Multi-level spacecraft system modeling method based on atomic components

Abstract

The invention relates to a multi-level spacecraft system modeling method based on atomic components, and the method comprises the following steps: S1, completing the design of a spacecraft model system according to a task demand; s2, performing component interface design of the spacecraft model system to form an interface diagram, an interface table and an interface protocol file; s3, developing a spacecraft atomic component model simulation program according to component modeling requirements; s4, atomic component model assembly is carried out through the spacecraft atomic component model simulation program, and a general spacecraft entity model is formed through packaging; and S5, performing parameter configuration on the general spacecraft entity model, completing construction of a specific entity, and forming an entity model of a specific model. According to the method, the requirements of multi-field spacecraft system simulation are met, the designed model system and composition are flexible, the modeling method is universal, the expansibility is high, the reuse rate is high, the development efficiency of complex spacecraft system simulation modeling and system development can be improved, and the method has very high guiding significance.

Description

Technical Field

[0001] The present invention relates to the technical field of spacecraft simulation, and in particular to a multi-level spacecraft system modeling method based on atomic components. Background Art

[0002] In recent years, with the development of digitalization, spacecraft digital simulation has shown a trend of large-scale, systematized, networked, and confrontational development. As the scale of simulation increases, high requirements are placed on the modeling efficiency, interactive capabilities, and reusability of spacecraft simulation systems. Therefore, a reusable, multi-level, and efficient spacecraft system modeling method has become an urgent need for modeling and simulation in the aerospace field.

[0003] Most of the current methods for spacecraft modeling and simulation focus more on dynamic modeling or finite element modeling of spacecraft subsystems and components, focusing on professional and field-level modeling, lacking focus on the field of system simulation and unable to meet the needs of full-function and multi-field functional simulation.

[0004] Traditional modeling methods have poor flexibility, high model reuse and transformation costs, and low development efficiency; the traditional spacecraft system simulation modeling process is not standardized, making it difficult to achieve smooth interaction between spacecraft models in different fields, and cannot ensure the consistency of simulation levels and granularity of different entities. Traditional spacecraft simulation modeling is difficult to provide specific modeling implementation routes and operation process references for spacecraft system modeling practice, and it is difficult to meet the requirements of system simulation for more complex, comprehensive, universal, cross-domain, and cross-disciplinary spacecraft simulation modeling. Summary of the invention

[0005] In order to solve the technical problems existing in the above-mentioned prior art, the purpose of the present invention is to provide a multi-level spacecraft system modeling method based on atomic components. The multi-level spacecraft system modeling method based on atomic components proposed in the present invention meets the needs of spacecraft system simulation in multiple fields such as aerospace remote sensing, communication, navigation, perception, environmental detection, launch and measurement and control. The designed model system and composition are flexible, the modeling method is universal, the expansibility is strong, and the reuse rate is high. It can improve the research and development efficiency of complex spacecraft system simulation modeling and system development, and has a strong guiding significance.

[0006] To achieve the above-mentioned object of the invention, the present invention provides a multi-level spacecraft system modeling method based on atomic components, comprising the following steps:

[0007] Step S1: Complete the design of the spacecraft model system according to the mission requirements;

[0008] Step S2, designing the component interfaces of the spacecraft model system, and forming an interface diagram, an interface table, and an interface protocol file;

[0009] Step S3, developing a simulation program for a spacecraft atomic component model according to component modeling requirements;

[0010] Step S4, assembling the atomic component model through the spacecraft atomic component model simulation program, and encapsulating to form a universal spacecraft entity model;

[0011] Step S5: Parameter configuration is performed on the general spacecraft entity model to complete the construction of a specific entity and form an entity model of a specific model.

[0012] According to a technical solution of the present invention, in step S1, the spacecraft model system is a three-layer model system architecture, which includes, from bottom to top, an atomic component layer, a spacecraft entity layer, and a spacecraft domain layer.

[0013] According to a technical solution of the present invention, in step S1, it specifically includes:

[0014] Step S11: According to the simulation task requirements, the aerospace equipment entities are sorted and classified according to the entity characteristics to form the spacecraft domain layer. The entity characteristics include the entity platform type, the business direction of the entity, and the payload type of the entity's affiliated unit. The entity platform type includes space-based and ground-based. The entity's business direction includes remote sensing, communication, navigation, and support. The entity's affiliated units include the Ministry of Land and Resources, the Ministry of Forestry, and the Ministry of Emergency Management.

