Space system architecture design perfecting method and system based on reliable safety analysis

Abstract

The application provides a space system architecture design perfecting method and system based on reliable safety analysis, comprising: determining a space task system architecture, reliability and safety requirements and various failure modes and mutual correlation based on space flight task design requirements, and constructing a failure transmission logic; constructing a simulation case based on the failure transmission logic on the basis of meeting the reliability and safety requirements, and testing the space task system based on the simulation case; perfecting the space task system architecture based on the space task system test results, the application carries out space task design based on a model, uses the generated system forward design model to complete the safety and reliability analysis of the space task, ensures the consistency of the space task design and the safety and reliability analysis, and realizes a complete closed loop from the requirement analysis and the system design to the reliability and safety analysis and the system architecture improvement.

Description

Technical Field

[0001] This invention relates to the field of aerospace system safety and reliability analysis technology, specifically to a method and system for improving aerospace system architecture design based on reliability and safety analysis. Background Technology

[0002] With the increasing complexity of space missions, model-based systems engineering (MBSE) methods have been widely applied in this field. The corresponding system safety and reliability analysis must also be based on models, thus giving rise to model-based safety and reliability analysis (MBSE). Complex space missions, such as manned spaceflight missions, are costly and risky, with the safety of astronauts being paramount. Therefore, with the gradual application of MBSE in the aerospace field, it is also necessary to develop model-based safety and reliability analysis methods suitable for space mission design. This ensures consistency between the design and reliability analysis models, identifies potential system risks during the conceptual design phase, and reduces development cycles and costs.

[0003] Currently, model-based safety and reliability analysis methods lack a systematic framework and are unsuitable for the needs of aerospace mission analysis. For example, existing methods primarily rely on Failure Mode and Effects Analysis (FMEA) and Fault Tree Analysis (FTA), offering limited functionality and failing to assess aerospace missions that consider the timing of failures and include contingency strategies. Furthermore, existing methods involve transforming a SysML-based system model into a readable model for the safety and reliability analysis platform, allowing for further analysis within that platform. While this method ensures model consistency, the increased model transmission links introduce the risk of untimely model updates. A feedback mechanism must be designed to link the safety and reliability analysis results across platforms with the SysML model; otherwise, safety and reliability analysis cannot be integrated into the closed loop of system design. However, by utilizing SysML for system design while simultaneously conducting safety and reliability analysis based on SysML, this shared modeling language approach effectively addresses the aforementioned issues. By extending SysML, a modeling language for the safety and reliability domain can be defined, enabling precise expression of safety and reliability analysis. However, this approach requires addressing the issues of integrating security and reliability analysis with system design, and how to specifically model and analyze the data. Summary of the Invention

[0004] To address the problems existing in the prior art, this invention provides a method for improving aerospace system architecture design based on reliability and security analysis, including:

[0005] Based on the design requirements of aerospace flight missions, the aerospace mission system architecture, reliability and safety requirements, and various failure modes are determined, and the correlation between the aerospace mission system architecture, reliability and safety requirements, and various failure modes is established.

[0006] Based on the aforementioned aerospace mission system architecture, reliability and safety requirements, and fault mode correlations, a fault propagation logic is constructed.

[0007] Based on the fault propagation logic, simulation test cases are constructed while meeting reliability and safety requirements, and the aerospace mission system is tested based on the simulation test cases.

[0008] The space mission system architecture was improved based on the test results.

[0009] Preferably, the process of determining the space mission system architecture, reliability and safety requirements, and various failure modes based on the space mission design requirements, and establishing the correlation between the space mission system architecture, reliability and safety requirements, and various failure modes, includes:

[0010] The top-level requirements for the system architecture and reliability and safety of the space mission are determined according to the design requirements of the space flight mission.

[0011] Based on the functions to be achieved in a spaceflight mission, several flight phases are determined, and the top-level requirements for reliability and safety are decomposed into each flight phase.

