Integrated construction method and device of satellite system design model and simulation model based on Modelica

Abstract

The present application discloses a method and device for building an integrated satellite system design model and simulation model based on Modelica. The method includes building a satellite system design model based on Modelica; obtaining the logical architecture of the satellite system based on the satellite system design model, the composition of the subsystems and the corresponding interface relationships between the subsystems; mapping the satellite system topological relationship and generating a satellite system simulation model based on a preset simulation type spectrum library and the logical architecture of the satellite system; simulating the simulation conditions set in the preset mission scenario of the satellite system design according to the satellite system simulation model, and verifying the correctness of the satellite system design according to the simulation results. The present application solves the technical problem that the satellite system design process and the simulation verification process cannot be well integrated. The integration of satellite system design and simulation based on the Modelica mechanism implemented by the present application improves efficiency and reduces time costs.

Description

Technical Field

[0001] The present application relates to the field of satellite system design and simulation integration, and more specifically, to a method and device for integrating a satellite system design model and a simulation model based on Modelica. Background Art

[0002] Satellite systems are complex, high-tech products involving multiple disciplines. Their development process requires gradually refining the satellite's functional modules to design the satellite system based on the satellite's mission requirements, and building a corresponding simulation model based on the designed satellite system to verify the correctness of the design.

[0003] The design of satellite systems mainly adopts a document-based approach, while the interface-based system joint simulation method can achieve multi-domain modeling and simulation to a certain extent.

[0004] However, the document-based satellite design process and the interface-based satellite system simulation process are independent of each other, resulting in the separation of satellite system design and simulation, making it difficult to achieve rapid satellite system design and multi-scheme demonstration, further reducing the satellite development efficiency.

[0005] With regard to the problem that the design and simulation of satellite systems cannot be well integrated in related technologies, no effective solution has been proposed so far. Summary of the invention

[0006] The main purpose of this application is to provide a method and device for automatically generating a satellite system model based on Modelica, so as to solve the problem that the satellite system design process and the simulation verification process cannot be well integrated.

[0007] In order to achieve the above-mentioned purpose, according to one aspect of the present application, a method for integrating the design model and the simulation model of a satellite system based on Modelica is provided.

[0008] The automatic generation method of satellite system model based on Modelica according to the present application includes: constructing a satellite system design model based on Modelica, wherein the satellite system design model mainly includes a demand analysis model, a functional decomposition model, etc., and the system design model is used to determine the functional modules required by the satellite system under the mission scenario and the corresponding functional indicator decomposition; based on the satellite system design model, the satellite subsystem composition and the corresponding interface relationship between the subsystems can be determined to obtain the logical architecture of the satellite system; based on the preset simulation type spectrum library and the logical architecture of the satellite system, the satellite system topological relationship is mapped and a satellite system simulation model is generated, wherein the mapping process involves that the satellite system simulation type spectrum library is constructed based on Modelica; according to the satellite system simulation model, the simulation working conditions set in the preset mission scenario of the satellite system design are simulated, and the correctness of the satellite system design is verified according to the simulation results. .

[0009] Furthermore, the logical architecture of the satellite system is obtained based on the satellite system design model, the composition of the subsystems and the corresponding interface relationships between the subsystems, and further includes: after determining the main functional modules of the satellite system, decomposing each functional module in the satellite system to determine the composition of the main functional modules of the satellite system and allocating functional indicators of related modules to subordinate submodules of the main functional modules; according to the decomposition results of the related modules and the submodules, designing corresponding subsystems and then determining the interface relationships between the subsystems to obtain the logical architecture of the satellite system.

[0010] Furthermore, the logical architecture of the satellite system is obtained based on the satellite system design model, the composition of the subsystems and the corresponding interface relationships between the subsystems, including: after determining the satellite system design model, the composition of the subsystems and the corresponding interface relationships between the subsystems, corresponding stand-alone modules are selected from an existing model spectrum library according to the design indicators assigned to each of the stand-alone machines and filled into the satellite system, so as to obtain the satellite system topological relationship of the composition and interface relationship from the overall satellite system to the subsystems and then to each module.

[0011] Furthermore, the satellite system design model is constructed based on Modelica, wherein the satellite system design model is used to process and analyze preset task functions and determine functional modules and corresponding functional indicators required to complete the preset tasks of the satellite system, including: establishing a satellite system design model based on Modelica for the satellite system to obtain the design indicators of the main functional modules and corresponding modules constituting the satellite system.

[0012] Further, the obtaining of the logical architecture of the satellite system based on the satellite system design model, the composition of the subsystems and the corresponding interface relationships between the subsystems includes: based on the satellite system design model, the composition of the subsystems and the corresponding interface relationships between the subsystems, according to a preset top-down decomposition method, the relevant functional modules of the satellite system are refined and decomposed to obtain each satellite functional module set supporting a satellite mission scenario; based on the satellite system design model, the composition of the subsystems and the corresponding interface relationships between the subsystems, according to a preset bottom-up design method, the satellite system composition is obtained according to each satellite functional module set to determine the interface relationship between the satellite systems; according to the satellite system composition, a current single machine is selected from a preset model library, and whole satellite parameter data is calculated according to the attributes of each single machine.

