements of rationality, which can identify problems in advance, avoid subsequent remedial redesign, and reduce design costs.

[0062] Step S305: Re-parse the design requirements text to determine the requirement indicators for the subsystems.

[0063] Step S306: Integrate the single-unit selection results of each subsystem corresponding to the design requirements text to obtain one or more satellite platform design schemes.

[0064] Step S307: Simulate one or more satellite platform design schemes to optimize one or more satellite platform design schemes.

[0065] Step S308: Output the satellite platform design scheme that has passed the simulation.

[0066] Steps S303 and S306-S308 can be referenced. Figure 1 The embodiments shown are not described in detail here to avoid repetition.

[0067] Figure 4 A flowchart illustrating a general satellite platform digital design method according to another embodiment of this application is provided. Figure 4 As shown, the method includes: Step S401: Parse the design requirement text to determine the load requirement indicators, which include one or more of the following: load type, load operating mode, power consumption, weight, and data volume.

[0068] Step S402: Analyze the load requirement indicators according to the subsystem performance indicators to determine the subsystems corresponding to the design requirement text and the requirement indicators of each subsystem.

[0069] Step S403: For each subsystem corresponding to the design requirement text, match the requirement indicators of the subsystem with the corresponding model library to obtain the single-machine selection result of the subsystem.

[0070] Step S404: For each subsystem, determine whether the subsystem's requirement indicators meet the corresponding rationality requirements. If the subsystem's requirement indicators do not meet the corresponding rationality requirements, proceed to step S405. If the subsystem's requirement indicators meet the corresponding rationality requirements, proceed to step S406.

[0071] Step S405: Re-parse the design requirements text to determine the requirement indicators for the subsystems.

[0072] Step S406: Integrate the single-unit selection results of each subsystem corresponding to the design requirements text to obtain one or more satellite platform design schemes.

[0073] Step S407: Conduct an overall review of one or more satellite platform design schemes. If the overall review of one or more satellite platform design schemes fails, proceed to step S408. If the overall review of one or more satellite platform design schemes passes, proceed to step S409.

[0074] Step S408: Reselect subsystems in one or more satellite platform design schemes that do not meet the overall integrity verification requirements until one or more satellite platform design schemes pass the overall integrity verification.

[0075] Step S409: Simulate one or more satellite platform design schemes to optimize one or more satellite platform design schemes.

[0076] Step S410: Output the satellite platform design scheme that has passed the simulation.

[0077] Steps S401-S406 and S409-S410 can be referred to Figure 1 or Figure 3 The embodiments shown are not described in detail here to avoid repetition. For steps S407-S408, this embodiment determines whether the satellite platform design meets the overall performance requirements, mainly by determining whether there is interference in the envelopes of each subsystem of the satellite platform and checking whether the attitude and orbit control subsystem meets the satellite requirements. Optionally, this embodiment can perform an overall verification of the satellite platform design using an overall verification model. This overall verification model can be trained based on data from historically designed satellite platforms (e.g., including the functional parameters of the satellite platform and the performance parameters of each subsystem). This overall verification model can be a rule-based expert system or a deep learning-based network model (e.g., a graph neural network or a large language model based on thought chain technology for reasoning).

[0078] Optionally, embodiments of this application further include: constructing a knowledge base, which includes one or more of the following: a parsing model, a matching model, a rationality verification model, an overall verification model, and an optimization model. The parsing model is used to parse the design requirement text and determine the subsystems corresponding to the design requirement text and the requirement indicators of each subsystem. The matching model is used to match the requirement indicators of the subsystems with the corresponding model library to obtain the single-unit selection results of the subsystems. The rationality verification model is used to determine whether the requirement indicators of the subsystems meet the rationality requirements corresponding to the subsystems. The overall verification model is used to perform an overall verification of the satellite platform design scheme obtained after integrating the single-unit selection results of each subsystem corresponding to the design requirement text. The optimization model includes multiple optimization strategies used to optimize satellite platform design schemes where simulation results do not meet the requirements.