[0012] Based on the flight phase, the subsystems included in the space mission system are determined, and the top-level reliability and safety requirements are decomposed into each flight phase and each subsystem to obtain the reliability and safety requirements of each subsystem.

[0013] Fault mode identification is performed based on the flight phase to obtain the fault mode;

[0014] Based on each flight phase, subsystems are established, along with the reliability and safety requirements of each subsystem and the correlation between each failure mode.

[0015] The flight phase is a multi-level flight phase, including at least a primary flight phase and sub-flight phases under the primary flight phase; each primary flight phase and sub-flight phase includes corresponding flight operations.

[0016] Preferably, the top-level requirements for reliability and safety are determined based on the design requirements of the spaceflight mission, including:

[0017] Based on the items involved in the design requirements of the spaceflight mission and the expected risks of the spaceflight mission, the top-level requirements for the reliability and safety of the spaceflight mission are obtained.

[0018] Preferably, the first-stage flight phase includes at least: the launch into low Earth orbit phase and / or the low Earth orbit flight phase; the sub-flight phase includes at least: the engine start-up sub-phase and / or the launch vehicle first-stage engine operation sub-phase.

[0019] Preferably, the step of constructing the fault propagation logic based on the aerospace mission system architecture, reliability and safety requirements, and fault mode correlation includes:

[0020] Based on the flight operations to be performed during the flight phases corresponding to each subsystem in the aforementioned space mission system architecture, the functions performed by each subsystem and the modules corresponding to those functions are determined.

[0021] The failure modes are improved based on the flight operations corresponding to each module and flight phase, and a failure propagation model is obtained by using risk assessment and modeling language.

[0022] Based on the reliability and safety requirements of each module, the fault propagation model, and each subsystem, the traceability relationships of each fault mode, aerospace flight mission design requirements, aerospace mission system, subsystem, and each module are determined.

[0023] Based on the aforementioned failure modes, spaceflight mission design requirements, space mission systems, subsystems, and the tracing relationships of each module, the fault propagation logic of the entire space mission system is constructed.

[0024] Preferably, the process of identifying fault modes based on the flight operations corresponding to each module and flight phase, refining the fault modes based on the identified fault modes and the corresponding modules and flight operations of the flight phases, and modeling them using risk assessment and modeling languages ​​to obtain a fault propagation model includes:

[0025] The basic model for security and reliability analysis is defined using a risk assessment and modeling language, and a basic type library is formed in the SysML system modeling language environment.

[0026] An iterative fault analysis method is used for each flight phase or flight operation to determine whether there are new fault modes in the space mission system and its subsystems. If so, the fault modes are improved based on the new fault modes.

[0027] A fault propagation model is obtained by modeling using the base model and the fault modes.

[0028] Preferably, the step of constructing simulation test cases based on the fault propagation logic while meeting reliability and safety requirements, and testing the aerospace mission system based on the simulation test cases, includes:

[0029] Establish simulation use cases with traceability relationships, based on top-level requirements, reliability and safety requirements for each flight phase and each subsystem.

[0030] Based on the fault propagation model, simulation analysis is performed using various use cases to determine the results of the safety and reliability analysis.

[0031] Based on the results of each safety and reliability analysis, the results are compared with the aerospace mission system architecture and each subsystem to improve the aerospace mission system architecture or improve the design of each subsystem.

[0032] The simulation analysis is based on qualitative analysis using FMEA and / or quantitative analysis using FTA.

[0033] Preferably, the comparison of each simulation analysis result with the aerospace mission system architecture and each subsystem, in order to improve the aerospace mission system architecture or improve the design of each subsystem, includes:

[0034] Compare the qualitative safety and reliability analysis results with the design principles of the aerospace mission system to verify whether they meet the reliability and safety design principles. If they do not meet the requirements, it is necessary to improve the system functional logic architecture or improve the subsystem design for the failure modes, flight phases or subsystems that are traceable to this requirement.

[0035] The quantitative safety and reliability analysis results are compared with the reliability and safety requirements of the aerospace mission system to verify whether they meet the requirements. If they do not meet the requirements, the system functional logic architecture or subsystem design needs to be improved for failure modes, flight phases or subsystems that are traceable to the requirements.