[0013] Furthermore, the simulation is performed according to the simulation model of the satellite system and the simulation conditions set in the preset mission scenario of the satellite system design, and the correctness of the satellite system design is verified according to the simulation results, including: system simulation analysis of initial conditions and boundary conditions given according to the simulation model of the satellite system and the mission conditions set in the preset mission scenario of the satellite system design; and extraction and analysis of the simulation results to verify the correctness of the satellite system design.

[0014] Furthermore, based on the preset simulation type spectrum library and the logical architecture of the satellite system, the satellite system topological relationship is mapped and a satellite system simulation model is generated, wherein the preset simulation type spectrum library involved in the mapping process is constructed based on Modelica, including: establishing a one-to-one correspondence between a stand-alone type spectrum library and a simulated stand-alone type spectrum library based on parameter information associated with paths, numbers, and names; mapping the satellite system topological relationship and generating a multi-domain simulation model of the satellite system.

[0015] In order to achieve the above-mentioned purpose, according to another aspect of the present application, a device for integrating the design model and the simulation model of a satellite system based on Modelica is provided.

[0016] The Modelica-based automatic generation device of satellite system models according to the present application includes: a satellite system task function analysis module, which is used to construct a satellite system design model based on Modelica, wherein the satellite system design model is used to process and analyze preset task functions, and determine the functional modules and corresponding functional indicators required to complete the preset tasks of the satellite system; a satellite system logical architecture module, which is used to obtain the logical architecture of the satellite system based on the satellite system design model, the composition of the subsystems and the corresponding interface relationships between the subsystems; a simulation verification model module, which is used to map the satellite system topological relationship and generate a satellite system simulation model based on a preset simulation type spectrum library and the logical architecture of the satellite system; a simulation verification analysis module, which is used to simulate according to the satellite system simulation model and the simulation conditions set in the preset task scenario of the satellite system design, and verify the correctness of the satellite system design according to the simulation results.

[0017] In order to achieve the above objective, according to another aspect of the present application, a computer-readable storage medium is provided, in which a computer program is stored, wherein the computer program is configured to execute the method when running.

[0018] In order to achieve the above objective, according to another aspect of the present application, an electronic device is provided, including a memory and a processor, wherein a computer program is stored in the memory, and the processor is configured to run the computer program to execute the described method.

[0019] In the embodiment of the present application, a method and device for integrating Modelica satellite system design model and simulation model are used. The satellite system design model is constructed based on Modelica, and the satellite system design model can be used to determine the composition of satellite subsystems and the corresponding interface relationships between the subsystems to obtain the logical architecture of the satellite system; based on a preset simulation spectrum library and the logical architecture of the satellite system, the satellite system topological relationship is mapped and a satellite system simulation model is generated, wherein the mapping process involves that the satellite system simulation spectrum library is constructed based on Modelica; according to the satellite system simulation model, simulation is performed on the simulation working conditions set in the preset mission scenario of the satellite system design, and the correctness of the satellite system design is verified according to the simulation results, thereby achieving the technical effect of shortening the satellite R&D cycle and reducing the R&D cost, and thus solving the technical problem that the design and simulation of the satellite system cannot be well integrated. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The drawings constituting a part of this application are used to provide a further understanding of this application, so that other features, purposes and advantages of this application become more obvious. The schematic embodiment drawings and their descriptions of this application are used to explain this application and do not constitute an improper limitation on this application. In the drawings:

[0021] FIG. 1( a ) is a schematic diagram of a satellite system function task analysis result in a method for building an integrated Modelica satellite system design model and simulation model according to an embodiment of the present application;

[0022] FIG1( b ) is a schematic diagram of the logical architecture relationship of satellite subsystems in the integrated construction method of Modelica satellite system design model and simulation model according to an embodiment of the present application;

[0023] FIG1( c ) is a schematic diagram of a satellite system type spectrum library architecture in a method for building an integrated Modelica satellite system design model and simulation model according to an embodiment of the present application;

[0024] Figure 2 It is a flowchart of a method for integrating a Modelica satellite system design model and a simulation model according to an embodiment of the present application;

[0025] Figure 3 It is a structural schematic diagram of a device for integrating a Modelica satellite system design model and a simulation model according to an embodiment of the present application;

[0026] Figure 4 It is a flowchart of a method for integrating a satellite system design model and a simulation model based on Modelica according to a preferred embodiment of the present application. DETAILED DESCRIPTION

[0027] In order to enable those skilled in the art to better understand the solution of the present application, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work should fall within the scope of protection of the present application.

[0028] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequential order. It should be understood that the data used in this way can be interchanged where appropriate, so that the embodiments of the present application described here. In addition, the terms "including" and "having" and any of their variations are intended to cover non-exclusive inclusions, for example, a process, method, system, product or device comprising a series of steps or units is not necessarily limited to those steps or units clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0029] In the present application, the terms "upper", "lower", "left", "right", "front", "back", "top", "bottom", "inner", "outer", "middle", "vertical", "horizontal", "lateral", "longitudinal" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the drawings. These terms are mainly used to better describe the present application and its embodiments, and are not used to limit the indicated devices, elements or components to have a specific orientation, or to be constructed and operated in a specific orientation.