[0015] Step S12: sort out all the aerospace equipment entities to be constructed to form a spacecraft entity layer;

[0016] Step S13: According to the aerospace equipment entity to be constructed, the atomic components inside the aerospace equipment entity are sorted out according to the component decomposition method to form a spacecraft atomic component layer;

[0017] The component splitting method includes: splitting the aerospace equipment entity into multiple atomic components according to the level and granularity requirements of the simulation and referring to the subsystem composition of the aerospace equipment entity. The components can be reused in different spacecraft entity layers.

[0018] According to a technical solution of the present invention, the component interface design includes external interface design, internal interface design and initialization interface design; the external interface refers to the interface between the aerospace equipment entities; the internal interface refers to the interface between the atomic components inside the aerospace equipment entities.

[0019] According to a technical solution of the present invention, in the step S2, it specifically includes:

[0020] Step S21, sorting out the interaction contents between the aerospace equipment entities, and completing the external interface design between the aerospace equipment entities;

[0021] Step S22, sorting out the interaction contents between the atomic components inside the aerospace equipment entity, and completing the internal interface design of the aerospace equipment entity;

[0022] Step S23, refine each type of external interface and internal interface, design the data characteristics of the interface transmission content, and form an interface protocol; the interface protocol is defined in the form of an interface protocol table, and the interface protocol table includes variable sequence number, variable name, variable type, data unit, meaning, and remarks;

[0023] Step S24, designing the initialization interface of the atomic components constituting the aerospace equipment entity; the initialization interface refers to the static inherent attribute parameters of the atomic components.

[0024] According to a technical solution of the present invention, the external interface design and the internal interface design are performed through an interface diagram and an interface table; the interface table includes an interface serial number, an interface name, an interface identifier, a sender, a receiver and content; the interface diagram is used to represent the topological relationship between the interface serial number, the sender and the receiver.

[0025] According to a technical solution of the present invention, in step S3, it specifically includes:

[0026] Step S31, constructing an atomic component code framework according to the simulation modeling specification requirements; the atomic component code framework includes a simulation initialization function, a simulation step function and a simulation termination function;

[0027] Step S32, according to the external interface, internal interface and interface protocol designed in step S2, and according to the interface identifier, write a data receiving function and a data output function;

[0028] Step S33: write special business functions; the special business functions are used to implement specific functions of atomic components;

[0029] Step S34, debugging the simulation component function, and iteratively updating the component function according to the debugging result; the component function includes the simulation initialization function, the data receiving function, the simulation stepping function, the data output function, the simulation termination function and the special service function;

[0030] Step S35, after the component debugging is completed, the relevant codes are compiled to generate a dynamic runtime library or an executable file, and the development of the spacecraft atomic component model simulation program is completed.

[0031] According to a technical solution of the present invention, in step S4, it specifically includes:

[0032] Step S41, uploading the dynamic runtime library or the executable file to the model assembly software or model assembly tool to store and manage the model;

[0033] Step S42: construct a new spacecraft entity model instance according to the spacecraft entity layer object;

[0034] Step S43, according to the atomic component layer, through the model assembly function provided by the model assembly software or tool, multiple atomic components are selected to assemble a spacecraft entity model instance, which is packaged and saved to form the general spacecraft entity model.

[0035] According to a technical solution of the present invention, in step S5, it specifically includes:

[0036] Step S51, saving the universal spacecraft entity model and renaming it;

[0037] Step S52, obtaining a renamed atomic component model composition list of the universal spacecraft entity model;

[0038] Step S53, performing parameter configuration on the atomic components in the atomic component model list one by one, and performing parameter assignment through the initialization interface of the atomic components;

[0039] Step S54: After the parameter configuration is completed, the model is saved to form a physical model of a specific model.

[0040] Compared with the prior art, the present invention has the following beneficial effects:

[0041] The multi-level spacecraft system modeling method based on atomic components proposed in the present invention meets the needs of spacecraft system simulation in multiple fields such as aerospace remote sensing, communication, navigation, perception, environmental detection, launch and measurement and control. The designed model system and composition are flexible, the modeling method is universal, the expansibility is strong, and the reuse rate is high. It can improve the research and development efficiency of complex spacecraft system simulation modeling and system development, and has strong guiding significance. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments are briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0043] Figure 1 A flowchart of a multi-level spacecraft system modeling method based on atomic components according to an embodiment of the present invention is schematically shown;

[0044] Figure 2A flowchart of a multi-level spacecraft system modeling method based on atomic components according to another embodiment of the present invention is schematically shown;