[0036] Preferably, the improved system functional logic architecture or subsystem design includes:

[0037] Based on the identified fault modes and prior knowledge, the corresponding emergency response strategies are determined.

[0038] The emergency response strategies corresponding to each failure mode are integrated into the aerospace mission system architecture to improve the mission's operational logic.

[0039] Based on the same inventive concept, this invention also provides a spaceflight mission safety and reliability analysis system for system design, comprising:

[0040] The relationship determination module is used to determine the aerospace mission system architecture, reliability and safety requirements, and various failure modes based on the aerospace flight mission design requirements, and to establish the correlation between the aerospace mission system architecture, reliability and safety requirements, and various failure modes.

[0041] The fault propagation logic construction module is used to construct fault propagation logic based on the aerospace mission system architecture, reliability and safety requirements, and fault mode correlations.

[0042] The simulation test module is used to construct simulation test cases based on the fault propagation logic while meeting reliability and safety requirements, and to test the aerospace mission system based on the simulation test cases.

[0043] An improvement module is used to improve the architecture of the space mission system based on the test results of the space mission system.

[0044] Based on the same inventive concept, the present invention also provides a computer device, comprising: one or more processors;

[0045] The processor is used to store one or more programs;

[0046] When the one or more programs are executed by the one or more processors, the aerospace system architecture design improvement method based on reliability and security analysis provided by the present invention is implemented.

[0047] Based on the same inventive concept, the present invention also provides a computer-readable storage medium having a computer program stored thereon, wherein when the computer program is executed, it implements the aerospace system architecture design improvement method based on reliability and security analysis provided by the present invention.

[0048] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0049] This invention provides a method and system for improving aerospace system architecture design based on reliability and safety analysis. The method includes: determining the aerospace mission system architecture, reliability and safety requirements, and various failure modes based on the aerospace flight mission design requirements, and establishing the correlation between the aerospace mission system architecture, reliability and safety requirements, and each failure mode; constructing fault propagation logic based on the correlation between the aerospace mission system architecture, reliability and safety requirements, and failure modes; constructing simulation test cases based on the fault propagation logic while meeting the reliability and safety requirements, and testing the aerospace mission system based on the simulation test cases; and improving the aerospace mission system architecture based on the test results. This invention, while conducting model-based aerospace mission design, utilizes the generated system forward design model to complete the safety and reliability analysis of the aerospace mission, ensuring consistency between the aerospace mission design and the safety and reliability analysis, and achieving a complete closed loop from requirements analysis and system design to reliability and safety analysis and system architecture improvement. Attached Figure Description

[0050] Figure 1This is a flowchart illustrating a method for improving aerospace system architecture design based on reliability and security analysis, as proposed in this invention.

[0051] Figure 2 This is a schematic diagram illustrating the aerospace mission design and safety / reliability analysis based on SysML according to the present invention.

[0052] Figure 3 This invention provides a complete system framework diagram for an aerospace system architecture design based on reliability and safety analysis. Detailed Implementation

[0053] This invention provides a method and system for improving aerospace system architecture design based on reliability and safety analysis. It integrates safety and reliability analysis into the design of complex aerospace mission systems using model-based systems engineering (MBSE) methods. Utilizing the element information generated from the aerospace mission system design, it constructs a multi-dimensional fault propagation logic and conducts safety and reliability analysis calculations driven by the model. This not only enables early verification of certain key indicators in aerospace missions but also truly achieves the integration of safety and reliability analysis with system design. Therefore, this invention mainly comprises two parts:

[0054] (1) Integration of space mission design and safety and reliability analysis

[0055] Space missions involve the collaborative operation of multiple systems. Therefore, the design of complex space missions requires not only the layer-by-layer decomposition of the top-level mission, assigning relevant subsystems or functions to corresponding systems for more detailed design, but also maintaining a traceability relationship with initial requirements throughout the design process to ensure that the design meets stakeholder needs. The safety and reliability analysis and verification process must be integrated with the space mission design process to promote iterative improvement of the entire system. This invention utilizes SysML for space mission design and safety and reliability analysis.