[0030] In addition, some of the above terms may be used to express other meanings in addition to indicating orientation or positional relationship. For example, the term "on" may also be used to express a certain dependency or connection relationship in some cases. For those of ordinary skill in the art, the specific meanings of these terms in this application can be understood according to specific circumstances.

[0031] In addition, the terms "installed", "set", "provided with", "connected", "connected", and "socketed" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral structure; it can be a mechanical connection, or an electrical connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be an internal connection between two devices, elements, or components. For those of ordinary skill in the art, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0032] At present, the design of satellite systems mainly adopts a document-based approach. The document-based process requires engineers to manually generate a variety of outputs: requirements analysis reports, outline design reports, detailed design reports, interface definition documents, system design specifications, etc. These outputs are usually presented in the form of text documents, spreadsheets, charts and presentation documents. In general, document-based design outputs have poor reusability and are prone to errors. The transmission of design documents between systems seriously restricts design efficiency. If a design parameter is changed, a large amount of rework and modification of the relevant content of the design document is required, and the whole process is time-consuming and labor-intensive.

[0033] The interface-based system joint simulation method can realize multi-domain modeling and simulation to a certain extent, but the interface-based joint simulation method has the following problems: first, the simulation tool must provide the corresponding interface; second, the joint simulation requires the decoupling between system domains or models during modeling, the solution efficiency is relatively low, and clock synchronization cannot be achieved in the solution time. This method is bound to be unable to describe all the characteristics of the multi-domain system and is complex to operate.

[0034] The inventors found that the document-based satellite design process and the interface-based satellite system simulation process are independent of each other, resulting in the separation of satellite system design and simulation, making it difficult to achieve rapid satellite system design and multi-scheme demonstration, further reducing the satellite development efficiency.

[0035] Among the related technologies, the Modelica mechanism has the advantages of object-oriented, non-causal modeling, multi-domain unified modeling, and design process simulation. It can realize the integration of the system design process and the simulation verification process of the satellite system, that is, to complete the satellite system function task analysis, logical architecture design, automatic generation of simulation verification models, simulation result verification analysis and other satellite R&D processes based on one platform.

[0036] In order to overcome the shortcomings of the existing satellite design process, a method for automatically generating a satellite system model based on Modelica is proposed in the embodiment of the present application to realize simulation integration based on Modelica satellite system design. The method combines the satellite system design simulation process with the Modelica mechanism, and can realize the integration of the satellite system design simulation process based on the model, which can effectively improve the efficiency of satellite design, reduce the difficulty and complexity of building a satellite multi-domain system simulation model, increase the reusability and scalability of the model, improve the design and analysis capabilities of the satellite, reduce the number of model tests, and greatly shorten the development cycle.

[0037] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0038] As shown in Figures 1(a), 1(b) and 1(c), the Modelica-based automatic generation method of a satellite system model in an embodiment of the present application involves a schematic diagram of the satellite system function task analysis, the logical architecture relationship of each satellite subsystem and the satellite system type library architecture.

[0039] like Figure 2 As shown, the method includes the following steps S201 to S204:

[0040] Step S201, constructing a satellite system design model based on Modelica, wherein the satellite system design model includes a demand analysis model and a functional decomposition model, and the system design model is used to determine the functional modules required by the satellite system under the mission scenario and the corresponding functional indicator decomposition;

[0041] Step S202, based on the satellite system design model, the satellite subsystem composition and the corresponding interface relationship between the subsystems can be determined to obtain the logical architecture of the satellite system;

[0042] Step S203, based on a preset simulation type spectral library and the logical architecture of the satellite system, mapping the satellite system topological relationship and generating a satellite system simulation model, wherein the mapping process involves that the satellite system simulation type spectral library is constructed based on Modelica;

[0043] Step S204, performing simulation according to the satellite system simulation model and the simulation working conditions set in the preset mission scenario of the satellite system design, and verifying the correctness of the satellite system design according to the simulation results.

[0044] From the above description, it can be seen that the present application achieves the following technical effects:

[0045] The satellite system design model is constructed based on Modelica, and

[0046] Based on the satellite system design model, the satellite subsystem composition and the corresponding interface relationship between the subsystems can be determined to obtain the logical architecture of the satellite system;

[0047] Based on a preset simulation spectral library and the logical architecture of the satellite system, the topological relationship of the satellite system is mapped and a satellite system simulation model is generated, wherein the mapping process involves that the satellite system simulation spectral library is constructed based on Modelica; according to the satellite system simulation model, simulation is performed on simulation conditions set in preset mission scenarios designed for the satellite system, and the correctness of the satellite system design is verified according to the simulation results, thereby achieving the technical effect of shortening the satellite R&D cycle and reducing the R&D cost, and further solving the technical problem that the design and simulation of the satellite system cannot be well integrated.

[0048] In the above step S201, a satellite system design model is constructed based on Modelica, that is, the decomposition of the satellite system functions into subsystem functions and then into each single machine functions is mainly completed according to the satellite system mission requirements, and the overall mission indicators of the satellite system are decomposed to each single machine step by step.

