Space system simulation deduction management system and construction method thereof

Abstract

The application relates to a space system simulation deduction management system based on a scheme and a strategy and a construction method thereof, which comprises a simulation scheme design module, a simulation strategy management module, a simulation instruction management module, a simulation scheduling management module, a simulation task design module, a simulation object function model and a simulation display module. The application realizes the design, automatic optimization control and state parallel evolution of a flight task process, so that in the simulation process, the reasonable working mode control of a spacecraft can be realized based on the simulation state of the space system.

Description

Technical Field

[0001] This invention relates to the field of spacecraft simulation and management technology, and in particular to a spacecraft system simulation and management system based on schemes and strategies, and its construction method. Background Technology

[0002] Currently, my country has formed a spacecraft system covering the main applications of aerospace, which can provide functions and services such as remote sensing Earth observation, emergency information support, broadcast communication, and satellite navigation. A series of studies on mission simulation and capability assessment of the aerospace system are also underway, which can provide certain data support for future aerospace system planning and demonstration, on-orbit satellite system maintenance, and mission application.

[0003] Aerospace system simulation analysis and evaluation are generally based on a given system composition and mission background. Under a specified or established mission process, evaluation indicators are formulated, and system capabilities and mission effectiveness are evaluated based on simulation calculation results. The basic process includes: determining the simulation mission background and the composition of the simulation object; formulating the mission process and evaluation indicators for the simulation object; establishing simulation model algorithms and evaluation algorithms; conducting simulation calculations and obtaining simulation data; and forming evaluation conclusions based on the simulation results. The simulation model algorithms and evaluation algorithms can be developed according to the actual entity object attributes, simulation granularity, and evaluation requirements to form a compliant process algorithm.

[0004] Currently, the simulation and verification process for various spacecraft, including satellites, focuses more on mission completion, such as target detection results and detection effectiveness, equipment working parameters and baseline capabilities. System development is generally based on predetermined verification scenarios or mission processes, that is, establishing background functional simulation models, working procedures and scripts, and completing experimental verification or performance analysis calculations with the support of simulation platforms, which has strong mission specificity. For example, in "Simulation Design and Application of High-Resolution Satellite On-Orbit Operation Mission Management" (see "Design and On-Orbit Verification of High-Resolution Multi-Mode Satellite Working Mode", Fan Lijia, Proceedings of the 7th Annual Conference on High-Resolution Earth Observation, 2020), a mission simulation verification system supporting the imaging working mode of the High-Resolution Multi-Mode Satellite was constructed; in "Research on On-Site Autonomous Mission Planning Method Based on Evolutionary Rules" (see "Research on On-Site Autonomous Mission Planning Method Based on Evolutionary Rules", Applied Optics, Sun Mingyuan et al., 2021, Vol. 42, No. 3), an on-board mission planning algorithm based on genetic programming was proposed; and in "Simulation and Parallel System of Spacecraft Flight Control" (see "Simulation and Parallel System of Spacecraft Flight Control", Journal of Astronautics, 2021, Vol. 42, No. 8), a simulation parallel system supporting the flight control operation of Chang'e-5 was constructed.

[0005] The above-mentioned research and analysis evaluation methods are limited to the specific task background and local functional verification of the research object. They cannot design the process changes of the simulation task according to the engineering task requirements, do not realize the self-organization and management function of the task process, the overall task process cannot be automatically adjusted and optimized according to the calculation state, and do not reflect the changes in the task process caused by the overall situation. Summary of the Invention

[0006] To address the technical problems existing in the prior art, the present invention aims to provide a space system simulation and management system based on schemes and strategies, and its construction method, which can make real-time judgments on the simulation status of the space system and control the spacecraft's reasonable working mode.

[0007] To achieve the above-mentioned objectives, this invention provides an aerospace system simulation and simulation management system, including a simulation scheme design module, a simulation strategy management module, a simulation instruction management module, a simulation scheduling management module, a simulation task design module, a simulation object functional model, and a simulation display module.

[0008] According to one technical solution of the present invention, the simulation scheme design module is used to implement the initial simulation scheme design, specify the working procedure and control instructions of the spacecraft in the simulation mission, and output the simulation scheme data and spacecraft control instructions;

[0009] The simulation strategy management module is used to implement spacecraft operating procedure conventions, define various operating procedure constraints and state transition relationships, and output the spacecraft operating procedure handling results.

[0010] The simulation instruction management module is used to implement the basic instruction set conventions for various working procedures of spacecraft, specify the basic instruction sequence and instruction parameter data for various working procedures, and output the basic instruction queue of working procedures.