[0056] (2) Methods for improving the functional logic architecture

[0057] Due to their high cost and risk, space missions often require the design of corresponding contingency strategies to address potential top-level failure modes. This is to improve mission reliability or reduce the severity of failure consequences and minimize damage. Therefore, when designing space missions, it is necessary to complete detailed designs of contingency strategies for identified typical failure modes and refine the overall mission's operational logic. This provides a reference for further safety and reliability analysis or detailed system design.

[0058] To better understand this invention, the following description, in conjunction with the accompanying drawings and examples, further illustrates the invention. Example 1:

[0059] This invention provides a method for improving the architecture design of aerospace systems based on reliability and security analysis, such as... Figure 1 As shown, it includes:

[0060] S1. Based on the design requirements of aerospace flight missions, determine the aerospace mission system architecture, reliability and safety requirements, and various failure modes, and establish the correlation between the aerospace mission system architecture, reliability and safety requirements, and various failure modes.

[0061] S2. Construct a fault propagation model based on the aforementioned aerospace mission system architecture, reliability and safety requirements, and fault mode correlations;

[0062] S3 constructs simulation test cases based on the fault propagation model while meeting reliability and safety requirements, and tests the aerospace mission system based on the simulation test cases;

[0063] S4. Improve the architecture of the space mission system based on the test results of the space mission system.

[0064] Taking a certain manned space mission as an example, combined with Figure 2 The present invention will now be described in detail.

[0065] Step S1: Based on the design requirements of the aerospace flight mission, determine the aerospace mission system architecture, reliability and safety requirements, and various failure modes, and establish the correlation between the aerospace mission system architecture, reliability and safety requirements, and various failure modes; specifically including:

[0066] ① Capturing and defining top-level reliability and security requirements. By understanding the top-level tasks and combining them with stakeholder expectations, the system design requirements are obtained. From the top-level requirements, the stakeholders' expectations regarding tolerable risks are extracted and transformed into a top-level requirement model itemized by reliability and security requirements.

[0067] ② Decomposition of functional architecture design and reliability and safety requirements for space missions.

[0068] Using a top-level requirements model (including a reliability and safety requirements model) as input, and combining prior knowledge, the space mission is decomposed into multiple different flight phases, and each flight phase is further decomposed into multiple different flight sub-phases or flight operations. For example, when defining the requirements for a manned space mission, based on prior knowledge, stakeholders related to the mission are identified, and their related requirements are defined. Requirements related to safety and reliability are separated out, such as the acceptable level of mission success rate and astronaut safety probability.

[0069] The top-level reliability and safety requirements are broken down into different flight phases, sub-phases, or flight operations to form expectations or corresponding design principles for the reliability and safety of different phases; for example, the key function of engine ignition belongs to the launch vehicle system, while the key function of manned spacecraft environmental maintenance belongs to the manned spacecraft system.

[0070] The detailed requirements are transformed into itemized requirement models, which are then linked to the corresponding flight phases, operational aspects, and top-level requirement models, enabling them to have traceability relationships with the system architecture and stakeholders.

[0071] ③: Decomposition of system architecture design and reliability and security requirements for space missions.

[0072] Identify which subsystems are required to perform each flight phase and operation, construct the system composition of the entire space mission, and assign each flight phase and operation to the corresponding subsystem.

[0073] The top-level reliability and security requirements are decomposed into subsystems to form the expectations and design principles for the reliability and security of each subsystem.

[0074] Establish a requirement model and construct its traceability relationship with the corresponding subsystems and the top-level requirement model.

[0075] ④: Fault mode identification, modeling, and construction of tracing relationships.