[0045] Figure 3 A schematic diagram of a spacecraft model system design according to another embodiment of the present invention is schematically shown;

[0046] Figure 4 A schematic diagram of an external interface of a Gaofen-5 satellite according to another embodiment of the present invention is schematically shown;

[0047] Figure 5 The figure schematically shows a schematic diagram of the internal interface of the Gaofen-5 satellite according to another embodiment of the present invention. DETAILED DESCRIPTION

[0048] The description of the embodiments of this specification should be combined with the corresponding drawings, which should be considered as part of the complete specification. In the drawings, the shape or thickness of the embodiments may be enlarged and indicated for simplification or convenience. Furthermore, the parts of each structure in the drawings will be described separately. It is worth noting that the elements not shown in the drawings or not described in words are in a form known to ordinary technicians in the relevant technical field.

[0049] The description of the embodiments herein and any reference to directions and orientations are only for the convenience of description and are not to be construed as any limitation on the scope of protection of the present invention. The following description of the preferred embodiments may involve combinations of features, which may exist independently or in combination, and the present invention is not particularly limited to the preferred embodiments. The scope of the present invention is defined by the claims.

[0050] like Figure 1 As shown, the multi-level spacecraft system modeling method based on atomic components provided by the present invention includes the following steps:

[0051] Step S1: Complete the design of the spacecraft model system according to the mission requirements;

[0052] Step S2, designing the component interfaces of the spacecraft model system, and forming an interface diagram, an interface table, and an interface protocol file;

[0053] Step S3, developing a simulation program for a spacecraft atomic component model according to component modeling requirements;

[0054] Step S4, assembling the atomic component model through the spacecraft atomic component model simulation program, and encapsulating to form a universal spacecraft entity model;

[0055] Step S5: Parameter configuration is performed on the general spacecraft entity model to complete the construction of a specific entity and form an entity model of a specific model.

[0056] The embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0057] like Figure 2 As shown, a multi-level spacecraft system modeling method based on atomic components according to the present invention is used to establish a spacecraft system simulation system of a natural disaster emergency management remote sensing dispatch system, including the following steps:

[0058] Step S1: According to the simulation task requirements of a natural disaster emergency management remote sensing dispatching system, the spacecraft model system design is completed. Figure 3 shown.

[0059] In step S1, the spacecraft model system is a three-layer model system architecture, which includes, from bottom to top, an atomic component layer, a spacecraft entity layer, and a spacecraft domain layer.

[0060] In step S1, it specifically includes:

[0061] Step S11: According to the simulation task requirements of a natural disaster emergency management remote sensing dispatching system, the aerospace equipment entities are sorted and classified according to the entity characteristics to form a spacecraft domain layer including optical remote sensing satellites, SAR remote sensing satellites, ground support systems, etc.;

[0062] The entity characteristics include the entity platform type, the entity's business direction, the entity's affiliated unit, the payload type, etc. The entity platform types include space-based and ground-based. The entity's business directions include remote sensing, communication, navigation, and support, etc. The entity's affiliated units include the Ministry of Land and Resources, the Ministry of Forestry, the Ministry of Emergency Management, etc.

[0063] Step S12: sort out all aerospace equipment entities to be constructed for a natural disaster emergency management remote sensing dispatch system to form a spacecraft entity layer. The objects of the entity layer include: in the field of optical remote sensing satellites: Ziyuan-3 satellite entity, Gaofen-5 satellite entity, etc.; in the field of SAR remote sensing satellites: Gaofen-3 satellite entity, etc.; in the field of ground support systems: remote sensing satellite mission control center, ground measurement and control station, ground data transmission station, etc.;

[0064] Step S13: According to the aerospace equipment entity to be constructed by a natural disaster emergency management remote sensing dispatch system, the atomic components inside the aerospace equipment entity are sorted out according to the component decomposition method to form a spacecraft atomic component layer. Taking the Gaofen-5 satellite entity as an example, the atomic component layer includes satellite platform components, satellite motion components, satellite power components, satellite optical remote sensing payload components, satellite measurement and control components, satellite data transmission components, etc.; all components are combined and duplicated items are removed to form a set of all atomic components in the atomic component layer.

[0065] The component-based decomposition method includes: according to the level and granularity requirements of the simulation, referring to the subsystem composition of the aerospace equipment entity, the aerospace equipment entity is decomposed into multiple atomic components, and the components can be reused in different spacecraft entity layers.