[0011] The simulation scheduling and management module is used to connect and schedule services with other modules, receive and distribute data, implement clock synchronization control of the system, schedule and distribute control commands for spacecraft work procedures, and enable information exchange between the system and other external engineering systems.

[0012] According to one technical solution of the present invention, the simulation task design module is used to implement simulation scene design, specify the entity composition, entity parameters, inter-entity relationships, and simulation environment in the simulation task, and output the simulation model composition, initial parameters of the simulation model, and initial simulation state.

[0013] The simulation object functional model includes multiple simulation calculation modules, which are used to perform the necessary calculations on the spacecraft entity to meet business requirements and mission objectives.

[0014] The simulation display module is used to implement the interface design of all input data and the interface display of all output data in the system; it also enables external data transmission and reception and clock synchronization through the simulation display service.

[0015] According to one technical solution of the present invention, the simulation calculation module includes at least a spacecraft dynamics calculation module, a spacecraft platform subsystem simulation calculation module, a spacecraft payload subsystem simulation calculation module, a ground station simulation calculation module, and a space environment simulation module.

[0016] According to one technical solution of the present invention, it is implemented based on a BS architecture, with all modules and services deployed on a server computer, and simulation control and monitoring achieved through a client web browser; all computing functions of the modules are encapsulated through services, and the modules call each other through services.

[0017] According to one aspect of the present invention, a method for constructing a space system simulation and deduction management system as described in any of the above technical solutions is provided, comprising the following steps:

[0018] Step S1: Select a simulation platform, establish a simulation scheduling management module, establish a scheduling support framework service, a dedicated external interface service, and a job program management service to realize the system's computational management;

[0019] Step S2: Establish a functional model of the simulation object based on the simulation platform, configure the data interface of the functional model of the simulation object based on the simulation platform, establish data communication between various modules, establish control command interface between various modules and simulation scheduling and management module, and output the calculation result data structure.

[0020] Step S3: Establish a simulation instruction management module to implement the same working process definition as the main body of each working mode in the actual installation, and output the simulation instruction library;

[0021] Step S4: Establish a simulation strategy management module to implement the state machine model of each simulation instruction and output the execution and switching conditions of each working mode and instruction;

[0022] Step S5: Establish a simulation scheme design module, design the overall information and stage details of the simulation task, and output the overall scheme design results and stage details.

[0023] Step S6: Establish a simulation task design module, design the simulation task scenario components, including the aerospace system object components, object parameters, object working process, battlefield environment, and time range; output data information structure, output design results to the simulation engine initialization method, wherein the object working process is composed of a time-based working mode sequence;

[0024] Step S7: Display the centroid position, velocity, pointing result information, and working status information of the aerospace system through visualization methods such as pie charts, curves, and cloud maps; demonstrate the self-organization and adjustment of the mission process; and display the system simulation calculation results.

[0025] According to a technical solution of the present invention, step S1 specifically includes:

[0026] The simulation simulation management system implements functions and services based on the simulation engine, including at least the management of computation module parameters, computation module computation scheduling, data distribution scheduling and interaction management, time consistency management, and computer computing resource allocation; it implements the distribution control of data structures between modules of the simulation object functional model through the simulation engine's data subscription and data sending methods; and it implements the initialization data interaction between the simulation engine and the simulation object functional model through the simulation engine's initialization method.

[0027] Establish an external interface service file / message interface channel to realize the reception, parsing and sending of messages and files that need to be transmitted between the simulation and simulation management system and other external software systems, and the scheduling support framework service.

[0028] Establish an engineering data protocol interface channel for external interface services to receive, parse, and send data information that needs to be transmitted between the simulation and simulation management system and external on-orbit or equipment systems, and provide scheduling support framework services.

[0029] Establish an external interface service engineering instruction protocol interface channel to realize the reception, parsing and sending of control instruction information that needs to be transmitted between the simulation and simulation management system and the external engineering test system;

[0030] A simulation engine workflow management service is established to retrieve task processes from the simulation task design module, simulation scheme design module, simulation instruction management module, simulation strategy management module, and engineering instruction protocol interface channel; orchestrate and generate control instructions; enable self-organizing adjustment of task processes and send them to the calculation module; before the simulation starts, retrieve task processes from the simulation scheme design module and generate a set of task process instructions with strategies by referring to the simulation instruction library; during the simulation, update the instruction queue according to the strategy and engineering instruction protocol interface channel information and broadcast it to the simulation calculation module.

