CN115659516A

CN115659516A - MBSE-based integrated aircraft design method and system

Info

Publication number: CN115659516A
Application number: CN202211385314.9A
Authority: CN
Inventors: 魏承; 张玉彤; 岳程斐; 曹喜滨
Original assignee: Harbin Institute of Technology
Current assignee: Harbin Institute of Technology
Priority date: 2022-11-07
Filing date: 2022-11-07
Publication date: 2023-01-31

Abstract

The invention provides an MBSE-based integrated aircraft design method and system, which comprises the steps of firstly analyzing task requirements of an integrated aircraft, then constructing a logic architecture of a carrying section and a rail entering section, and constructing a flow relation among different subsystems; the structure, parameters and behaviors of the subsystem are refined, and the flow relation among all physical components is perfected; constructing an alternative physical original type spectrum library, integrating a domain model into a system architecture model, developing dynamic simulation to verify system operation indexes, adjusting functions, structural models and parameters in a design scheme, improving system performance, and finally freezing the system design and type selection scheme; on the premise of meeting the reliability, the invention reasonably reduces the equipment redundancy to improve the load-mass ratio and the load ratio of the aircraft, and simultaneously constructs the composition, parameters and behaviors of each subsystem in a complex state, thereby facilitating design and optimization personnel to carry out quantitative and qualitative evaluation, statistical analysis, demand change and management and field design on the system and improving the overall design capability.

Description

MBSE-based integrated aircraft design method and system

Technical Field

The invention belongs to the technical field of system engineering, and particularly relates to an MBSE-based integrated aircraft design method and system.

Background

The integrated design of rocket, satellite and load is realized by the satellite-rocket integrated aircraft, the satellite-rocket integrated aircraft is composed of a multi-stage power system and an autonomous in-orbit spacecraft system, the direct in-orbit of satellite control and carrying is realized according to tasks, the proportion of effective load can be obviously improved compared with the traditional design, meanwhile, the multi-stage solid power system is adopted, the satellite-rocket integrated aircraft can be stored for a long time, the rapid deployment capability is realized, the cost is lower, and the rapid space response capability is greatly improved.

The satellite-rocket-borne integrated aircraft is a complex system, and the integrated design does not clearly distinguish the load, the platform and the carrier rocket final stage, so that the excessive redundancy of system resources can be reduced, and the system design is more complex. The complexity of system design is represented by: the system design stage has more and multidisciplinary requirements, and the system design ensures that all the requirements are met; the system composition structure is more complex, the division of system load, platform and the like is not clear any more, and the problem to be solved in the design stage is also the problem of how to design a structure which meets the requirement and simultaneously reduces excessive redundancy; the system has various use scenes, different systems need to work in a plurality of system stages, the system scheduling behavior is complex, and the system behavior in the design stage is ensured to be reasonable, which is also one of the difficulties difficult to solve in the traditional system engineering; the system has the advantages that the interfaces of the integrated system are inconsistent, the integrated system has a larger number of interfaces which are cross-system, the consistency of the transmission types of the interfaces of the systems is ensured, the errors of the system design can be reduced, and the cost is saved.

In view of the above common problems of complex system design, advanced model-based system engineering (MBSE) has been developed abroad to deal with the problems. MBSE follows a traditional system engineering flow: requirements, functionality, logic, physics, and unifying models throughout, building a system model in a form that is easily understood by designers and stakeholders. Three contents of the MBSE are a modeling language, a modeling tool and a modeling method, sysML is generally used as the modeling language, the advantages of an object-oriented method and a process-oriented method are integrated, and system requirements, system scenes, system behaviors, system components, system parameters and the like are designed and displayed in a visual model form so as to meet the requirements of stakeholders of all parties; meanwhile, the executable characteristic of the system enables each stage of system design to be simulated to different degrees so as to verify early and carry out early design iteration, and the system cost is reduced. The special behavior and state simulation in the MBSE can verify whether the system behavior design meets the requirements or not, parameter simulation is also performed to a certain degree, early quality, power, cost, reliability and other parameter verification can be performed, meanwhile, the unique model can ensure the consistency of interfaces among systems, and the interface errors of the traditional design are reduced.

The MBSE has the advantages of being combined, an integrated design theory and method are provided, and an idea is provided for integrated complex system design. In the model-based integrated design, the advantages of MBSE design are fully utilized, the integrated design idea is fully exerted in the system design, behavior coupling analysis is carried out in behaviors, the function redundancy is structurally removed, meanwhile, the early-stage reliability design can be carried out, and the problem that the system reliability is insufficient due to the fact that the redundancy is too low is avoided. And performing system-level simulation, and performing design balance analysis according to a simulation result so as to improve the indexes of the system load-mass ratio and the load ratio. The complex system behaviors and various system states of the integrated aircraft can also be verified by using SysML model simulation so as to clarify the interaction and interface between complex systems. And finally, constructing a system model capable of reflecting the actual structure and behavior of the integrated aircraft.