[0066] Step S2, designing the component interfaces of the spacecraft model system sorted out in step S1, and forming an interface diagram, an interface table and an interface protocol file;

[0067] Component interface design includes external interface design, internal interface design and initialization interface design; external interface refers to the interface between aerospace equipment entities; internal interface refers to the interface between atomic components inside aerospace equipment entities.

[0068] External interface design and internal interface design are carried out through interface diagrams and interface tables; the interface table includes interface serial number, interface name, interface identifier, sender, receiver and content; the interface diagram is used to represent the topological relationship between interface serial number, sender and receiver.

[0069] In step S2, it specifically includes:

[0070] Step S21: sort out the interaction contents between aerospace equipment entities, complete the external interface design between aerospace equipment entities, and form an external interface diagram and an external interface table. Figure 4 As shown, the external interface table is shown in Table 1.

[0071] Table 1

[0072]

[0073] Step S22: sort out the interaction between the atomic components inside the aerospace equipment entity, complete the internal interface design of the aerospace equipment entity, and form an internal interface diagram and an internal interface table. Taking the Gaofen-5 satellite entity model as an example, the internal interface diagram is as follows: Figure 5 As shown, the internal interface table is shown in Table 2.

[0074]

[0075] Step S23, refine each type of external interface and internal interface, design the data characteristics of the interface transmission content, and form an interface protocol; the interface protocol is defined in the form of an interface protocol table, and the interface protocol table includes variable sequence number, variable name, variable type, data unit, meaning, and remarks; taking the track and attitude interface (NB-GDZT) in the internal interface table as an example, the refined interface protocol form is shown in Table 3 below. In addition to commonly used types such as integers, floating-point numbers, and strings, standard variable types can also be nested in custom structures.

[0076] Table 3

[0077]

[0078]

[0079] Step S24, design the initialization interface of the atomic components that constitute the aerospace equipment entity; the initialization interface refers to the static inherent attribute parameters of the atomic components. Taking the initialization interface (INIT-WXYD) of the satellite motion component as an example, the detailed initialization interface protocol form is shown in Table 4 below. In addition to commonly used types such as integers, floating-point numbers, and strings, standard variable types can also be nested using custom structures.

[0080] Table 4

[0081] Serial number Variable Name Variable Types Data Unit meaning Remark 1. EpochTime UTCTime / UTC time in epoch none 2. SemiMajorAxis double m Satellite initialization orbit elements, semi-major axis none 3. Eccentricity double / Satellite initialization orbit elements, eccentricity none 4. Inclination double deg Satellite initialization orbit elements, orbit inclination none 5. RAAN double deg Satellite initialization orbit elements, ascending node right ascension none 6. Omega double deg Satellite initialization orbit elements, perigee argument none 7. TrueAnomaly double deg Satellite initialization orbit elements, true anomaly none 8. SatMass double kg Satellite initial mass none 9. EngineThrust double N Satellite orbit control engine thrust none 10. EngineISP double s Specific impulse value of satellite orbit control engine none 11. SatAttAngle double deg Satellite attitude adjustment maximum roll angle none 12. SatAttAngleRate double deg / s Satellite attitude adjustment maximum angular velocity none

[0082] Step S3, developing a simulation program for the spacecraft atomic component model according to the interface design requirements of step S2 and the component modeling requirements;

[0083] In step S3, it specifically includes:

[0084] Step S31, construct an atomic component code framework according to the simulation modeling specification requirements; the atomic component code framework includes a simulation initialization function, a simulation step function and a simulation termination function; taking the satellite motion component as an example, the three types of function names are SatMotion_init(), SatMotion_Step(), and SatMotion_Stop().

[0085] The SatMotion_init() function mainly completes the initialization of variables related to satellite motion, loading of resource files, pre-allocation of memory space, and other processing. For example: calculating the position, speed, and attitude of the satellite at the initial simulation time based on the orbital elements at the satellite epoch, and loading the ephemeris file in advance.

[0086] The SatMotion_Step() function mainly completes the update of satellite motion data and the working status of motion components in each simulation step. Depending on whether there is an orbit change instruction, the orbital dynamics algorithm is called to update the satellite's position, velocity, orbital elements, and attitude at the current simulation time.

[0087] The SatMotion_Stop() function mainly completes operations such as class destruction and release of related memory resources when the simulation ends.

[0088] Step S32, according to the external interface, internal interface and interface protocol designed in step S2, and according to the interface identifier, write the data receiving function and the data output function; they are XX_InputInterface() function and XX_OutputInterface() function respectively. Taking the satellite motion component as an example, the orbit and attitude interface (NB-GDZT) is the output interface, and the function name is named NBGDZT_OutputInterface(). This function mainly formats the orbit and attitude data calculated in the SatMotion_Step() function according to the interface protocol in step S23.