[0031] According to one technical solution of the present invention, step S2 specifically includes:

[0032] Establish basic computing functions and utilize the principles of orbital dynamics, attitude dynamics, and physical physics to realize spacecraft dynamics calculations, platform state calculations, payload state calculations, ground station state calculations, and space environment state calculations. Calculate and obtain the center of mass position, velocity, pointing results, and field distribution information of the spacecraft platform, payload, space environment, and ground station.

[0033] Establish working mode and command management functions to manage each working mode, implement basic calculation functions to respond to the working mode, manage each control command, and implement basic calculation functions to respond to the command, including at least track control, equipment start-up and shutdown, attitude control, and state switching; output the results and status to a data structure.

[0034] Establish a data interface function, and configure the connection of the model data interface based on the simulation platform to realize the data communication between the calculation modules. The model obtains input information, including data calculation results and instruction information, according to the ISIM data subscription method, and outputs result information according to the simulation platform data sending method; at the same time, the output result information structure is synchronously sent to the message queue.

[0035] The simulation model is packaged into a usable program file according to the calling requirements of the simulation platform's computing modules, forming a computing service that can be used by the simulation engine.

[0036] According to one technical solution of the present invention, step S5 specifically includes:

[0037] The simulation task design module obtains overall simulation task information, including scheme name, scheme time, and scheme style. It also designs the stage information in the overall simulation task information, including the identifier, objective, name, time, available entity model, and transition conditions for each stage. The design results are then output to the simulation engine's initialization method.

[0038] Detailed design phase information, including the identifier, objectives, name, time, available entity models, transition conditions, and task package information for each phase. Task package information includes task objectives, entity models used, entity operation control instructions, and entity model name, action to be performed, action object, instruction execution time, and instruction parameters. The design results are output to the simulation engine's job program management service.

[0039] According to one technical solution of the present invention, step S7 specifically includes:

[0040] Receive information on the center of mass position, velocity, pointing results, and operational status of the aerospace system through a message queue;

[0041] Data on motion trajectory, velocity direction, injury degree, and assessment results are established using visualization methods such as pie charts, curves, and cloud maps.

[0042] The task process and instruction execution status are established using a curve method.

[0043] Compared with the prior art, the present invention has the following beneficial effects:

[0044] According to the present invention, a complete self-organizing simulation process based on schemes and strategies is established, including a simulation scheme design module, a simulation strategy design module, a simulation instruction management module, and a simulation scheduling management module. During the simulation process, the simulation scheme and simulation strategy can be designed based on the initial simulation scheme, and the simulation process can be dynamically and automatically adjusted through control instructions based on the real-time calculation results of the simulation object. A simulation system and software supporting task process control are established.

[0045] The simulation control command adjustment is determined by a state machine based on the actual working process and engineering constraints of the simulation object. Based on preconditions, termination conditions, permission conditions, and immediate execution conditions, the simulation process, which previously followed scripts and other predetermined designs, is enriched. Based on the scheme, strategy, and control command, a simulation process control method that coordinates the simulation before and during the simulation can be given, thereby updating the subsequent simulation process in real time and realizing the self-organization and optimization of the task process.

[0046] The aerospace system simulation and analysis management system of the present invention is highly operable and can be used as an improvement to existing aerospace system simulation analysis and evaluation tools, enriching simulation and evolution results. Attached Figure Description

[0047] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly described below. Obviously, the drawings described below are merely some embodiments of the present invention, and those skilled in the art can obtain other drawings based on these drawings without creative effort.

[0048] Figure 1 This diagram illustrates a space system simulation and management system provided in an embodiment of the present invention.

[0049] Figure 2 This is a schematic diagram illustrating the workflow management service provided in an embodiment of the present invention. Detailed Implementation

[0050] The description of the embodiments in this specification should be taken in conjunction with the accompanying drawings, which should form part of the complete specification. In the drawings, the shape or thickness of the embodiments may be exaggerated and may be indicated in a simplified or convenient manner. Furthermore, parts of the various structures in the drawings will be described separately; it is worth noting that elements not shown in the figures or not described in words are in a form known to those skilled in the art.

[0051] The descriptions of the embodiments herein, including any references to directions and orientations, are for ease of description only and should not be construed as limiting the scope of the invention. The following description of preferred embodiments involves combinations of features, which may exist independently or in combination; the invention is not particularly limited to the preferred embodiments. The scope of the invention is defined by the claims.

[0052] like Figure 1 As shown, the aerospace system simulation and simulation management system of the present invention includes a simulation scheme design module, a simulation strategy management module, a simulation command management module, a simulation scheduling management module, a simulation task design module, a simulation object functional model, and a simulation display module.