The existing aircraft design method is mainly embodied in structural parameter modeling of a system, or structural and behavioral modeling is carried out under a single subsystem, although the system engineering process is met, the interaction among different subsystems is less researched, and the whole process from launching to entering into orbit to execute tasks of the aircraft is rarely involved.

Disclosure of Invention

Aiming at the defects in the prior art, the invention provides an MBSE-based integrated aircraft design method and system, which are used for constructing a satellite-rocket-borne integrated complex aircraft so as to solve the problems of complex structure of an aircraft system, more interaction among components and system behavior switching in different flight stages.

The invention is realized by the following technical scheme:

an MBSE-based integrated aircraft design, optimization and evaluation method comprises the following steps:

the method specifically comprises the following steps:

step A: performing integrated aircraft task demand analysis after the task demand is obtained;

analyzing the task requirements of the integrated aircraft, constructing an operation scene in SysML according to the task idea to sort out the design requirements of the system, decomposing and clustering the functional requirements of the integrated aircraft composition system, combining the same functions of different components, analyzing the functions of subsystems at all levels under the MBSE flow and designing behaviors and test cases;

and B: constructing a logic architecture;

constructing a logic architecture of a carrying section and a track entering section, decomposing and distributing functions and behaviors, defining a top subsystem according to the requirements of all levels of subsystems of the integrated aircraft, defining a parameter library into a corresponding packet, and constructing flow relations and interfaces between different subsystems according to interaction among behaviors;

and C: designing a physical architecture;

the subsystem structure, parameters, behaviors and physical architecture of the integrated aircraft are refined; perfecting parameter modeling, and constructing a parameter diagram to verify system indexes; establishing the state and behavior of each subsystem, and perfecting the flow relationship among the physical components and defining interfaces in detail;

step D: designing and selecting a type spectrum library;

constructing an alternative physical original type spectrum library, integrating the alternative physical original type spectrum library into a type spectrum package corresponding to a system architecture in an example mode, selecting a corresponding type spectrum original and verifying a system static index for a given index;

step E: performing combined simulation verification;

integrating the domain model to a system architecture model, and performing dynamic simulation to verify system operation indexes;

step F: optimizing the system design scheme, adjusting functions, structural models and parameters in the design scheme according to the simulation result, and finally freezing the system design and model selection scheme.

Further, the air conditioner is provided with a fan,

in the step a, the method specifically comprises the following steps:

step A1: determining task requirements of the integrated aircraft and constructing a model-based requirement library by using an MBSE (multi-component modeling system) modeling language;

step A2: constructing an integrated aircraft professional glossary;

step A3: analyzing and refining system requirements, obtaining system design requirements from a system task scene designed in an operation concept (ConOps), further obtaining the requirements of each level of aircraft system, constructing a requirement diagram and generating a requirement matrix;

step A4: constructing each system behavior of the aircraft, and performing functional clustering on the behaviors and component mapping to obtain the system requirement which is in accordance with the integrated design after redundancy optimization;

further, the air conditioner is provided with a fan,

the logic architecture design specifically comprises: designing a white box model with functions and structures meeting requirements;

in the step B, the following steps are specifically included:

step B1: constructing a top layer model of a track entering section and a carrying section, defining interaction between the top layer model and the carrying section, and defining parameters;

and step B2: respectively constructing a structure model of a logic architecture of the next stage for the track entering section and the carrying section;

and step B3: distributing the behavior requirements to each subsystem, and defining the composition, state and behavior of different subsystems;

and step B4: and defining the interactive relation among different subsystems according to the behavior requirements.

Further, the air conditioner is provided with a fan,

the physical architecture is specifically as follows: a physical model which corresponds to the white box model of the logic architecture in the step B and enables the system to specifically realize functions comprises physical components, mechanisms and equipment;

in the step C, the following steps are specifically included:

step C1: each subsystem is refined to a physical composition model, the requirements are distributed, and the requirement coverage is verified;

and C2: completely designing the behavior of each subsystem;

and C3: and defining the interaction of the physical components in the subsystems, distributing the interaction between the subsystems into physical components, and simultaneously completely defining the interactive flow and the ports.

Further, the air conditioner is provided with a fan,

in the step D, the following steps are specifically included:

step D1: defining required parameters of a physical original which can construct a spectrum library;

step D2: carrying out instance definition on each physical original according to the existing model, and assigning and storing the parameters;

and D3: generating an example table of the type spectrum;

step D4: according to the assigned task requirements, carrying out instance selection and parameter simulation on the type spectrum, and verifying whether the selected type spectrum set can meet the indexes;

the type spectrum library specifically comprises the following components: and modeling the commercial off-the-shelf COTS or the existing model of the available physical component, integrating the modeled physical component into a system model, taking the model as a part of the model in an example form, selecting the model in system verification, and further calculating parameters.