[0079] Figure 5 A block diagram of a general-purpose satellite platform digital design apparatus according to an embodiment of this application is shown. Figure 5 As shown, the general-purpose satellite platform digital design device 500 includes: The parsing module 501 is used to obtain the design requirement text, parse the design requirement text, and determine the subsystems corresponding to the design requirement text and the requirement indicators of each subsystem. The matching module 502 is used to match the requirement indicators of each subsystem corresponding to the design requirement text with the model library corresponding to the subsystem to obtain the single-machine selection result of the subsystem. The integration module 503 is used to integrate the single-unit selection results of each subsystem corresponding to the design requirements text to obtain one or more satellite platform design schemes. The simulation module 504 is used to simulate the design schemes of the one or more satellite platforms in order to optimize the design schemes of the one or more satellite platforms. Output module 505 is used to output the satellite platform design scheme obtained through the simulation.

[0080] Optionally, the parsing module is further configured to: parse the design requirement text to determine load requirement indicators, wherein the load requirement indicators include one or more of the following: load type, load operating mode, power consumption, weight, and data volume; and parse the load requirement indicators according to the subsystem performance indicators to determine the subsystems corresponding to the design requirement text and the requirement indicators of each subsystem.

[0081] Optionally, the device further includes a first verification module, configured to: for each subsystem, determine whether the requirement indicators of the subsystem meet the corresponding rationality requirements of the subsystem; the matching module is further configured to, when the requirement indicators of the subsystem do not meet the corresponding rationality requirements of the subsystem, re-parse the design requirement text to determine the requirement indicators of the subsystem.

[0082] Optionally, the subsystems corresponding to the design requirements text include one or more of the following: structural mechanism subsystem, attitude and orbit control subsystem, power supply subsystem, integrated electronic subsystem, measurement and control data transmission subsystem, thermal control subsystem, and propulsion subsystem; The matching module is further configured to: in response to the subsystems corresponding to the design requirement text including an attitude and orbit control subsystem, an integrated electronic subsystem, a measurement and control data transmission subsystem, and / or a propulsion subsystem, match the requirement indicators of the attitude and orbit control subsystem, the integrated electronic subsystem, the measurement and control data transmission subsystem, and / or the propulsion subsystem with the corresponding model library to obtain the single-unit selection results of the attitude and orbit control subsystem, the integrated electronic subsystem, the measurement and control data transmission subsystem, and / or the propulsion subsystem; and in response to the subsystems corresponding to the design requirement text including a power supply subsystem, match the requirement indicators of the attitude and orbit control subsystem, the integrated electronic subsystem, the measurement and control data transmission subsystem, and / or the propulsion subsystem with the corresponding model library to obtain the single-unit selection results of the attitude and orbit control subsystem, the integrated electronic subsystem, the measurement and control data transmission subsystem, and / or the propulsion subsystem. Based on the unit selection results of the transmission subsystem and / or propulsion subsystem and the requirement indicators of the power supply subsystem, the unit selection results of the power supply subsystem are determined from the type library corresponding to the power supply subsystem; in response to the subsystems corresponding to the design requirement text, including the structural mechanism subsystem and / or thermal control subsystem, based on the unit selection results of the attitude and orbit control subsystem, integrated electronic subsystem, telemetry and data transmission subsystem, propulsion subsystem and / or power supply subsystem, the unit selection results of the structural mechanism subsystem and / or thermal control subsystem are determined from the type library corresponding to the structural mechanism subsystem and / or thermal control subsystem.

[0083] Optionally, the device further includes a second verification module, used to: perform an overall verification of the one or more satellite platform design schemes; the matching module is also used to, if the overall verification of the one or more satellite platform design schemes fails, reselect subsystems in the one or more satellite platform design schemes that do not meet the overall verification requirements, until the one or more satellite platform design schemes pass the overall verification.

[0084] Optionally, the simulation module is further configured to: perform satellite mechanical response simulation on the satellite platform design scheme according to the load mechanical response conditions; perform satellite thermal analysis simulation on the satellite platform design scheme if the result of the satellite mechanical response simulation of the satellite platform design scheme meets the first requirement; and perform mechanical-thermal joint simulation on the satellite platform design scheme if the result of the satellite thermal analysis simulation of the satellite platform design scheme meets the second condition.