[0053] Through the simulation mission design module, simulation scheme design module, simulation strategy management module, simulation command management module, and simulation scheduling management module, the design, automatic optimization control, and parallel state evolution of the flight mission process are realized. Thus, during the simulation process, the spacecraft's reasonable working mode control can be carried out in real time based on the simulation state of the aerospace system.

[0054] In one embodiment of the present invention, preferably, the simulation scheme design module is used to implement the initial simulation scheme design, specify the working procedure and control instructions of the spacecraft in the simulation task, and output the simulation scheme data and spacecraft control instructions;

[0055] The simulation strategy management module is used to implement spacecraft operating procedure conventions, define various operating procedure constraints and state transition relationships, and output the spacecraft operating procedure handling results.

[0056] The simulation instruction management module is used to implement the basic instruction set conventions for various working procedures of spacecraft, specify the basic instruction sequence and instruction parameter data for various working procedures, and output the basic instruction queue of working procedures.

[0057] The simulation scheduling and management module is used to connect and schedule services with other modules, receive and distribute data, implement clock synchronization control of the system, schedule and distribute control commands for spacecraft work procedures, and enable information exchange between the system and other external engineering systems.

[0058] Specifically, when establishing the simulation command management module, the same working process as the actual installation of each working mode is established. Various basic working modes of the spacecraft are formed by controlling the command sequence. For each command, command type, command semantics, command code, command time, basic command parameters, dynamic data, verification words, etc. are established to form a command and working mode database. The basic command parameters remain unchanged in the simulation application. Dynamic data refers to the command definition without setting specific parameter values. By specifying the information source and requirements, the calculation result data of the spacecraft simulation calculation module is read as required in the simulation application as command parameters to complete the real-time dynamic reorganization of command codewords and the work procedure management service of forwarding them into the system.

[0059] For the various basic working modes and instructions within those modes in the simulation instruction management module, the simulation strategy management module can establish a state machine model, design state execution and switching conditions, including preconditions, termination conditions, permission conditions, and immediate execution instructions. It specifies the condition types, engineering variable associations, judgment conditions, and actions taken when conditions are not met. Preconditions are entry permission judgments; when the calculation results of the associated engineering variable data during simulation meet the judgment conditions, the instruction is allowed to execute. Otherwise, the corresponding basic working mode is executed according to the specified disposal threshold. Termination conditions are the result judgment conditions of the action; when the calculation results of the associated engineering variable data during simulation meet the judgment conditions, the execution of this instruction ends. Permission conditions allow entry into the working mode only when these conditions are met; otherwise, the system waits until the conditions are met. Immediate execution instructions execute immediately when the calculation results of the associated engineering variable data during simulation meet the judgment conditions. The union of multiple execution conditions is used.

[0060] In establishing the simulation scheme design module, a scheme design template is first created, specifying the overall information and phase details of the simulation task. The overall information specifies the overall scheme information and phase overall information. The overall scheme information includes the scheme name, scheme time, and scheme style. The phase overall information specifies the identifier, objective, name, time, available entity models, and transition conditions for each phase. In addition to the overall information for each phase, the phase details specify the task package information for this phase. The task package information specifies the objective, application direction, available entity models, and various entity work control command information. The control command information includes the entity model name, execution action, action object, command execution time, and command parameters. Before the simulation begins, the overall scheme design results are written into the overall parameters of the spacecraft simulation calculation module, and the task package information is parsed into command codewords and forwarded to the work program management service within the system.

[0061] To establish a simulation scheduling and management module, it is necessary to build general internal system functions and services, such as computing module parameter management, computing module computing scheduling, data distribution scheduling and interaction management, time consistency management, and computer computing resource allocation; commercial software architectures such as ISIM simulation platform and XSIM simulation platform or other self-developed software architectures can be adopted;

[0062] Furthermore, based on general distribution scheduling and interactive management, a dedicated external interface service is built, establishing a file / message interface channel to realize the transmission of messages and files between this system and other external software systems, and parsing file data content, such as task programs and task times, and transferring it to the overall parameters of the spacecraft simulation calculation module within the system; an engineering command protocol interface channel is built to realize the transmission of control command information between this system and external engineering test systems, and parsing it into command codewords and forwarding it to the working program management service within the system to update the command queue; an engineering data protocol interface channel is built to realize the transmission of data information between this system and external on-orbit or equipment systems, and parsing and forwarding it to the spacecraft simulation calculation module within the system, writing it into the corresponding data memory of the module, and directly modifying the data results to complete data injection;

[0063] At the same time, a work procedure management service will be established, including:

[0064] First, before the simulation begins, the simulation scheme is parsed based on the basic working mode to form a sequence of control instructions, and various conditions of the basic working mode specified in the simulation strategy are obtained to form a sequence of control instructions with execution constraints.