Further, the air conditioner is provided with a fan,

in the step E, the method specifically includes the following steps:

step E1: constructing models in each field, and performing reconstruction meeting integration according to MBSE model specifications;

step E2: according to the characteristics of different models, model integration is carried out;

step E3: performing joint simulation to verify the dynamic performance index of the system;

the field model specifically comprises: the non-MBSE model meeting various simulations of the operation of the aircraft comprises a ballistic calculating model, a structural analysis model and a controller model;

further, the air conditioner is provided with a fan,

in step F, the method specifically comprises the following steps:

step F1: by adjusting the parameters of the physical components, parameter sets capable of improving indexes such as system carrier-to-mass ratio, load ratio and the like are searched on the premise of meeting the requirements and used as system parameter optimization;

step F2: aiming at the flow optimization related to the system behavior, performing behavior optimization according to a sequence diagram and a time line diagram obtained by simulation so as to increase the response capability of the system;

step F3: and after an optimization scheme which is in line with the expectation is obtained in the feasible interval, freezing the system design and the model selection scheme.

An integrated aircraft design, optimization and evaluation system based on MBSE:

the system comprises: the system comprises a task demand analysis subsystem, a logic architecture subsystem, a physical architecture subsystem, a pattern library design analysis subsystem, a simulation verification subsystem and a result output subsystem;

the task demand analysis subsystem is used for analyzing the task demand of the integrated aircraft after the task demand is obtained;

analyzing the task requirements of the integrated aircraft, decomposing and clustering the functional requirements of the integrated aircraft composition system, analyzing the functions of subsystems at all levels under an MBSE flow, and designing behaviors and test cases;

the logic architecture subsystem is used for designing a logic architecture;

constructing a logic architecture of a carrying section and a rail entering section, decomposing and distributing functions and behaviors, defining a top subsystem according to the requirements of all levels of subsystems of the integrated aircraft, defining a parameter library into corresponding packages, and constructing flow relations among different subsystems;

the physical architecture subsystem is used for designing a physical architecture;

the subsystem structure, parameters, behaviors and physical architecture of the integrated aircraft are refined; perfecting parameter modeling, and constructing a parameter diagram to verify system indexes; establishing the state and behavior of each subsystem, and perfecting the flow relationship among the physical components;

the model spectral library design analysis subsystem is used for designing and selecting a model spectral library;

the simulation verification subsystem is used for performing joint simulation verification;

and the result output subsystem is used for optimizing a system design scheme, adjusting functions, structural models and parameters in the design scheme according to a simulation result, and finally freezing the system design and model selection scheme.

An electronic device comprising a memory storing a computer program and a processor implementing the steps of any of the above methods when the processor executes the computer program.

A computer readable storage medium storing computer instructions which, when executed by a processor, implement the steps of any of the above methods.

The invention has the beneficial effects

The invention solves the problem that the joint design of the overall design stage of the large-scale complex integrated aircraft lacks an implementation flow and a technical scheme, and the invention carries out functional design and coupling analysis and early verification to find the defects of the system design during the overall design of the system, thereby ensuring the consistency of a large number of system interfaces and simultaneously carrying out parameter iteration and optimization, optimizing the performance of the system and greatly reducing the system iteration cost and the research and development period.

The invention combines the advantages of MBSE to construct an integrated aircraft complete and standardized model, reasonably reduces equipment redundancy on the premise of meeting reliability to improve the load-mass ratio and the load ratio of the aircraft, simultaneously constructs the composition, parameters and behaviors of each subsystem in a complex state, simulates to verify each index, forms a complete integrated aircraft architecture model on the basis, and is convenient for design and optimization personnel to carry out quantitative and qualitative evaluation, statistical analysis, demand change and management and field design on the system, thereby improving the overall design capability. .

Drawings

FIG. 1 is a flow chart of the present invention;

FIG. 2 is a task overall demand graph;

FIG. 3 is a SysML glossary of definitions of partial terms of art;

FIG. 4 is a SysML glossary of partial parameter relationships;

FIG. 5 is a schematic diagram of automatic demand-to-constraint conversion;

FIG. 6 is a flow chart of system behavior demand allocation and function consolidation;

FIG. 7 is a diagram of an assignment matrix describing the assignment of partial behaviors to system components;

FIG. 8 is a usage diagram depicting a fast response domain;

FIG. 9 is a diagram illustrating an integrated aircraft overhead structure module definition;

FIG. 10 is a diagram illustrating an in-orbit spacecraft logical structure module definition;

FIG. 11 is a state machine diagram of an orbiting spacecraft executing a planet to control an arrow or controlling the orbiting spacecraft itself;

FIG. 12 is a control system physical architecture module definition diagram;

FIG. 13 is an example of a profile and a table of profiles for a thruster portion assembly;

FIG. 14 is a diagram illustrating integration of a multi-domain physics model with a system architecture model.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

The invention provides an integrated aircraft design method and system based on MBSE (minimum Block error), which comprises the steps of constructing a model of an aircraft with a carrying section and an orbit entering section integrated integrally, applying the MBSE according to a system engineering process, carrying out behavior analysis and clustering from the requirement, establishing a logical model of a system for reducing excessive redundancy, refining the logical model into a physical model of the system, constructing a physical component type spectrum library and a field system model to carry out various indexes of the system simulation verification system, and carrying out parameter optimization to improve the performance of the system. Finally, an integrated aircraft model meeting various indexes of the system is generated, and designers in each stage can obtain required design information from respective visual angles in a verifiable manner.