[0085] Optionally, the device further includes an optimization module for: If the simulation results of the satellite mechanical response of the satellite platform design scheme do not meet the first requirement, the structural mechanism subsystem of the satellite platform design scheme shall be optimized according to the preset first optimization strategy; or, If the satellite thermal analysis simulation results of the satellite platform design scheme do not meet the second condition, the thermal control subsystem of the satellite platform design scheme shall be optimized according to the preset second optimization strategy; or, If the results of the combined mechanical and thermal simulation of the satellite platform design scheme do not meet the third condition, the structural mechanism subsystem and thermal control subsystem of the satellite platform design scheme are jointly optimized according to the preset third optimization strategy.

[0086] The above-described apparatus can execute the method provided in the embodiments of the present invention, and has the corresponding functional modules and beneficial effects for executing the method. Technical details not described in detail in this embodiment can be found in the general satellite platform digital design method provided in the embodiments of the present invention.

[0087] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0088] The various embodiments in this specification are described in a related manner. Similar or identical parts between embodiments can be referred to mutually. Each embodiment focuses on describing the differences from other embodiments. In particular, the system embodiments are basically similar to the method embodiments, so the description is relatively simple; relevant parts can be referred to the descriptions of the method embodiments.

[0089] The above description is merely a preferred embodiment of the present invention and is not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention are included within the scope of protection of the present invention.

Claims

1. A general digital design method for satellite platforms, characterized in that, include: Obtain the design requirement text, parse the design requirement text, and determine the subsystems corresponding to the design requirement text and the requirement indicators of each subsystem; For each subsystem corresponding to the design requirement text, the requirement indicators of the subsystem are matched with the corresponding model library to obtain the single-unit selection result of the subsystem; the model library includes one or more of the following: product size information, envelope information, interface information, data interface performance indicators, reliability information, and cost information; By integrating the single-unit selection results of each subsystem corresponding to the design requirements text, one or more satellite platform design schemes are obtained; Simulations are performed on the design schemes of the one or more satellite platforms to optimize them. Output the satellite platform design scheme obtained through the simulation.

2. The method according to claim 1, characterized in that, The step of parsing the design requirement text to determine the subsystems corresponding to the design requirement text and the requirement indicators of each subsystem includes: The design requirement text is parsed to determine the load requirement indicators, which include one or more of the following: load type, load operating mode, power consumption, weight, and data volume. The load requirement indicators are analyzed according to the subsystem performance indicators to determine the subsystems corresponding to the design requirement text and the requirement indicators of each subsystem.

3. The method according to claim 1, characterized in that, The method further includes: For each subsystem, determine whether the demand indicators of the subsystem meet the corresponding rationality requirements of the subsystem; If the requirement indicators of the subsystem do not meet the corresponding rationality requirements of the subsystem, the design requirement text shall be re-parsed to determine the requirement indicators of the subsystem.

4. The method according to claim 1, characterized in that, The subsystems corresponding to the design requirements text include one or more of the following: structural mechanism subsystem, attitude and orbit control subsystem, power supply subsystem, integrated electronic subsystem, measurement and control data transmission subsystem, thermal control subsystem, and propulsion subsystem; For each subsystem corresponding to the design requirement text, the requirement indicators of the subsystem are matched with the corresponding model library to obtain the single-machine selection result of the subsystem, including: In response to the subsystems corresponding to the design requirements text, including the attitude and orbit control subsystem, integrated electronic subsystem, measurement and control data transmission subsystem, and / or propulsion subsystem, the requirement indicators of the attitude and orbit control subsystem, integrated electronic subsystem, measurement and control data transmission subsystem, and / or propulsion subsystem are matched with the corresponding type library to obtain the single-unit selection results of the attitude and orbit control subsystem, integrated electronic subsystem, measurement and control data transmission subsystem, and / or propulsion subsystem; In response to the subsystems corresponding to the design requirements text, including the power supply subsystem, the single-unit selection results of the attitude and orbit control subsystem, integrated electronic subsystem, measurement and control data transmission subsystem and / or propulsion subsystem, as well as the requirements indicators of the power supply subsystem, are determined from the type library corresponding to the power supply subsystem. In response to the subsystems corresponding to the design requirements text, including the structural mechanism subsystem and / or thermal control subsystem, the individual unit selection results of the structural mechanism subsystem and / or thermal control subsystem are determined from the model library corresponding to the structural mechanism subsystem and / or thermal control subsystem based on the unit selection results of the attitude and orbit control subsystem, integrated electronic subsystem, measurement and control data transmission subsystem, propulsion subsystem and / or power supply subsystem.