[0065] During the simulation, before the control command is executed, the execution requirements are compared with the spacecraft simulation state data specified by the conditions. Based on the comparison results, the handling method is executed, the subsequent command queue is updated according to the handling method, the command queue is written into the command memory, and broadcast to the spacecraft simulation calculation module.

[0066] The specific work procedure management service process is as follows: Figure 2 As shown, the process includes: running the test step; obtaining the list of instructions executed in the previous step; obtaining the output of the model in the previous step; determining whether the instruction completion condition is met; if yes, proceeding to the next step; otherwise, returning to the first step; recording instruction completion; reading the next instruction; determining whether there are any instructions waiting to be executed; if yes, proceeding to the next step; otherwise, ending directly; determining whether the instruction occurrence condition is met; if yes, proceeding to the next step; otherwise, ending this step; sending instructions to the external network and to the nodes; ending this step; and returning to the first step after this step is completed.

[0067] When establishing the simulation display module, it receives all output data from the spacecraft system simulation business calculation module, such as the position, velocity, relative relationship, and working results of all simulated entities. It then displays multi-dimensional information in the form of tables, curves, animations, and in the form of two-dimensional maps, two-dimensional views, and three-dimensional maps, in a way that is consistent with the time of the simulation scheduling support framework. The simulation display service and message structure receive the above output data from the simulation scheduling management module.

[0068] In one embodiment of the present invention, preferably, the simulation task design module is used to implement simulation scene design, specify the entity composition, entity parameters, inter-entity relationships, and simulation environment in the simulation task, and output the simulation model composition, initial parameters of the simulation model, and initial simulation state.

[0069] The simulation object functional model includes multiple simulation calculation modules, which are used to perform the necessary calculations on the spacecraft entity to meet business requirements and mission objectives.

[0070] The simulation display module is used to implement the interface design of all input data and the interface display of all output data in the system; it also enables external data transmission and reception and clock synchronization through the simulation display service.

[0071] In one embodiment of the present invention, preferably, the simulation calculation module includes at least a spacecraft dynamics calculation module, a spacecraft platform subsystem simulation calculation module, a spacecraft payload subsystem simulation calculation module, a ground station simulation calculation module, and a space environment simulation module.

[0072] The simulation object functional model includes a variety of simulation calculation modules, such as the spacecraft dynamics calculation module to realize the spacecraft's orbit calculation, receive the simulation time, the position, velocity, orbital maneuver strategy, and attitude information of the spacecraft's center of mass at the previous moment, and generate the position, velocity, and attitude information of the spacecraft's center of mass at the current moment;

[0073] For example, the spacecraft platform subsystem simulation calculation module receives simulation time, the previous moment's status data such as solar panel power, battery charging and discharging status, node temperature, and health status of various subsystems of the spacecraft platform (mechanical, electrical, thermal, etc.), realizes the calculation of functions such as attitude control, power supply and distribution balance, and data management, and outputs the simulation time, the current moment's spacecraft solar panel power, battery charging and discharging status, node temperature, health status subsystem status data, and working mode.

[0074] For example, the spacecraft payload subsystem simulation calculation module realizes the function and status calculation of the spacecraft payload equipment, receives the simulation time, the status data and working mode of the spacecraft payload equipment at the previous moment, calculates the detection results of the spacecraft payload equipment at the simulation time and the current moment, and outputs the simulation time, the status data and working mode of the spacecraft payload equipment at the current moment.

[0075] For example, the space environment simulation module calculates the positions of the Sun, Earth, and Moon, taking the simulation time, the previous position information of the Sun, Earth, and Moon, and the spacecraft's position and orientation information as inputs, and outputs the positions of the Sun, Earth, and Moon in various coordinate systems and the position and orientation information of the Sun, Earth, and Moon relative to the spacecraft; the ground station simulation calculation module calculates the telemetry, tracking, and command (TT&C) data transmission conditions between the spacecraft and the ground station, taking the simulation time, the previous position and orientation information of the ground station and the spacecraft as inputs, and outputs the simulation time and the visible status information of the spacecraft relative to the ground station at the current moment;

[0076] The above output data is received and sent to the simulation scheduling and management module through the spacecraft system simulation business computing service and message structure.

[0077] The simulation object's functional model has multiple simulation calculation modules that can also receive control commands, parse command parameters such as orbit change, charging, imaging, steering, and mechanism rotation, and specific parameters such as command execution time, rotation target, and command start time. It can also execute commands according to the command parameters and output command execution status and spacecraft status. The simulation system simulation business calculation service and message structure are used to receive and send the above output data to the simulation scheduling and management module.