[0076] For each captured flight phase or flight operation to be performed, identify the corresponding failure mode;

[0077] The identified fault models are modeled using the Risk Assessment and Modeling Language (RAAML) published by the International System Association, including the definition of name, type, and attributes;

[0078] Once the failure mode is determined to belong to a specific flight phase and subsystem, the system architecture, reliability and safety requirements, and the correlation between each failure mode of the space mission are established.

[0079] Step S2: Construct a fault propagation model based on the aforementioned aerospace mission system architecture, reliability and safety requirements, and fault mode correlations; specifically including:

[0080] ⑤: Top-level design and fault analysis of each subsystem. Using the top-level requirement model and architecture model related to each subsystem as input, further detailed design is carried out, and the fault modes of the subsystems are identified and modeled.

[0081] ⑥: Improve the system's overall failure modes. Use failure analysis methods to comprehensively identify all potential failure modes of the entire system.

[0082] ⑦: Construction of fault propagation logic. Based on the logical structure expressed by the system model and fault model, extract fault-related elements, establish the relationship between fault modes at different levels and at the same level, and form the fault propagation logic of the entire system.

[0083] Step S3 involves constructing simulation test cases based on the fault propagation model while meeting reliability and safety requirements, and then testing the aerospace mission system based on these simulation test cases; specifically including:

[0084] ⑧: Quantitative analysis of safety and reliability. Based on the system's overall mission, flight stages, and the reliability and safety requirements of each system, simulation scenarios with traceability relationships are established, and corresponding safety and reliability analyses are conducted based on fault modes and fault propagation logic.

[0085] Step S4: Based on the test results of the space mission system, improve the architecture of the space mission system to verify the requirements and improve the system, specifically including:

[0086] Compare the qualitative reliability and safety analysis results with the design principles of the space mission system with traceability to verify whether the reliability and safety design principles are verified. If they do not meet the requirements, it is necessary to improve the system functional logic architecture or improve the subsystem design for the failure modes, flight phases or subsystems with traceability to the requirements.

[0087] Compare the quantitative reliability and safety analysis results with the reliability and safety requirements that have a traceability relationship to verify whether they meet the requirements. If they do not meet the requirements, the system functional logic architecture or subsystem design needs to be improved for the failure modes, flight phases or subsystems that have a traceability relationship with the requirements.

[0088] After system improvements are completed, failure modes need to be reanalyzed and reliability and safety analyses conducted until all reliability and safety requirements are met.

[0089] (2) The methods for improving the system's functional logic architecture are as follows:

[0090] Due to their high cost and risk, space missions often require the design of corresponding contingency strategies to address potential top-level system failure modes. This aims to improve mission reliability or mitigate the severity of failure consequences and reduce damage. Therefore, when designing a space mission, it is necessary to complete the detailed design of contingency strategies for identified typical failure modes and refine the overall mission's operational logic. This provides a reference for further safety and reliability analysis or detailed system design. The specific steps are as follows:

[0091] ①: Functional Failure Mode to Emergency Strategy Generation Mechanism. Based on the identified failure modes for each function, and using prior knowledge, corresponding emergency strategies are designed. These emergency strategies are defined using SysML activity diagrams, including each key step in executing the strategy and the judgment criteria. Specifically, branch nodes and decision nodes in the activity diagram are used for definition. Each branch provides a corresponding judgment criterion, which can be a quantitative indicator or a qualitative description. Finally, the consequences of each scenario need to be connected. If the consequence allows the task to continue, this path needs to be connected to the normal activity diagram flow at the next higher level; otherwise, it ends with a terminator.

[0092] ②: Mechanism for Improving Emergency Strategies to Functional Architecture. After designing the emergency strategies for each failure mode, they need to be integrated into the functional architecture to improve the task's operational logic. Each function may have multiple failure modes and emergency strategies. When improving the task logic, the possible order of failure modes must first be determined. If there is a clear order, the emergency strategy corresponding to the most likely failure mode is connected to the original function through a decision node, and its exit point is then connected to the emergency strategy corresponding to the next failure mode through another decision node. If there is no clear order, the original function connects to multiple decision nodes through branch nodes, which in turn connect to all emergency strategies.