[0049] In a specific implementation, the satellite system design model is used to process and analyze preset mission functions.

[0050] In a preferred embodiment, the functional modules and corresponding functional indicators required to complete the preset tasks of the satellite system are determined based on the satellite system design model.

[0051] In the above step S202, the logical architecture of the satellite system is obtained based on the satellite system design model, the composition of the subsystems and the corresponding interface relationships between the subsystems, that is, according to the satellite mission function analysis results, the satellite system composition and the interface relationships between the systems are determined, and on this basis, based on the satellite design type spectrum library, the single machine of each subsystem is selected to complete the satellite system logical architecture design.

[0052] In a specific implementation, the logical architecture of the satellite system corresponds to a real satellite system.

[0053] In a preferred embodiment, a logical architecture is obtained based on the subsystems, satellite system design models and docking relationships.

[0054] In the above step S203, based on the preset simulation type library and the logical architecture of the satellite system, the satellite system topological relationship is mapped and a satellite system simulation model is generated. That is, based on the satellite system logical architecture, the satellite system logical architecture model is automatically mapped to generate a system simulation model through path, model name, number association, etc., and simulation verification analysis is carried out.

[0055] In a specific implementation, the preset simulation spectral library involved in the mapping process is constructed based on Modelica.

[0056] In a preferred embodiment, the simulation verification model is automatically generated: first, based on the path, number, name association, etc., a one-to-one correspondence is established between the design single-machine model spectral library and the simulation single-machine model spectral library, and then the satellite system logical architecture design results are mapped to generate a multi-domain simulation model of the satellite system.

[0057] In the above step S204, simulation is performed according to the simulation model of the satellite system and the simulation conditions set in the preset mission scenario of the satellite system design, and the correctness of the satellite system design is verified according to the simulation results.

[0058] In a specific implementation, the satellite-type spectral library built based on the Modelica language has the advantages of strong reusability and easy expansion, can be built once and reused countless times, and can automatically map the design model to generate the system simulation model through path, number, and name association. This reduces the model development workload caused by the separation of the design model and the simulation model.

[0059] Based on the above steps, the design process and simulation process of the satellite system are further integrated. Based on the design spectrum library and the simulation spectrum library, they are associated through paths, numbers, names, etc., so that the satellite system design model can be mapped directly to generate a simulation model, and the system design scheme demonstration and multi-scheme comparison can be quickly realized. This method is suitable for the development process of complex satellite systems. Compared with existing methods, the operation method is simple, and it can greatly shorten the R&D cycle and reduce R&D costs.

[0060] As a preferred embodiment of the present invention, the logical architecture of the satellite system is obtained based on the satellite system design model, the composition of the subsystems and the corresponding interface relationships between the subsystems, and further includes: after determining the main functional modules of the satellite system, decomposing each functional module in the satellite system to determine the composition of the main functional modules of the satellite system and allocating functional indicators of related modules to subordinate submodules of the main functional modules; according to the decomposition results of the related modules and the submodules, designing corresponding subsystems and then determining the interface relationships between the subsystems to obtain the logical architecture of the satellite system.

[0061] During the specific implementation, according to the decomposition results of key modules and sub-modules, a bottom-up approach is used to design corresponding subsystems such as control subsystem, energy subsystem, propulsion subsystem, etc., and the interface relationship between each subsystem is determined to form a complete satellite system. It is required that the modules of the designed satellite system and subsystem are clear, and the functional indicators of each module can cover the corresponding design indicators.

[0062] As a preferred embodiment of the present invention, the logical architecture of the satellite system is obtained based on the satellite system design model, the composition of the subsystems and the corresponding interface relationships between the subsystems, including: after determining the satellite system design model, the composition of the subsystems and the corresponding interface relationships between the subsystems, corresponding stand-alone modules are selected from an existing spectrum library according to the design indicators assigned to each stand-alone machine and filled into the satellite system, so as to obtain a satellite system topological relationship of the composition and interface relationships from the overall satellite system to the subsystems and then to each module.

[0063] During the specific implementation, after determining the composition of the satellite system and subsystems and the corresponding interface relationships, the corresponding stand-alone modules are selected from the existing model library according to the design indicators assigned to each stand-alone machine and quickly filled into the system, forming a satellite system topology with clear composition and interface relationships from the entire system to the subsystem and then to each module. The stand-alone module contains information such as quality, service life, reliability, etc. Based on the accompanying information of the stand-alone machine, the quality, life, reliability, etc. of the entire satellite can be preliminarily estimated.

[0064] As a preferred embodiment of the present invention, the satellite system design model is constructed based on Modelica, wherein the satellite system design model is used to process and analyze preset task functions, and determine the functional modules and corresponding functional indicators required to complete the preset tasks of the satellite system, including: by establishing a satellite system design model based on Modelica to obtain the design indicators of the main functional modules and corresponding modules constituting the satellite system.

[0065] During specific implementation, by establishing a work task analysis model for the satellite system, the main functional modules constituting the satellite system and the design indicators of the corresponding modules can be obtained.