5. The method according to claim 1, characterized in that, By integrating the unit selection results of each subsystem corresponding to the design requirements text, one or more satellite platform design schemes are obtained, including: Based on the satellite unit layout design requirements for the largest installation contact surface, the selection result of the satellite platform frame structure is determined; Based on the satellite platform's framework structure selection results, the single-unit selection results of each subsystem corresponding to the design requirements text, and the multi-objective genetic algorithm, one or more satellite platform design schemes are obtained.

6. The method according to claim 1, characterized in that, Before simulating the design schemes of the one or more satellite platforms, the method further includes: A comprehensive review of the design schemes for the one or more satellite platforms shall be conducted. If the overall integrity test of one or more satellite platform design schemes fails, the subsystems in the one or more satellite platform design schemes that do not meet the overall integrity test requirements shall be reselected until the one or more satellite platform design schemes pass the overall integrity test.

7. The method according to claim 1, characterized in that, The simulation of the design schemes of the one or more satellite platforms includes: For each satellite platform design scheme, a satellite mechanical response simulation is performed based on the load mechanical response conditions. If the satellite mechanical response simulation results of the satellite platform design scheme meet the first requirement, then the satellite thermal analysis simulation is performed on the satellite platform design scheme. If the results of the satellite thermal analysis simulation of the satellite platform design scheme meet the second condition, a combined mechanical and thermal simulation of the satellite platform design scheme is performed.

8. The method according to claim 7, characterized in that, The simulation of the design schemes of the one or more satellite platforms also includes: If the simulation results of the satellite mechanical response of the satellite platform design scheme do not meet the first requirement, the structural mechanism subsystem of the satellite platform design scheme shall be optimized according to the preset first optimization strategy; or, If the satellite thermal analysis simulation results of the satellite platform design scheme do not meet the second condition, the thermal control subsystem of the satellite platform design scheme shall be optimized according to the preset second optimization strategy; or, If the results of the combined mechanical and thermal simulation of the satellite platform design scheme do not meet the third condition, the structural mechanism subsystem and thermal control subsystem of the satellite platform design scheme are jointly optimized according to the preset third optimization strategy.

9. The method according to any one of claims 1-8, characterized in that, The method further includes: constructing a knowledge base, which includes one or more of the following: a parsing model, a matching model, a rationality verification model, an overall verification model, and an optimization model; The analytical model is used to parse the design requirement text and determine the subsystems corresponding to the design requirement text and the requirement indicators of each subsystem. The matching model is used to match the requirement indicators of the subsystem with the model library corresponding to the subsystem to obtain the single-unit selection result of the subsystem; The rationality verification model is used to determine whether the demand indicators of the subsystem meet the rationality requirements corresponding to the subsystem. The overall verification model is used to perform an overall verification of the satellite platform design scheme obtained after the individual selection results of each subsystem corresponding to the integrated design requirements text. The optimization model includes multiple optimization strategies for optimizing satellite platform design schemes where simulation results do not meet requirements.

10. A general-purpose satellite platform digital design device, characterized in that, include: The parsing module is used to obtain the design requirement text, parse the design requirement text, and determine the subsystems corresponding to the design requirement text and the requirement indicators of each subsystem. The matching module is used to match the requirement indicators of each subsystem corresponding to the design requirement text with the model library corresponding to the subsystem to obtain the single-unit selection result of the subsystem; the model library includes one or more of the following: product size information, envelope information, interface information, data interface performance indicators, reliability information and cost information; The integration module is used to integrate the single-unit selection results of each subsystem corresponding to the design requirements text to obtain one or more satellite platform design schemes. The simulation module is used to simulate the design schemes of the one or more satellite platforms in order to optimize the design schemes of the one or more satellite platforms. The output module is used to output the satellite platform design scheme obtained through the simulation.

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