[0093] The advantage of this invention is that, while carrying out model-based aerospace mission design, the generated system forward design model is used to complete the safety and reliability analysis of the aerospace mission, ensuring the consistency between the aerospace mission design and the safety and reliability analysis, and realizing a complete closed loop from requirements analysis and system design to reliability and safety analysis and system architecture improvement.

[0094] Example 2:

[0095] Based on the same inventive concept, this invention also provides a system for improving aerospace system architecture design based on reliability and safety analysis, such as... Figure 3 As shown, it includes:

[0096] The relationship determination module is used to determine the aerospace mission system architecture, reliability and safety requirements, and various failure modes based on the aerospace flight mission design requirements, and to establish the correlation between the aerospace mission system architecture, reliability and safety requirements, and various failure modes.

[0097] The fault propagation logic construction module is used to construct fault propagation logic based on the aerospace mission system architecture, reliability and safety requirements, and fault mode correlations.

[0098] The simulation test module is used to construct simulation test cases based on the fault propagation logic while meeting reliability and safety requirements, and to test the aerospace mission system based on the simulation test cases.

[0099] An improvement module is used to improve the architecture of the space mission system based on the test results of the space mission system.

[0100] Each module in this embodiment is used to implement the aerospace system architecture design improvement method based on reliability and security analysis in Example 1. For specific implementation, please refer to Example 1, which will not be repeated here.

[0101] Example 3

[0102] Based on the same inventive concept, this invention also provides a computer device, which includes a processor and a memory. The memory stores a computer program, which includes program instructions. The processor executes the program instructions stored in the computer storage medium. The processor may be a Central Processing Unit (CPU), or other general-purpose processors, digital signal processors (DSPs), application-specific integrated circuits (ASICs), field-programmable gate arrays (FPGAs), or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. It is the computing and control core of the terminal, suitable for implementing one or more instructions, specifically suitable for loading and executing one or more instructions in the computer storage medium to implement corresponding method flows or corresponding functions, thereby realizing the steps of the aerospace system architecture design improvement method based on reliability and security analysis in the above embodiments.

[0103] Example 4

[0104] Based on the same inventive concept, this invention also provides a storage medium, specifically a computer-readable storage medium (Memory), which is a memory device in a computer device used to store programs and data. It is understood that the computer-readable storage medium here can include both the built-in storage medium in the computer device and extended storage media supported by the computer device. The computer-readable storage medium provides storage space that stores the terminal's operating system. Furthermore, this storage space also stores one or more instructions suitable for loading and execution by a processor. These instructions can be one or more computer programs (including program code). It should be noted that the computer-readable storage medium here can be high-speed RAM or non-volatile memory, such as at least one disk storage device. The processor can load and execute one or more instructions stored in the computer-readable storage medium to implement the steps of the aerospace system architecture design improvement method based on reliability and security analysis in the above embodiments.

[0105] Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

[0106] Those skilled in the art will understand that embodiments of this application can be provided as methods, systems, or computer program products. Therefore, this application can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, this application can take the form of a computer program product embodied on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code.

[0107] This application is described with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of this application. It will be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, generate instructions for implementing the flowchart... Figure 1 One or more processes and / or boxes Figure 1 A device that provides the functions specified in one or more boxes.

[0108] These computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing device to function in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1 The function specified in one or more boxes.

[0109] These computer program instructions may also be loaded onto a computer or other programmable data processing equipment to cause a series of operational steps to be performed on the computer or other programmable equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable equipment for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.

[0110] The above are merely embodiments of the present invention and are not intended to limit 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 the claims of the present invention pending approval.