[0066] As a preferred embodiment of the present invention, the obtaining of the logical architecture of the satellite system based on the satellite system design model, the composition of the subsystems and the corresponding interface relationships between the subsystems includes: based on the satellite system design model, the composition of the subsystems and the corresponding interface relationships between the subsystems, the relevant functional modules of the satellite system are refined and decomposed in a preset top-down decomposition manner to obtain a set of functional modules of each satellite supporting a satellite mission scenario; based on the satellite system design model, the composition of the subsystems and the corresponding interface relationships between the subsystems, the satellite system composition is obtained according to each set of satellite functional modules in a preset bottom-up design manner to determine the interface relationship between the satellite systems; and the current single machine is selected from a preset model library according to the satellite system composition, and whole satellite parameter data is calculated according to the attributes of each single machine.

[0067] In specific implementation, the top-down decomposition method can further refine and decompose the key functional modules of the satellite system to obtain a set of functional modules supporting satellite mission scenarios.

[0068] The bottom-up design method described herein designs the satellite system composition according to a set of satellite functional modules and determines the interface relationship between various satellite systems.

[0069] According to the composition of the satellite system, an existing single machine is selected from the model database, and the life, quality and reliability of the entire satellite can be preliminarily calculated based on the properties of each single machine.

[0070] As a preference in this embodiment, the simulation is performed according to the simulation model of the satellite system and the simulation conditions set in the preset mission scenario designed for the satellite system, and the correctness of the satellite system design is verified according to the simulation results, including: system simulation analysis of initial conditions and boundary conditions given according to the simulation model of the satellite system and the mission conditions set in the preset mission scenario designed for the satellite system; and extracting and analyzing the simulation results to verify the correctness of the satellite system design.

[0071] During the specific implementation, based on the generated satellite system simulation model, system simulation analysis is carried out according to the satellite's mission conditions and given initial conditions and boundary conditions. The correctness of the design results is further verified by extracting and analyzing the simulation results.

[0072] As a preference in this embodiment, based on the preset simulation type spectrum library and the logical architecture of the satellite system, the satellite system topological relationship is mapped and a satellite system simulation model is generated, wherein the preset simulation type spectrum library involved in the mapping process is constructed based on Modelica, including: establishing a one-to-one correspondence between a stand-alone spectrum library and a simulated stand-alone spectrum library based on parameter information associated with paths, numbers, and names; mapping the satellite system topological relationship and generating a multi-domain simulation model of the satellite system.

[0073] During the specific implementation, a one-to-one correspondence is established between the design single-machine model spectral library and the simulation single-machine model spectral library, and then the satellite system logical architecture design results are mapped to generate a multi-domain simulation model of the satellite system.

[0074] Among them, the simulation stand-alone model library is mainly built based on the Modelica mechanism. The constructed system-type library involves dynamic subsystem, propulsion subsystem, energy subsystem, integrated electronic system, and measurement subsystem. Each subsystem contains several models of stand-alone machines, such as the measurement subsystem includes coded solar sensor type 1, coded solar sensor type 4, integrated coded solar sensor, etc. Based on each model of stand-alone machine and the designed system logic architecture, a satellite system simulation model is automatically generated in a bottom-up manner.

[0075] It should be noted that the steps shown in the flowcharts of the accompanying drawings can be executed in a computer system such as a set of computer executable instructions, and that, although a logical order is shown in the flowcharts, in some cases, the steps shown or described can be executed in an order different from that shown here.

[0076] According to an embodiment of the present application, a device for implementing the above method based on the integrated construction of the satellite system design model and the simulation model based on Modelica is also provided. Figure 3 As shown, the device comprises:

[0077] The satellite system mission function analysis module 301 is used to construct a satellite system design model based on Modelica, wherein the satellite system design model includes a demand analysis model and a function decomposition model, and the system design model is used to determine the function modules required by the satellite system under the mission scenario and the corresponding function indicator decomposition;

[0078] A satellite system logic architecture module 302 is used to determine the satellite subsystem composition and the corresponding interface relationship between the subsystems based on the satellite system design model to obtain the logic architecture of the satellite system;

[0079] The simulation verification model module 303 is used to map the satellite system topology relationship and generate a satellite system simulation model based on a preset simulation type spectrum library and the logical architecture of the satellite system, wherein the mapping process involves that the satellite system simulation type spectrum library is constructed based on Modelica;

[0080] The simulation verification analysis module 304 is used to perform simulation according to the satellite system simulation model and the simulation working conditions set in the preset mission scenario of the satellite system design, and verify the correctness of the satellite system design according to the simulation results.

[0081] The satellite system mission function analysis module 301 in the embodiment of the present application builds a satellite system design model based on Modelica, that is, it mainly completes the decomposition of the satellite system function to the subsystem function and then to each single machine function according to the satellite system mission requirements, and transfers the total mission indicators of the satellite system to each single machine step by step.

[0082] In a specific implementation, the satellite system design model is used to process and analyze preset mission functions.

[0083] In a preferred embodiment, the functional modules and corresponding functional indicators required to complete the preset tasks of the satellite system are determined based on the satellite system design model.