[0089] Step S33, in order to make programming more standardized, write special business functions; special business functions are used to implement specific functions of atomic components; taking the satellite motion component as an example, a high-precision orbit predictor can write a separate HPOP_OrbitPredictor() function, in which the conversion and integral calculation of orbit data are realized, etc., to facilitate the calling of functions such as SatMotion_Step() in S31.

[0090] Step S34, debug the simulation component function, and iteratively update the component function according to the debugging result; the component function includes a simulation initialization function, a data receiving function, a simulation stepping function, a data output function, a simulation termination function and a special service function;

[0091] The simulation initialization function mainly completes the initialization assignment of internal variables of the atomic component model and the loading of resource files; the data receiving function mainly receives the interactive data in the input interface of the atomic component, and performs parsing, conversion and processing; the simulation step function mainly completes the access of the atomic component input data and the calculation of the status data of this simulation time step, and is the most important function in the atomic component; the data output function mainly completes the conversion, arrangement, output and other operations of the atomic component output interface data; the simulation termination function mainly completes the memory release, class instance destruction, process exit and other operations; the special business function mainly completes the related functions required for the implementation of the atomic component model.

[0092] All functions are written to meet programming language specifications and comment requirements.

[0093] Step S35: After the component debugging is completed, the relevant codes are compiled to generate a dynamic runtime library or an executable file, and the development of the spacecraft atomic component model simulation program is completed.

[0094] Step S4, assembling the atomic component model through a spacecraft atomic component model simulation program, and encapsulating to form a universal spacecraft entity model;

[0095] In step S4, it specifically includes:

[0096] Step S41, uploading the dynamic runtime library or executable file generated in step S35 to the model assembly software or model assembly tool to store and manage the model;

[0097] Step S42, constructing a new spacecraft entity model instance according to the spacecraft entity layer object of step S12;

[0098] Step S43, according to the spacecraft atomic component layer of step S13, through the model assembly function provided by the model assembly software or tool, select multiple atomic components, assemble a spacecraft entity model instance, encapsulate and save it, and form a general spacecraft entity model.

[0099] Step S5: Parameter configuration is performed on the general spacecraft entity model to complete the construction of the specific entity and form an entity model of a specific model.

[0100] In step S51, it specifically includes:

[0101] Step S51, save the universal spacecraft entity model, and name the universal spacecraft entity model as the satellite name;

[0102] Step S52, obtaining a list of atomic component models of the renamed universal spacecraft entity model;

[0103] Step S53: Parameter configuration is performed on the atomic components in the atomic component model list one by one, and parameter assignment is performed through the initialization interface of the atomic components;

[0104] Step S54: After the parameter configuration is completed, the model is saved to form a physical model of a specific model.

[0105] It should also be noted that, in this article, the terms "include", "comprises" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or terminal device including a series of elements includes not only those elements, but also includes other elements not explicitly listed, or also includes elements inherent to such process, method, article or terminal device. In the absence of further restrictions, the elements defined by the sentence "comprises a ..." do not exclude the existence of other identical elements in the process, method, article or terminal device including the elements.

[0106] Finally, it should be noted that the above is a preferred embodiment of the present invention. It should be pointed out that although the preferred embodiment of the present invention has been described, for those skilled in the art, once the basic creative concept of the present invention is known, several improvements and modifications can be made without departing from the principles of the present invention, and these improvements and modifications should also be regarded as the protection scope of the present invention. Therefore, the attached claims are intended to be interpreted as including the preferred embodiment and all changes and modifications that fall within the scope of the embodiments of the present invention.

Claims

1. A multi-level spacecraft system modeling method based on atomic components, characterized in that: The following steps are involved: Step S1: Complete the design of the spacecraft model system according to the mission requirements; Step S2, designing the component interfaces of the spacecraft model system to form an interface diagram, an interface table and an interface protocol file; Step S3, developing a simulation program for a spacecraft atomic component model according to component modeling requirements; Step S4, assembling the atomic component model through the spacecraft atomic component model simulation program, and encapsulating to form a universal spacecraft entity model; Step S5: Parameter configuration is performed on the general spacecraft entity model to complete the construction of a specific entity and form an entity model of a specific model.

2. The multi-level spacecraft system modeling method based on atomic components according to claim 1 is characterized in that: In step S1, the spacecraft model system is a three-layer model system architecture, which includes, from bottom to top, an atomic component layer, a spacecraft entity layer, and a spacecraft domain layer.