An integrated aircraft design, optimization and evaluation method based on MBSE comprises the following steps:

the method specifically comprises the following steps:

performing integrated aircraft mission requirement analysis, and constructing operation scenes (ConOps) in SysML to comb system design requirements; decomposing and clustering functional requirements of an integrated aircraft composition system, analyzing the functions of subsystems at all levels under an MBSE flow, and designing behaviors and test cases;

and B: designing a logic architecture;

constructing a logic architecture of a carrying section and a rail entering section, decomposing and distributing functions and behaviors, defining a top subsystem according to the requirements of all levels of subsystems of the integrated aircraft, defining a parameter library into corresponding packets, and constructing a flow relation between different subsystems;

and C: designing a physical architecture;

step D: designing and selecting a type spectrum library;

step E: performing combined simulation verification;

In the step (A), the first step is carried out,

the system design requirements are specifically as follows: drawing the detailed performance requirement of the system from the load-mass ratio and load ratio constraint specified in the task design index and the performance index of the rapidity of the system; the aircraft system is designed to meet the functional sequence of the mission, i.e. the functional requirements that the system should have.

The functional decomposition specifically comprises the following steps: obtaining the function requirements of the system to meet the indexes and the function requirements of subsystems at all levels obtained by the function flow design;

the functional clustering specifically comprises the following steps: preliminarily obtaining the functions of each system and each subsystem according to a traditional design method, then positioning the same functions of different systems according to an integrated design idea, and combining the functions to reduce function overlapping;

the MBSE flow is a part of the system model by constructing a demand model and a design case in the system model according to a system function thought based on the model.

In the step a, the method specifically comprises the following steps:

establishing and dividing form documents of the task requirements determined by negotiation of the overall design department, and constructing an MBSE requirement graph in an importing mode provided by a SysML tool so as to take the task requirements as a part of a system model in a text model mode.

The load ratio, the quick response requirement and the like of the overall task requirement of the system should be taken as top-level requirements. The MBSE modeling language is selected as SysML language.

A task overall demand graph (REQ) is constructed according to FIG. 2, a task most attention demand comprising a carrier-to-mass ratio, a load-to-load ratio and a quick response is constructed, an ID value and a text content are defined, a top-level demand generally has a larger integer or letter ID such as '1', a demand of a subsequent derivative refinement is generally set to have ID such as '1.1' to indicate classification, and meanwhile, the demand ID ensures the uniqueness of the demand.

Step A2: constructing an integrated aircraft professional glossary;

constructing a Glossary (Glossary) in the SysML language; constructing a SysML term table representing professional terms as shown in FIG. 3 can avoid language ambiguity with designers of all subsystems, define a load ratio as load quality, define various nouns including integrated aircrafts, have the advantages that the terms are underlined and highlighted during modeling and can display meanings after a mouse is placed, and meanwhile, the complete term table can verify whether spelling errors exist by using a confirmation function;

constructing a glossary of terms representing mathematical relationships as in FIG. 4, constructing mathematical terms such as "no exceed" such that it has a mathematical meaning of "≦" and requirements written and assigned in a specified format may enable automatic translation of requirements into constraints and automatic verification,

for example, the index is written into the requirement with the quality less than 100kg according to the format, meanwhile, the parameter carrier-to-mass ratio of the system model is established to satisfy the requirement,

the mathematical constraint of "quality <100" is automatically generated in SysML as in fig. 5, enabling demand autoverification and simultaneous changes of demand changes to the model.

Step A3: analyzing and refining system requirements, obtaining system design requirements from a system task scene designed in an operation concept (ConOps), further obtaining the requirements of each level of aircraft system, constructing a requirement diagram and generating a requirement matrix; the specific implementation of step A3 is described below with reference to fig. 6:

taking the task requirements obtained in the step A1 as an input starting point, constructing a system operation concept (ConOps), and mainly performing interaction analysis, system task switching, system task flow design and the like of an aircraft system and external systems such as a remote control and remote measurement center to perform task analysis and define functional requirements; the task flow is refined by comprehensively utilizing the use diagram, the activity diagram, the module definition diagram and the sequence diagram, and then flow analysis is carried out to obtain a series of functions and performance requirements of the system and the subsystems, if a control system can control the function requirements of a carrying section and a rail entering section, the requirements are gradually refined to a subsystem level, and then the requirements, particularly the function requirements, of each subsystem are drawn; and constructing a system use case diagram, constructing an integrated aircraft use scene case according to task requirements, and designing a system test case.

And constructing use cases of the integrated aircraft system by using the use case diagram of the SysML, wherein the use cases comprise use scenes such as launching, orbit entering, task executing and the like, constructing an interactive relation with an operator, and constructing a test case to verify the rapidity index.