[0084] In the satellite system logic architecture module 302 of the embodiment of the present application, the logic architecture of the satellite system is obtained based on the satellite system design model, the composition of the subsystems and the corresponding interface relationships between the subsystems, that is, according to the satellite mission function analysis results, the satellite system composition and the interface relationships between the systems are determined, and on this basis, based on the satellite design type spectrum library, the single machine of each subsystem is selected to complete the satellite system logic architecture design.

[0085] In a specific implementation, the logical architecture of the satellite system corresponds to a real satellite system.

[0086] In a preferred embodiment, a logical architecture is obtained based on the subsystems, satellite system design models and docking relationships.

[0087] In the simulation verification model module 303 of the embodiment of the present application, the satellite system topology relationship is mapped and a satellite system simulation model is generated based on the preset simulation type library and the logical architecture of the satellite system. That is, based on the satellite system logical architecture, the satellite system logical architecture model is automatically mapped to generate a system simulation model through path, model name, number association, etc., and simulation verification analysis is carried out.

[0088] In a specific implementation, the preset simulation spectral library involved in the mapping process is constructed based on Modelica.

[0089] In a preferred embodiment, the simulation verification model is automatically generated: first, based on the path, number, name association, etc., a one-to-one correspondence is established between the design single-machine model spectral library and the simulation single-machine model spectral library, and then the satellite system logical architecture design results are mapped to generate a multi-domain simulation model of the satellite system.

[0090] The simulation verification analysis module 304 of the embodiment of the present application performs simulation according to the simulation model of the satellite system and the simulation conditions set in the preset mission scenario of the satellite system design, and verifies the correctness of the satellite system design according to the simulation results.

[0091] In a specific implementation, the satellite-type spectral library built based on the Modelica language has the advantages of strong reusability and easy expansion, can be built once and reused countless times, and can automatically map the design model to generate the system simulation model through path, number, and name association. This reduces the model development workload caused by the separation of the design model and the simulation model.

[0092] Based on the above modules, the design process and simulation process of the satellite system are further integrated. Based on the design spectrum library and the simulation spectrum library, they are associated through paths, numbers, names, etc., so that the satellite system design model can be mapped directly to generate a simulation model, and the system design scheme demonstration and multi-scheme comparison can be quickly realized. This method is suitable for the development process of complex satellite systems. Compared with existing methods, it has a simple operation method, can greatly shorten the R&D cycle, and reduce R&D costs.

[0093] Obviously, those skilled in the art should understand that the above modules or steps of the present application can be implemented by a general computing device, they can be concentrated on a single computing device, or distributed on a network composed of multiple computing devices, and optionally, they can be implemented by a program code executable by a computing device, so that they can be stored in a storage device and executed by the computing device, or they can be made into individual integrated circuit modules, or multiple modules or steps therein can be made into a single integrated circuit module for implementation. In this way, the present application is not limited to any specific combination of hardware and software.

[0094] In order to better understand the above-mentioned process of the automatic generation method of the Modelica satellite system model, the above-mentioned technical solution is explained below in combination with the preferred embodiment, but it is not used to limit the technical solution of the embodiment of the present invention.

[0095] The automatic generation method of the satellite system model based on Modelica in the embodiment of the present application completes the design process and simulation verification process of the satellite system based on a platform through a set of mechanisms. Firstly, it can effectively avoid the problems of poor consistency, low communication efficiency, and easy ambiguity caused by the document-based system design process. Secondly, the simulation verification based on a platform can avoid the tedious switching of multiple professional software and the mismatch of software interfaces, thereby reducing the workload of simulation engineers.

[0096] In addition, this technology further integrates the design process and simulation process of the satellite system. Based on the design spectrum library and the simulation spectrum library, they are associated through paths, numbers, names, etc., and can directly generate simulation models by mapping the satellite system design model, and quickly realize the system design scheme demonstration and multi-scheme comparison. This method is suitable for the development process of complex satellite systems. Compared with existing methods, it has a simple operation method, can greatly shorten the R&D cycle, and reduce R&D costs.

[0097] like Figure 4 FIG. 1 is a flow chart of a method for automatically generating a satellite system model based on Modelica in an embodiment of the present application, which specifically includes the following steps:

[0098] Step S401, satellite system mission function analysis.

[0099] Satellite system mission function analysis: According to the work mission of the satellite system, analyze the functions that the satellite needs to have, build a satellite system function task analysis model, and determine the main functional modules and corresponding functional indicators required to support the satellite system to complete the predetermined tasks; by establishing a satellite system work task analysis model, the main functional modules that make up the satellite system and the design indicators of the corresponding modules can be obtained.

[0100] Satellite system mission function analysis: According to the satellite system's work tasks, a detailed analysis is carried out to determine the functional modules that the satellite system needs to have in order to complete the expected tasks. For example, when a meteorological satellite is working, the detector is required to point to the earth, so it is necessary to have an attitude determination module and an attitude control module. Similarly, determine that the satellite system covers all the functional modules necessary for the work tasks. While determining the satellite's functional modules, the system's mission indicators are also allocated to the corresponding modules. For example, the satellite's design life is 10 years, and the life allocated to each functional module must not be less than 10 years; the total mass of the satellite must not be higher than 2t, and the sum of the masses allocated to all functional modules must not be greater than 2t.