[0078] In one embodiment of the present invention, preferably, it is implemented based on a B / S architecture, with all modules and services deployed on a server computer, and simulation control and monitoring achieved through a client web browser; all computing functions of the modules are encapsulated through services, and the modules call each other through services.

[0079] According to one aspect of the present invention, a method for constructing a space system simulation and deduction management system as described in any of the above technical solutions is provided, comprising the following steps:

[0080] Step S1: Select a simulation platform, which can be ISIM. Establish a simulation scheduling management module, and establish scheduling support framework services, dedicated external interface services, and job management services to realize the computational management of the system.

[0081] Step S2: Establish a functional model of the simulation object based on the simulation platform, configure the data interface of the functional model of the simulation object based on the simulation platform, establish data communication between various modules, establish control command interface between various modules and simulation scheduling and management module, and output the calculation result data structure.

[0082] Step S3: Establish a simulation instruction management module to implement the same working process definition as the main body of each working mode in the actual installation, and output the simulation instruction library;

[0083] Step S4: Establish a simulation strategy management module to implement the state machine model of each simulation instruction and output the execution and switching conditions of each working mode and instruction;

[0084] Step S5: Establish a simulation scheme design module, design the overall information and stage details of the simulation task, and output the overall scheme design results and stage details.

[0085] Step S6: Establish a simulation task design module, design the simulation task scenario components, including the aerospace system object components, object parameters, object working process, battlefield environment, and time range; output data information structure, output design results to the simulation engine initialization method, wherein the object working process is composed of a time-based working mode sequence;

[0086] Step S7: Display the centroid position, velocity, pointing result information, and working status information of the aerospace system through visualization methods such as pie charts, curves, and cloud maps; demonstrate the self-organization and adjustment of the mission process; and display the system simulation calculation results.

[0087] In this embodiment,

[0088] In one embodiment of the present invention, preferably, step S1 specifically includes:

[0089] The simulation simulation management system implements functions and services based on the simulation engine, including at least the management of computation module parameters, computation module computation scheduling, data distribution scheduling and interaction management, time consistency management, and computer computing resource allocation; it implements the distribution control of data structures between modules of the simulation object functional model through the simulation engine's data subscription and data sending methods; and it implements the initialization data interaction between the simulation engine and the simulation object functional model through the simulation engine's initialization method.

[0090] Establish an external interface service file / message interface channel to realize the reception, parsing and sending of messages and files that need to be transmitted between the simulation and simulation management system and other external software systems, and the scheduling support framework service.

[0091] Establish an engineering data protocol interface channel for external interface services to receive, parse, and send data information that needs to be transmitted between the simulation and simulation management system and external on-orbit or equipment systems, and provide scheduling support framework services.

[0092] Establish an external interface service engineering instruction protocol interface channel to realize the reception, parsing and sending of control instruction information that needs to be transmitted between the simulation and simulation management system and the external engineering test system;

[0093] A simulation engine workflow management service is established to retrieve task processes from the simulation task design module, simulation scheme design module, simulation instruction management module, simulation strategy management module, and engineering instruction protocol interface channel; orchestrate and generate control instructions; enable self-organizing adjustment of task processes and send them to the calculation module; before the simulation starts, retrieve task processes from the simulation scheme design module and generate a set of task process instructions with strategies by referring to the simulation instruction library; during the simulation, update the instruction queue according to the strategy and engineering instruction protocol interface channel information and broadcast it to the simulation calculation module.

[0094] In one embodiment of the present invention, preferably, step S2 specifically includes:

[0095] Establish basic computing functions and utilize the principles of orbital dynamics, attitude dynamics, and physical physics to realize spacecraft dynamics calculations, platform state calculations, payload state calculations, ground station state calculations, and space environment state calculations. Calculate and obtain the center of mass position, velocity, pointing results, and field distribution information of the spacecraft platform, payload, space environment, and ground station.

[0096] Establish working mode and command management functions to manage each working mode, implement basic calculation functions to respond to the working mode, manage each control command, and implement basic calculation functions to respond to the command, including at least track control, equipment start-up and shutdown, attitude control, and state switching; output the results and status to a data structure.

[0097] Establish a data interface function, and configure the connection of the model data interface based on the simulation platform to realize the data communication between the calculation modules. The model obtains input information, including data calculation results and instruction information, according to the ISIM data subscription method, and outputs result information according to the simulation platform data sending method; at the same time, the output result information structure is synchronously sent to the message queue.