For example, fig. 8 shows that an integrated aircraft quick response case is constructed, a quick response task includes quick test, quick benchmark determination, quick transmission and quick deployment sub-cases, the system boundary of the cases is designed to be the integrated aircraft, and operators related to different cases are respectively a command center, a remote control and remote measurement system, transmission maintenance personnel and the like. Through the design use case, the external visible service provided by the system is clear, and the executor triggering and participating in the task is determined.

Step A4: constructing each system behavior of the aircraft, and carrying out functional clustering on the demand, the behavior and the component mapping to obtain the demand of the system which accords with the integrated design after redundancy optimization;

the redundancy optimization conforming to the integrated design specifically comprises the following steps: the aircraft with the satellite-rocket-borne integrated design controls the carrying section through the orbit entering section, and particularly reduces the structural redundancy of repeated functions under the condition of meeting the system requirements by combining the same functions of different systems, particularly combining the electric and control systems of the last stage of the carrying section as a core.

Designing system behaviors according to subsystem requirements, and constructing a relationship between the requirements and the behaviors, for example, a control system has a function of controlling a carrying section and a track entering section, so that the control system has states of a launching track entering stage and a task stage, constructs a state machine diagram, and constructs corresponding behaviors in the states, for example, ignition separation of the carrying section is controlled in the track entering stage, a posture and orbit control system is controlled in the task stage, and the requirements are distributed to the behaviors;

design comprehensive iteration is carried out, system constituent elements are preliminarily defined, functional requirements are distributed to obtain a functional architecture, a behavior-design matrix is generated by utilizing a system modeling language and tools as shown in fig. 7, subsystem function combination and structure redundancy removal are carried out, new system function analysis distribution is carried out to carry out iterative design, and finally an integrated logic functional architecture design scheme which reduces excessive redundancy and meets the functional requirements of the system is obtained.

If the control system composition is defined according to the control system behaviors, the control execution mechanisms of the carrying section and the rail entering section are defined by using the module definition diagram, and the interaction relation between the carrying section and the rail entering section is defined by using the internal module diagram, so that the rocket-borne computer required to interact by the carrying section control system is combined to the satellite-borne computer, and the structure and the interaction of the control system and the satellite-borne data management system are constructed.

In the step B, the following steps are specifically included:

step B1: constructing a top layer model of a rail entering section and a carrying section, defining interaction between the rail entering section and the carrying section, and defining parameters of the rail entering section and the carrying section;

the top layer model specifically comprises: the method is characterized in that a system and subsystem structure block is constructed by using a module definition diagram (BDD) of SysML, corresponding parts do not need to be completely defined, the structure and behavior definition of a white box can be performed by only defining the name of the structure or behavior by using the advantages of MBSE modeling, the definition of interaction mainly comprises a stream and a port, and the specific type and content of the interaction can not be specified when the definition is not determined.

The specific method for defining interaction and parameters is as follows: building a system top structure model by using a module definition diagram (BDD), wherein the BDD comprises an integrated spacecraft and an orbit segment and a carrying segment which are arranged below the spacecraft, and building an internal BDD to define the interaction between the orbit segment and the carrying segment; other attributes of the inbound and carrier segments are defined, such as value attributes of parameters such as mass power, and the status of the inbound segment.

The logic architecture design specifically comprises: designing a white box model with functions and structures meeting requirements; enabling it to describe the system implemented; the white box model constructed here focuses on the subsystems of the system and the interaction among the subsystems, and the behaviors that the subsystems can realize; and step B2: respectively constructing a structure model of a logic architecture of the next stage for the track entering section and the carrying section;

according to the analysis of the overall design knowledge and the requirements, a module definition diagram is constructed as shown in FIG. 10, and control systems of different sections, data management systems of a carrying section, load systems and other related subsystems are defined; constructing an internal block diagram to define an interactive relationship between the control system and the data management system, and distributing the interaction of the step A1 to the defined corresponding interaction;

and defining flow information corresponding to interaction, including port names, information flow or physical flow transmitted by the interaction flow, and the like, for example, a sensitive element under a control system of a carrying section and a rail entering section transmits measurement data to a data management system of the carrying section, and the data management system transmits a control instruction of an actuating mechanism of a corresponding control system. The flow and interface definitions herein need not be specified to a specific type of detail, and may simply be replaced with a block of interfaces or flow types, named to specify content.

And step B3: distributing the behavior requirements to each subsystem, and defining the states and behaviors of different subsystems;

the method comprises the steps of distributing requirements and functions to a system structure model by using the distribution relation of SysML to realize requirement coverage, and specifically modeling defined system behaviors, wherein the defined system behaviors comprise the states of the system and behaviors in different states, and interactive combined behaviors among multiple subsystems are represented by 'signals'.

The state machine diagram of the orbiting spacecraft constructed as shown in fig. 11, the orbiting spacecraft is responsible for controlling the carrier segment during the orbit and controlling the orbit during the orbit and meeting the load work requirement during the mission.