[0101] Step S402: satellite system logical architecture design.

[0102] Satellite system logical architecture design: After determining the main functional modules that the satellite must have, a top-down approach is used to further decompose each functional module of the satellite, determine the composition of the main functional modules of the satellite system and assign the functional indicators of the key modules to their subordinate sub-modules.

[0103] According to the decomposition results of key modules and sub-modules, the corresponding subsystems such as control subsystem, energy subsystem, propulsion subsystem, etc. are designed using a bottom-up approach, and the interface relationship between each subsystem is determined to form the entire satellite system. It is required that the modules of the designed satellite system and subsystem are clear, and the functional indicators of each module can cover the corresponding design indicators.

[0104] After determining the composition of the satellite system and subsystems and the corresponding interface relationships, select the corresponding stand-alone modules from the existing model library according to the design indicators assigned to each stand-alone machine and quickly fill them into the system, forming a satellite system topology with clear composition and interface relationships from the entire system to the subsystem and then to each module. The stand-alone module contains information such as quality, service life, reliability, etc. Based on the accompanying information of the stand-alone machine, the quality, life, reliability, etc. of the entire satellite can be preliminarily estimated.

[0105] The top-down decomposition method can further refine and decompose the key functional modules of the satellite system to obtain a set of functional modules supporting satellite mission scenarios.

[0106] The bottom-up design method described herein designs the satellite system composition according to a set of satellite functional modules and determines the interface relationship between various satellite systems.

[0107] The existing single machine is selected from the model database according to the composition of the satellite system, and the life, quality, reliability, etc. of the entire satellite can be preliminarily calculated based on the properties of each single machine.

[0108] After determining all the functional modules required by the satellite system, the system logical architecture design uses a top-down approach to decompose each functional module to obtain a set of satellite system functional modules. Based on the decomposition results, the satellite system, subsystem and even the single machine level are designed layer by layer. The design process needs to determine the interface relationship between each system and the decomposition and transmission path of the design indicators. On this basis, the existing single machine model library is further used to complete the selection of each single machine.

[0109] Step S403: automatically generate a system simulation verification model.

[0110] The automatic generation of simulation verification models is based on the constructed simulation spectrum library. According to the clear satellite system topological relationship, the satellite system topology can be automatically mapped to generate a satellite system simulation model.

[0111] At the same time, based on the satellite spectrum model library, the designed satellite system is automatically generated into a satellite system simulation model through mapping according to the satellite design results.

[0112] Automatic generation of simulation verification model: First, based on path, number, name association, etc., a one-to-one correspondence is established between the design single-machine model library and the simulation single-machine model library, and then the satellite system logical architecture design results are mapped to generate a multi-domain simulation model of the satellite system.

[0113] The simulation stand-alone model library is mainly built based on the Modelica mechanism. The constructed system-type library involves dynamic subsystem, propulsion subsystem, energy subsystem, integrated electronic system, and measurement subsystem. Each subsystem contains several models of stand-alone machines, such as the measurement subsystem includes coded solar sensor type 1, coded solar sensor type 4, integrated coded solar sensor, etc. Based on each model of stand-alone machine and the designed system logic architecture, a satellite system simulation model is automatically generated in a bottom-up manner.

[0114] Step S404: Conduct simulation verification analysis based on the system simulation results.

[0115] Carry out simulation verification analysis. After the satellite system simulation model is generated, set the simulation conditions according to the mission scenario of the satellite design, and verify the correctness of the system design based on the simulation solution results of the model. Set the simulation conditions according to the satellite work mission scenario based on the automatically generated system simulation model, and extract the simulation solution results of the analysis to verify the correctness of the system design.

[0116] The simulation analysis is carried out based on the generated satellite system simulation model. The system simulation analysis is carried out according to the initial conditions and boundary conditions given by the satellite's mission conditions. The correctness of the design results is further verified by extracting and analyzing the simulation results.

[0117] The integration of satellite system design and simulation based on the Modelica mechanism can reduce the energy spent by engineers on document writing during the satellite system design process, and can avoid problems such as poor consistency of design documents, low communication efficiency, and easy ambiguity. The satellite model library built based on the Modelica language has the advantages of strong reusability and easy expansion. It can be built once and reused countless times, and can automatically map the design model to generate a system simulation model through path, number, and name association. The workload of model development caused by the separation of design models and simulation models is greatly reduced. This application can quickly realize the rapid design and simulation verification of satellite system solutions, compare multiple solutions, improve the development efficiency of satellite systems, save costs, and improve product competitiveness.