Claims

1. A method for improving the architecture design of aerospace systems based on reliability and safety analysis, characterized in that, include: Based on the design requirements of aerospace flight missions, the aerospace mission system architecture, reliability and safety requirements, and various failure modes are determined, and the correlation between the aerospace mission system architecture, reliability and safety requirements, and various failure modes is established. Based on the correlation between the aforementioned aerospace mission system architecture, reliability and safety requirements, and failure modes, a fault propagation logic is constructed. Based on the fault propagation logic, simulation test cases are constructed while meeting reliability and safety requirements, and the aerospace mission system is tested based on the simulation test cases. The architecture of the space mission system is designed based on the test results of the space mission system; The process involves determining the space mission system architecture, reliability and safety requirements, and various failure modes based on the design requirements of the spaceflight mission, and establishing the correlation between the space mission system architecture, reliability and safety requirements, and various failure modes, including: The top-level requirements for the system architecture and reliability and safety of the space mission are determined according to the design requirements of the space flight mission. Based on the functions to be achieved in a spaceflight mission, several flight phases are determined, and the top-level requirements for reliability and safety are decomposed into each flight phase. Based on the flight phase, the subsystems included in the space mission system are determined, and the top-level reliability and safety requirements are decomposed into each flight phase and each subsystem to obtain the reliability and safety requirements of each subsystem. Fault mode identification is performed based on the flight phase to obtain the fault mode; Based on each flight phase, subsystems are established, along with their reliability and safety requirements and the relationships between various failure modes. The flight phase is a multi-level flight phase, including at least a primary flight phase and sub-flight phases under the primary flight phase; both the primary flight phase and the sub-flight phase include corresponding flight operations. The fault propagation logic, constructed based on the correlation between the aerospace mission system architecture, reliability and safety requirements, and failure modes, includes: Based on the flight operations to be performed during the flight phases corresponding to each subsystem in the aforementioned space mission system architecture, the functions performed by each subsystem and the modules corresponding to those functions are determined. The failure modes are improved based on the flight operations corresponding to each module and flight phase, and a failure propagation model is obtained by using risk assessment and modeling language. Based on the modules, fault propagation models, and reliability and safety requirements of each subsystem, the relationships between each fault mode, aerospace flight mission design requirements, aerospace mission system, subsystems, and modules are determined. Based on the aforementioned failure modes, spaceflight mission design requirements, space mission systems, subsystems, and the relationships between modules, the fault propagation logic of the entire space mission system is constructed.

2. The method as described in claim 1, characterized in that, The top-level requirements for reliability and safety are determined based on the design requirements of the aerospace flight mission, including: Based on the items involved in the design requirements of the spaceflight mission and the expected risks of the spaceflight mission, the top-level requirements for reliability and safety are obtained.

3. The method as described in claim 1, characterized in that, The first-stage flight phase includes at least the launch into low Earth orbit phase and / or the low Earth orbit flight phase; the sub-flight phases include at least the engine start-up sub-phase and / or the first-stage engine operation sub-phase of the launch vehicle.

4. The method as described in claim 1, characterized in that, The failure mode is improved based on the flight operations corresponding to each module and flight phase, and a failure propagation model is obtained by using risk assessment and modeling language, including: The basic model for reliability and security analysis is defined using a risk assessment and modeling language, and a basic type library is formed in the SysML system modeling language environment. An iterative fault analysis method is used for each flight phase or flight operation to determine whether there are new fault modes in the space mission system and its subsystems. If so, the fault modes are improved based on the new fault modes. A fault propagation model is obtained by modeling using the base model and the fault modes.

5. The method as described in claim 1, characterized in that, Based on the fault propagation logic, simulation test cases are constructed while meeting reliability and safety requirements. The space mission system is then tested based on these simulation test cases, including: Establish simulation use cases that are related to the top-level requirements, the reliability and safety requirements of each flight phase, and each subsystem; Based on the fault propagation model, simulation analysis is performed using various use cases to determine the reliability and security analysis results. Based on the results of each reliability and security analysis, the system architecture and subsystems of the space mission are compared to improve the functional logic architecture of the system or improve the design of each subsystem. The simulation analysis is based on qualitative analysis using Failure Mode and Effects Analysis (FMEA) and / or quantitative analysis using Fault Tree Analysis (FTA).