Based on the method, different states and executed behaviors of different systems are built, the emphasis is on state and switching, the flow of the behaviors may not need to be detailed to how the behaviors are implemented, for example, the measurement sensing behaviors of sensitive elements are defined as basic activities of an activity diagram, and the detailed behaviors of measuring the star sensor when the star sensor is started do not need to be defined downwards, and the detailed behaviors are usually designed in a physical phase.

According to the behavior among the cross-subsystems, the interaction existing among different subsystems is determined, port and flow modeling is carried out on the subsystems with the relationship, the interaction among the different subsystems is achieved, meanwhile, the activity of the subsystems is refined, and the ports through which signals are transmitted and received are specified in an activity diagram.

If the control system controls the carrying section to be separated, the state of the carrying section is changed into a separated state from work, the change of the state is triggered by signals on different state connecting lines of a state machine diagram, and the signals are given by the control system and the ports of the carrying section and the track entering section through which the signals are transmitted need to be specified.

The complete activity of the system at the level, namely the behavior logic architecture of the system, is obtained by continuously constructing the behavior state and interaction of the system

The physical architecture is specifically as follows: the white box model corresponding to the logic architecture in the step B enables the system to specifically realize physical models of functions, including physical components, mechanisms, equipment and the like, and the physical models form an actual system;

in step C, the method specifically comprises the following steps:

as shown in fig. 12, the structure of the control system is detailed, and the control system includes a sensing element and an actuator, where the sensing element includes a star sensor, a gyroscope, and the like; and constructing a physical component structure block and a parameter relation, and further distributing the requirements of the subsystems, so that the system requirements can be verified by actual composition, and verifying whether the system requirements are all verified by utilizing a requirement relation matrix generated by an MBSE tool.

And step C2: completely designing the behavior of each subsystem;

the behavior of the subsystem is distributed to the physical components, the behavior executed by the system is realized by the basic behavior of the physical components according to different states and interaction relations, for example, a sensitive original and an execution mechanism of the control system have standby, working and failure states, the standby or working behavior is executed in different states, the corresponding system behavior is executed such as executing orbital transfer, detailed design is carried out such as controlling the track execution mechanism to be started and shut down, controlling the attitude execution system to carry out attitude adjustment, and data transmission between the corresponding components and the satellite-borne computer.

Meanwhile, it is necessary to define how to switch backup components after some components fail to ensure the normal operation of the system, which is also the content of the MBSE that needs to be considered heavily about the normal operation of the system and is an advantage over the traditional system engineering.

The complete definition of the flow and the port is specifically as follows: the complete mode of the stream and the port is defined in the SysML, the complete mode comprises the port type and the type of the transmission stream, and the error that the port definition is inconsistent, which is common in the traditional system engineering, is avoided by modeling and defining each port in detail.

The specific method in step C3 is: according to the behavior interaction of the physical components under the subsystem, the interaction relation between the physical components is defined, including the relation between the ports and the streams, and meanwhile, the ports and the streams of the physical components are completely defined. If the attitude sensitive original element is connected with the satellite-borne computer through a cable, the system is composed of a bilateral port and information flow in a SysML model, the port type is defined as a proxy port, the transferred attitude measurement attribute is defined, the information flow is defined as an item flow (item flow) type, the transferred information type is designated as a corresponding attitude measurement attribute, and the consistency of the types between the port and between the corresponding flows is ensured. Furthermore, the type of the value attribute, such as the attitude measurement attribute, should be stored in a special SysML package for value attribute management.

In step D, the type spectrum library specifically comprises: and modeling the commercial off-the-shelf COTS or the existing model of the available physical component, integrating the modeled physical component into a system model, taking the model as a part of the model in an example form, selecting the model in system verification, and further calculating parameters.

The method specifically comprises the following steps:

according to the comparison between the physical components and the models, obtaining the parameter set required by the corresponding models in the system architecture model, constructing corresponding SysML instances, defining the parameters of the mass, power and thrust magnitude of a thruster of a certain model as shown in FIG. 13, obtaining the physical instances of the corresponding models, and defining the instances of other physical components with models to obtain a SysML type spectrum library.

And D3: generating an example table of the type spectrum to facilitate query, and simultaneously modifying, adding and deleting examples in the table;

according to the index requirements such as quality, the relation between the system quality parameters and the quality parameters of the physical components is realized in system modeling, the examples of the physical components are selected for parameter assignment, the simulation calculation function of an MBSE modeling tool is utilized to automatically realize system parameter calculation, and meanwhile, the index verification is carried out;

if the quality index of the aircraft is verified, the system estimation quality such as the structure is defined, the model of the selectable component is selected to comprise a load type spectrum, the total mass of the aircraft under the current type spectrum set and the corresponding load ratio are obtained through simulation calculation, and whether the requirement is met is verified.