[0098] The simulation model is packaged into a usable program file according to the calling requirements of the simulation platform's computing modules, forming a computing service that can be used by the simulation engine.

[0099] In one embodiment of the present invention, preferably, step S5 specifically includes:

[0100] The simulation task design module obtains overall simulation task information, including scheme name, scheme time, and scheme style. It also designs the stage information in the overall simulation task information, including the identifier, objective, name, time, available entity model, and transition conditions for each stage. The design results are then output to the simulation engine's initialization method.

[0101] Detailed design phase information, including the identifier, objectives, name, time, available entity models, transition conditions, and task package information for each phase. Task package information includes task objectives, entity models used, entity operation control instructions, and entity model name, action to be performed, action object, instruction execution time, and instruction parameters. The design results are output to the simulation engine's job program management service.

[0102] In one embodiment of the present invention, preferably, step S7 specifically includes:

[0103] Receive information on the center of mass position, velocity, pointing results, and operational status of the aerospace system through a message queue;

[0104] Data on motion trajectory, velocity direction, injury degree, and assessment results are established using visualization methods such as pie charts, curves, and cloud maps.

[0105] The task process and instruction execution status are established using a curve method.

[0106] This invention discloses a space system simulation and deduction management system applicable to the field of space system simulation analysis and evaluation, comprising remote sensing satellites, communication satellites, navigation satellites, ground stations, and ground entities. Through this space system simulation and deduction management system, an automatically evolving system deduction process can be obtained during space system simulation analysis and evaluation. The simulation process supports automatic optimization control of simulation tasks based on the simulation status of the space system, building upon the initial mission design results. This improves the operational processes of many concerned tasks and equipment, enhances the mission management system in general system applications, and better completes space system simulation deduction.

[0107] The sequence numbers of the various steps involved in the method of the present invention do not imply the order of execution of the method. The execution order of each step should be determined by its function and internal logic, and should not constitute any limitation on the implementation process of the embodiments of the present invention.

[0108] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A space system simulation and management system, characterized in that, It includes a simulation scheme design module, a simulation strategy management module, a simulation instruction management module, a simulation scheduling management module, a simulation task design module, a simulation object functional model, and a simulation display module; The simulation scheme design module is used to implement the initial simulation scheme design, specify the working procedures and control commands of the spacecraft in the simulation mission, and output simulation scheme data and spacecraft control commands; The simulation strategy management module is used to implement spacecraft operating procedure conventions, define various operating procedure constraints and state transition relationships, and output the spacecraft operating procedure handling results; The simulation instruction management module is used to implement the basic instruction set conventions for various working procedures of spacecraft, specify the basic instruction sequence and instruction parameter data for various working procedures, and output the basic instruction queue of working procedures. The simulation scheduling and management module is used to connect and schedule services with other modules, receive and distribute data, control the system's clock synchronization, schedule and distribute control commands for the spacecraft's working procedures, and enable the system to interact with other external engineering systems. The simulation task design module is used to design simulation scenarios, specify the entity composition, entity parameters, relationships between entities, and simulation environment in the simulation task, and output the simulation model composition, initial parameters of the simulation model, and initial state of the simulation. The simulation object functional model includes multiple simulation calculation modules, which are used to perform the necessary calculations on the spacecraft entity to meet business requirements and mission objectives. The simulation display module is used to implement the interface design of all input data and the interface display of all output data in the system; it also enables external data transmission and reception and clock synchronization through the simulation display service.

2. The aerospace system simulation and management system according to claim 1, characterized in that, The simulation calculation module includes at least a spacecraft dynamics calculation module, a spacecraft platform subsystem simulation calculation module, a spacecraft payload subsystem simulation calculation module, a ground station simulation calculation module, and a space environment simulation module.

3. The aerospace system simulation and management system according to claim 2, characterized in that, Implemented based on a B / S architecture, all modules and services are deployed on the server computer, and simulation control and monitoring are achieved through a client web browser; all computing functions of the modules are encapsulated through services, and the modules call each other through services.