[0118] The above description is only the preferred embodiment of the present application and is not intended to limit the present application. For those skilled in the art, the present application may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A method for building an integrated satellite system design model and simulation model based on Modelica, characterized in that: include: Building a satellite system design model based on Modelica, wherein the satellite system design model includes a demand analysis model and a functional decomposition model. The system design model is used to determine the functional modules required by the satellite system under the mission scenario and the corresponding functional indicator decomposition; Based on the satellite system design model, the satellite subsystem composition and the corresponding interface relationship between the subsystems can be determined to obtain the logical architecture of the satellite system; Based on a preset simulation type spectral library and the logical architecture of the satellite system, the satellite system topological relationship is mapped and a satellite system simulation model is generated, wherein the mapping process involves that the satellite system simulation type spectral library is constructed based on Modelica; Based on the preset simulation type spectral library and the logical architecture of the satellite system, the satellite system topological relationship is mapped and a satellite system simulation model is generated, wherein the mapping process involves that the satellite system simulation type spectral library is constructed based on Modelica, including: Based on the parameter information associated with the path, number, and name, a one-to-one correspondence is established between the stand-alone model spectral library and the simulated stand-alone model spectral library; Mapping the satellite system topological relationship and generating a multi-domain simulation model of the satellite system; According to the satellite system simulation model, simulation is performed in simulation conditions set in a preset mission scenario designed for the satellite system, and the correctness of the satellite system design is verified based on the simulation results.

2. The method according to claim 1, characterized in that The satellite system design model can be used to determine the satellite subsystem composition and the corresponding interface relationship between the subsystems to obtain the logical architecture of the satellite system, and further includes: After determining the main functional module of the satellite system, decomposing each functional module in the satellite system, determining the composition of the main functional module of the satellite system and allocating the functional indicators of the relevant modules to the subordinate submodules of the main functional module; According to the decomposition results of the related modules and the submodules, the corresponding subsystems are designed and then the interface relationships between the subsystems are determined to obtain the logical architecture of the satellite system.

3. The method according to claim 2, characterized in that The satellite system design model can be used to determine the satellite subsystem composition and the corresponding interface relationship between the subsystems to obtain the logical architecture of the satellite system, including: After determining the composition of the satellite system and its subsystems and the corresponding interface relationships between the subsystems, the corresponding stand-alone modules are selected from the existing model library according to the design indicators assigned to each of the stand-alone machines and filled into the satellite system simulation model to obtain the overall satellite system simulation model.

4. The method according to claim 1, characterized in that: The satellite system design model is constructed based on Modelica, wherein the satellite system design model includes a demand analysis model and a functional decomposition model. The system design model is used to determine the functional modules required by the satellite system under the mission scenario and the corresponding functional indicator decomposition, including: A satellite system design model based on Modelica is established to obtain the main functional modules constituting the satellite system and the design indicators of the corresponding modules.

5. The method according to claim 1, characterized in that The satellite system design model can be used to determine the satellite subsystem composition and the corresponding interface relationship between the subsystems to obtain the logical architecture of the satellite system, including: Based on the satellite system design model, the composition of the subsystems and the corresponding interface relationships between the subsystems, the relevant functional modules of the satellite system are refined and decomposed in a preset top-down decomposition manner to obtain a set of functional modules of each satellite that supports the satellite mission scenario; Based on the satellite system design model, the composition of the subsystems and the corresponding interface relationships between the subsystems, the satellite system composition is obtained according to each satellite functional module set in a preset bottom-up design manner to determine the interface relationship between the satellite systems; According to the composition of the satellite system, a current single machine is selected from a preset spectrum library, and the whole satellite parameter data is calculated according to the properties of each single machine.

6. The method according to claim 1, characterized in that The simulating according to the satellite system simulation model and the simulation conditions set in the preset mission scenario designed for the satellite system, and verifying the correctness of the satellite system design according to the simulation results, includes: The system simulation analysis of the initial conditions and boundary conditions is given according to the satellite system simulation model and the mission conditions set in the preset mission scenario designed for the satellite system; Extract and analyze the simulation results to verify the correctness of the satellite system design.

7. A device for building an integrated satellite system design model and simulation model based on Modelica, characterized in that: include: Satellite system mission function analysis module, used to construct satellite system design model using Modelica, wherein the satellite system design model includes a demand analysis model and a function decomposition model. The system design model is used to determine the function modules required by the satellite system under the mission scenario and the corresponding function indicator decomposition; A satellite system logic architecture module, which is used to determine the satellite subsystem composition and the corresponding interface relationship between the subsystems based on the satellite system design model to obtain the logic architecture of the satellite system; A simulation verification model module is used to map the satellite system topological relationship and generate a satellite system simulation model based on a preset simulation spectrum library and the logical architecture of the satellite system, wherein the mapping process involves that the satellite system simulation spectrum library is constructed based on Modelica; the satellite system topological relationship is mapped based on the preset simulation spectrum library and the logical architecture of the satellite system and generate a satellite system simulation model, wherein the mapping process involves that the satellite system simulation spectrum library is constructed based on Modelica, including: Based on the parameter information associated with the path, number, and name, a one-to-one correspondence is established between the stand-alone model spectral library and the simulated stand-alone model spectral library; Mapping the satellite system topological relationship and generating a multi-domain simulation model of the satellite system; The simulation verification analysis module is used to perform simulation according to the satellite system simulation model and the simulation working conditions set in the preset mission scenario of the satellite system design, and verify the correctness of the satellite system design according to the simulation results.

8. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores a computer program, wherein the computer program is configured to execute the method according to any one of claims 1 to 6 when executed.

9. An electronic device comprising a memory and a processor, characterized in that: A computer program is stored in the memory, and the processor is configured to run the computer program to perform the method according to any one of claims 1 to 6.

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