In step E, the domain model specifically is: the non-MBSE language model meeting various simulations of the operation of the aircraft comprises a trajectory resolving model, a structural analysis model, an attitude and orbit control model and the like; and models built within other software. In connection with fig. 14. The method specifically comprises the following steps:

step E1: constructing models in each field, carrying out reconstruction meeting integration according to MBSE model specifications, and enabling the models to have interfaces integrated with a system architecture model;

for some software supporting FMI, an FMU file can be generated, and integration of a system model and a field model is achieved by utilizing an FMI interface of an MBSE modeling tool; for customizing the field model, the system architecture model can be called to the field model according to the interface form customized by software requirements, and the integratability of the model is realized.

for a parameter model, a Matlab function script is generally integrated in a parameter graph; the models such as control generally use a Simulink model, and can be directly integrated in a SysML model;

for the FMU model, the FMU model can be imported into blocks, and corresponding parameter relationships are constructed to be integrated; modification in the behavioral graph is required for the behavioral model for model integration.

Furthermore, opaque properties may be called in the parameter graph or the behavior graph to adopt a non-SysML language model such as a Java model or the like. For the rapidity index verification, the launch section carrying needs to be evaluated, for example, fig. 14 shows that multiple domain models which can be integrated in SysML include aircraft domain models supporting FMI interfaces such as Ansys models, the orbital transfer executed in the orbital entry section can obtain an orbital transfer strategy through Matlab files, and the orbital transfer strategy is integrated in corresponding parameter and behavior models, and then the verification of the control system during the orbital transfer is realized by utilizing the Simulink model integration of the control system.

In addition, for self-developed domain models, integrated simulation verification can be performed through customizing FMI interfaces or behavioral graph communication. The integrated model can be connected with a parameter map, a module definition map, a behavior map and the like in the SysML, corresponding parameters are obtained from the SysML model, and a calculation result is returned to the system model.

for rapid dynamic multidisciplinary simulation, MBSE joint field model simulation is carried out, a designed test case is combined, firstly, a simulation GUI is constructed to facilitate manual operation of control system behaviors and states, a physical component type spectrum is selected or a simulation initial value is manually given, simulation is carried out, various indexes of the system are verified according to a curve, a time line graph and a sequence graph output by simulation, the time required by the system to enter the orbit and reach a task point is focused, whether the indexes such as corresponding quality power and the like meet the requirements or not at the time and whether the control system component selection is reasonable or not are determined.

If not, the model needs to be reselected or other system assignments need to be simulated again.

If no proper result is obtained, the system is designed again in the previous step, whether unreasonable or improved places exist in the design stage is searched, or system indexes are negotiated and modified, and iterative design is carried out.

In step F, the method specifically comprises the following steps:

step F2: aiming at the process optimization related to the system behavior, performing behavior optimization according to a sequence diagram and a time line diagram obtained by simulation, and adjusting unreasonable places to perform behavior optimization with the aim of increasing the system response capacity;

The overall design of the system is a continuous iteration process, the simulation verification can be continuously carried out during the modeling period by utilizing the advantages of the MBSE, the step iteration can be conveniently carried out in time when the verification fails,

therefore, the design flow does not completely follow the linear design shown in fig. 1, and parallel, incremental and iterative designs exist in different steps according to the actual design situation. Only the theoretical linear steps are shown in fig. 1 and no flow of iterations etc. is shown that can be performed. The nature of MBSE modeling guarantees flexibility in system design, so that iterations can occur at any stage.

the logic architecture subsystem is used for designing a logic architecture;

the subsystem structure, parameters, behaviors and physical architecture of the integrated aircraft are refined, and the requirements are distributed to the level to achieve full coverage of the requirements; perfecting parameter modeling, and constructing a parameter diagram to verify system indexes such as a carrier-to-mass ratio and a power index; establishing the state and behavior of each subsystem, and perfecting the flow relationship among the physical components;

the result output subsystem is used for optimizing a system design scheme, adjusting functions, structural models and parameters in the design scheme according to a simulation result, improving the system performance, and finally freezing the system design and model selection scheme.

The memory in the embodiments of the present application may be either volatile memory or nonvolatile memory, or may include both volatile and nonvolatile memory. The non-volatile memory may be a Read Only Memory (ROM), a Programmable ROM (PROM), an Erasable PROM (EPROM), an electrically Erasable EPROM (EEPROM), or a flash memory. Volatile memory can be Random Access Memory (RAM), which acts as external cache memory. By way of example, but not limitation, many forms of RAM are available, such as Static Random Access Memory (SRAM), dynamic Random Access Memory (DRAM), synchronous Dynamic Random Access Memory (SDRAM), double data rate SDRAM, enhanced SDRAM, SLDRAM, synchronous Link DRAM (SLDRAM), and direct rambus RAM (DR RAM). It should be noted that the memories of the methods described herein are intended to comprise, without being limited to, these and any other suitable types of memories.