4. A method for constructing a space system simulation and deduction management system as described in any one of claims 1 to 3, characterized in that, Includes the following steps: Step S1: Select a simulation platform, establish a simulation scheduling management module, establish a scheduling support framework service, a dedicated external interface service, and a job program management service to realize the system's computational management; Step S2: Establish a functional model of the simulation object based on the simulation platform, configure the data interface of the functional model of the simulation object based on the simulation platform, establish data communication between various modules, establish control command interface between various modules and simulation scheduling and management module, and output the calculation result data structure. Step S3: Establish a simulation instruction management module to implement the same working process definition as the main body of each working mode in the actual installation, and output the simulation instruction library; Step S4: Establish a simulation strategy management module to implement the state machine model of each simulation instruction and output the execution and switching conditions of each working mode and instruction; Step S5: Establish a simulation scheme design module, design the overall information and stage details of the simulation task, and output the overall scheme design results and stage details. Step S6: Establish a simulation mission design module to design the simulation mission scenario components, including the aerospace system object components, object parameters, object working process, battlefield environment, and time range. The output data information structure outputs the design results to the simulation engine's initialization method. The object's working process consists of a time-based sequence of working modes. Step S7: Display the centroid position, velocity, pointing result information, and working status information of the aerospace system through visualization methods such as pie charts, curves, and cloud maps; demonstrate the self-organization and adjustment of the mission process; and display the system simulation calculation results.

5. The method for constructing the aerospace system simulation and management system according to claim 4, characterized in that, Step S1 specifically includes: The simulation simulation management system implements functions and services based on the simulation engine, including at least the management of computation module parameters, computation module computation scheduling, data distribution scheduling and interaction management, time consistency management, and computer computing resource allocation; it implements the distribution control of data structures between modules of the simulation object functional model through the simulation engine's data subscription and data sending methods; and it implements the initialization data interaction between the simulation engine and the simulation object functional model through the simulation engine's initialization method. Establish an external interface service file / message interface channel to realize the reception, parsing and sending of messages and files that need to be transmitted between the simulation and simulation management system and other external software systems, and the scheduling support framework service. Establish an engineering data protocol interface channel for external interface services to receive, parse, and send data information that needs to be transmitted between the simulation and simulation management system and external on-orbit or equipment systems, and provide scheduling support framework services. Establish an external interface service engineering instruction protocol interface channel to realize the reception, parsing and sending of control instruction information that needs to be transmitted between the simulation and simulation management system and the external engineering test system; A simulation engine workflow management service is established to retrieve task processes from the simulation task design module, simulation scheme design module, simulation instruction management module, simulation strategy management module, and engineering instruction protocol interface channel; orchestrate and generate control instructions; enable self-organizing adjustment of task processes and send them to the calculation module; before the simulation starts, retrieve task processes from the simulation scheme design module and generate a set of task process instructions with strategies by referring to the simulation instruction library; during the simulation, update the instruction queue according to the strategy and engineering instruction protocol interface channel information and broadcast it to the simulation calculation module.

6. The method for constructing the aerospace system simulation and management system according to claim 4, characterized in that, Step S2 specifically includes: Establish basic computing functions and utilize the principles of orbital dynamics, attitude dynamics, and physical physics to realize spacecraft dynamics calculations, platform state calculations, payload state calculations, ground station state calculations, and space environment state calculations. Calculate and obtain the center of mass position, velocity, pointing results, and field distribution information of the spacecraft platform, payload, space environment, and ground station. Establish working mode and command management functions to manage each working mode, implement basic calculation functions to respond to the working mode, manage each control command, and implement basic calculation functions to respond to the command, including at least track control, equipment start-up and shutdown, attitude control, and state switching; output the results and status to a data structure. Establish a data interface function, and configure the connection of the model data interface based on the simulation platform to realize the data communication between the calculation modules. The model obtains input information, including data calculation results and instruction information, according to the ISIM data subscription method, and outputs result information according to the simulation platform data sending method; at the same time, the output result information structure is synchronously sent to the message queue. The simulation model is packaged into a usable program file according to the calling requirements of the simulation platform's computing modules, forming a computing service that can be used by the simulation engine.

7. The method for constructing the aerospace system simulation and management system according to claim 4, characterized in that, Step S5 specifically includes: The simulation task design module obtains overall simulation task information, including scheme name, scheme time, and scheme style. It also designs the stage information in the overall simulation task information, including the identifier, objective, name, time, available entity model, and transition conditions for each stage. The design results are then output to the simulation engine's initialization method. Detailed design phase information, including the identifier, objectives, name, time, available entity models, transition conditions, and task package information for each phase. Task package information includes task objectives, entity models used, entity operation control instructions, and entity model name, action to be performed, action object, instruction execution time, and instruction parameters. The design results are output to the simulation engine's job program management service.

8. The method for constructing the aerospace system simulation and simulation management system according to claim 4, characterized in that, Step S7 specifically includes: Receive information on the center of mass position, velocity, pointing results, and operational status of the aerospace system through a message queue; Data on motion trajectory, velocity direction, injury degree, and assessment results are established using visualization methods such as pie charts, curves, and cloud maps. The task process and instruction execution status are established using a curve method.

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