6. The method as described in claim 5, characterized in that, The results of each reliability and security analysis are compared with the aerospace mission system architecture and each subsystem to improve the system's functional logic architecture or the design of each subsystem, including: Compare the qualitative reliability and safety analysis results with the design principles of the aerospace mission system to verify whether they comply with the reliability and safety design principles. If they do not comply, it is necessary to improve the system functional logic architecture or improve the subsystem design for failure modes, flight phases or subsystems that are related to the requirements. The quantitative reliability and safety analysis results are compared with the reliability and safety requirements of the space mission system to verify whether they meet the requirements. If they do not meet the requirements, the system functional logic architecture or subsystem design needs to be improved for failure modes, flight phases or subsystems that are related to the requirements.

7. The method as described in claim 6, characterized in that, The improvement of the system's functional logic architecture or the enhancement of subsystem design include: Based on the identified fault modes and prior knowledge, the corresponding emergency response strategies are determined. The emergency response strategies corresponding to each failure mode are integrated into the aerospace mission system architecture to improve the mission's operational logic.

8. A system for improving the architecture design of aerospace systems based on reliability and safety analysis, characterized in that, include: The relationship determination module is used to determine the aerospace mission system architecture, reliability and safety requirements, and various failure modes based on the aerospace flight mission design requirements, and to establish the correlation between the aerospace mission system architecture, reliability and safety requirements, and various failure modes. The fault propagation logic construction module is used to construct fault propagation logic based on the correlation between the aerospace mission system architecture, reliability and safety requirements, and fault modes. The simulation test module is used to construct simulation test cases based on the fault propagation logic while meeting reliability and safety requirements, and to test the aerospace mission system based on the simulation test cases. An improvement module is used to design the architecture of the space mission system based on the test results of the space mission system; The relationship determination module, based on the design requirements of the aerospace flight mission, determines the aerospace mission system architecture, reliability and safety requirements, and various failure modes, and establishes the correlation between the aerospace mission system architecture, reliability and safety requirements, and various failure modes, including: The top-level requirements for the system architecture and reliability and safety of the space mission are determined according to the design requirements of the space flight mission. Based on the functions to be achieved in a spaceflight mission, several flight phases are determined, and the top-level requirements for reliability and safety are decomposed into each flight phase. Based on the flight phase, the subsystems included in the space mission system are determined, and the top-level reliability and safety requirements are decomposed into each flight phase and each subsystem to obtain the reliability and safety requirements of each subsystem. Fault mode identification is performed based on the flight phase to obtain the fault mode; Based on each flight phase, subsystems are established, along with their reliability and safety requirements and the relationships between various failure modes. The flight phase is a multi-level flight phase, including at least a primary flight phase and sub-flight phases under the primary flight phase; both the primary flight phase and the sub-flight phase include corresponding flight operations. The fault propagation logic constructed in the propagation logic construction module, based on the correlation between the aerospace mission system architecture, reliability and safety requirements, and failure modes, includes: Based on the flight operations to be performed during the flight phases corresponding to each subsystem in the aforementioned space mission system architecture, the functions performed by each subsystem and the modules corresponding to those functions are determined. The failure modes are improved based on the flight operations corresponding to each module and flight phase, and a failure propagation model is obtained by using risk assessment and modeling language. Based on the modules, fault propagation models, and reliability and safety requirements of each subsystem, the relationships between each fault mode, aerospace flight mission design requirements, aerospace mission system, subsystems, and modules are determined. Based on the aforementioned failure modes, spaceflight mission design requirements, space mission systems, subsystems, and the relationships between modules, the fault propagation logic of the entire space mission system is constructed.

9. A computer device, characterized in that, include: One or more processors; The processor is used to store one or more programs; When the one or more programs are executed by the one or more processors, the method for improving the aerospace system architecture design based on reliable security analysis as described in any one of claims 1 to 7 is implemented.

10. A computer-readable storage medium, characterized in that, It contains a computer program, which, when executed, implements the aerospace system architecture design improvement method based on reliability and security analysis as described in any one of claims 1 to 7.

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