In the above embodiments, the implementation may be wholly or partially realized by software, hardware, firmware, or any combination thereof. When implemented in software, may be implemented in whole or in part in the form of a computer program product. The computer program product includes one or more computer instructions. When loaded and executed on a computer, cause the processes or functions described in accordance with the embodiments of the application to occur, in whole or in part. The computer may be a general purpose computer, a special purpose computer, a network of computers, or other programmable device. The computer instructions may be stored on a computer readable storage medium or transmitted from one computer readable storage medium to another, for example, from one website, computer, server, or data center to another website, computer, server, or data center via wire (e.g., coaxial cable, fiber optic, digital Subscriber Line (DSL)) or wireless (e.g., infrared, wireless, microwave, etc.). The computer-readable storage medium can be any available medium that can be accessed by a computer or a data storage device, such as a server, a data center, etc., that incorporates one or more of the available media. The usable medium may be a magnetic medium (e.g., a floppy disk, a hard disk, a magnetic tape), an optical medium (e.g., a Digital Video Disk (DVD)), or a semiconductor medium (e.g., a Solid State Disk (SSD)), among others.

In implementation, the steps of the above method may be performed by integrated logic circuits of hardware in a processor or instructions in the form of software. The steps of a method disclosed in connection with the embodiments of the present application may be directly implemented by a hardware processor, or may be implemented by a combination of hardware and software modules in a processor. The software module may be located in ram, flash memory, rom, prom, or eprom, registers, etc. storage media as is well known in the art. The storage medium is located in a memory, and a processor reads information in the memory and completes the steps of the method in combination with hardware of the processor. To avoid repetition, it is not described in detail here.

It should be noted that the processor in the embodiments of the present application may be an integrated circuit chip having signal processing capabilities. In implementation, the steps of the above method embodiments may be performed by integrated logic circuits of hardware in a processor or instructions in the form of software. The processor described above may be a general purpose processor, a Digital Signal Processor (DSP), an Application Specific Integrated Circuit (ASIC), a Field Programmable Gate Array (FPGA) or other programmable logic device, discrete gate or transistor logic, discrete hardware components. The various methods, steps, and logic blocks disclosed in the embodiments of the present application may be implemented or performed. A general purpose processor may be a microprocessor or the processor may be any conventional processor or the like. The steps of the method disclosed in connection with the embodiments of the present application may be directly implemented by a hardware decoding processor, or implemented by a combination of hardware and software modules in the decoding processor. The software module may be located in ram, flash memory, rom, prom, or eprom, registers, etc. storage media as is well known in the art. The storage medium is located in a memory, and a processor reads information in the memory and completes the steps of the method in combination with hardware of the processor.

The integrated aircraft design method and system based on the MBSE provided by the invention are introduced in detail, the principle and the implementation mode of the invention are explained, and the description of the embodiment is only used for helping to understand the method and the core idea of the invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed, and in summary, the content of the present specification should not be construed as a limitation to the present invention.

Claims

1. An integrated aircraft design method based on MBSE is characterized in that:

the method specifically comprises the following steps:

analyzing the task requirements of the integrated aircraft, constructing an operation scene in SysML according to a task idea to sort system design requirements, decomposing and clustering the functional requirements of the integrated aircraft composition system, combining the same functions of different component assemblies, analyzing the functions of subsystems at all levels under an MBSE flow and designing behaviors and test cases;

and B: constructing a logic architecture;

and C: designing a physical architecture;

step D: designing and selecting a type spectrum library;

step E: performing combined simulation verification;

2. The method of claim 1, further comprising:

in the step a, the method specifically comprises the following steps:

step A2: constructing an integrated aircraft professional glossary;

step A3: analyzing and refining system requirements, obtaining system design requirements from a system task scene designed in an operation concept ConOps, further obtaining the requirements of each level of aircraft system, constructing a requirement diagram and generating a requirement matrix;

step A4: and constructing each system behavior of the aircraft, and performing functional clustering on the behaviors and the component mapping to obtain the system requirement which is in line with the integrated design after redundancy optimization.

3. The method of claim 2, further comprising:

in the step B, the following steps are specifically included:

4. The method of claim 3, further comprising:

in the step C, the following steps are specifically included:

and step C2: completely designing the behavior of each subsystem;

5. The method of claim 4, further comprising:

in the step D, the following steps are specifically included:

and D3: generating an example table of the type spectrum;

6. The method of claim 5, further comprising:

in the step E, the method specifically includes the following steps:

the field model specifically comprises: non-MBSE models that satisfy simulations of aircraft operation include ballistic solution models, structural analysis models, and controller models.

7. The method of claim 6, wherein:

in step F, the method specifically comprises the following steps:

8. An integrated aircraft design, optimization and evaluation system based on MBSE is characterized in that:

the system is realized based on the method of any one of claims 1 to 7;

the logic architecture subsystem is used for designing a logic architecture;

9. An electronic device comprising a memory and a processor, the memory storing a computer program, wherein the processor implements the steps of the method according to any one of claims 1 to 7 when executing the computer program.

10. A computer readable storage medium storing computer instructions which, when executed by a processor, carry out the steps of the method of any one of claims 1 to 7.