3. The atomic component-based multi-level spacecraft system modeling method according to claim 2 is characterized in that: In the step S1, it specifically includes: Step S11: According to the simulation task requirements, the aerospace equipment entities are sorted and classified according to the entity characteristics to form the spacecraft field layer. The entity characteristics include the entity platform type, the business direction of the entity, the entity's affiliated unit, and the payload type. The entity platform type includes space-based and ground-based. The entity's affiliated business direction includes remote sensing, communication, navigation, and support. The entity's affiliated units include the Ministry of Land and Resources, the Ministry of Forestry, and the Ministry of Emergency Management. Step S12: sort out all the aerospace equipment entities to be constructed to form a spacecraft entity layer; Step S13: According to the aerospace equipment entity to be constructed, the atomic components inside the aerospace equipment entity are sorted out according to the component decomposition method to form a spacecraft atomic component layer; The component splitting method includes: splitting the aerospace equipment entity into multiple atomic components according to the level and granularity requirements of the simulation and referring to the subsystem composition of the aerospace equipment entity. The components can be reused in different spacecraft entity layers.

4. The atomic component-based multi-level spacecraft system modeling method according to claim 3 is characterized in that: The component interface design includes external interface design, internal interface design and initialization interface design; the external interface refers to the interface between the aerospace equipment entities; the internal interface refers to the interface between the atomic components inside the aerospace equipment entities.

5. The atomic component-based multi-level spacecraft system modeling method according to claim 4 is characterized in that: In the step S2, it specifically includes: Step S21, sorting out the interaction contents between the aerospace equipment entities, and completing the external interface design between the aerospace equipment entities; Step S22: sorting out the interaction contents between the atomic components inside the aerospace equipment entity, and completing the internal interface design of the aerospace equipment entity; Step S23, refine each type of external interface and internal interface, design the data characteristics of the interface transmission content, and form an interface protocol; the interface protocol is defined in the form of an interface protocol table, and the interface protocol table includes variable sequence number, variable name, variable type, data unit, meaning, and remarks; Step S24, designing the initialization interface of the atomic components constituting the aerospace equipment entity; the initialization interface refers to the static inherent attribute parameters of the atomic components.

6. The atomic component-based multi-level spacecraft system modeling method according to claim 5, characterized in that: The external interface design and the internal interface design are performed through an interface diagram and an interface table; the interface table includes an interface serial number, an interface name, an interface identifier, a sender, a receiver and content; the interface diagram is used to represent the topological relationship between the interface serial number, the sender and the receiver.

7. The atomic component-based multi-level spacecraft system modeling method according to claim 2, characterized in that: In the step S3, it specifically includes: Step S31, constructing an atomic component code framework according to the simulation modeling specification requirements; the atomic component code framework includes a simulation initialization function, a simulation step function and a simulation termination function; Step S32, according to the external interface, internal interface and interface protocol designed in step S2, and according to the interface identifier, write a data receiving function and a data output function; Step S33: write special business functions; the special business functions are used to implement specific functions of atomic components; Step S34, debugging the simulation component function, and iteratively updating the component function according to the debugging result; the component function includes the simulation initialization function, the data receiving function, the simulation stepping function, the data output function, the simulation termination function and the special service function; Step S35, after the component debugging is completed, the relevant codes are compiled to generate a dynamic runtime library or an executable file, and the development of the spacecraft atomic component model simulation program is completed.

8. The atomic component-based multi-level spacecraft system modeling method according to claim 7, characterized in that: In the step S4, it specifically includes: Step S41, uploading the dynamic runtime library or the executable file to the model assembly software or model assembly tool to store and manage the model; Step S42: construct a new spacecraft entity model instance according to the spacecraft entity layer object; Step S43, according to the atomic component layer, through the model assembly function provided by the model assembly software or tool, multiple atomic components are selected to assemble a spacecraft entity model instance, which is packaged and saved to form the general spacecraft entity model.

9. The atomic component-based multi-level spacecraft system modeling method according to claim 1, characterized in that: In the step S5, it specifically includes: Step S51, saving the universal spacecraft entity model and renaming it; Step S52, obtaining a renamed atomic component model composition list of the universal spacecraft entity model; Step S53, performing parameter configuration on the atomic components in the atomic component model list one by one, and performing parameter assignment through the initialization interface of the atomic components; Step S54: After the parameter configuration is completed, the model is saved to form a physical model of a specific model.

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