A Simulation Method, System and Device for a Spacecraft System Driven by a Hybrid of Time Events

Abstract

The present invention provides a simulation method, system and device for a spacecraft system driven by a time-event hybrid, belonging to the field of aerospace technology. First, a simulation framework is designed by combining time-driven and event-driven. Then, a control instruction set is established: the control instruction set is divided into a general instruction set and a dynamic instruction set according to the urgency of the event occurrence. Next, a component model of the spacecraft simulation system is established, and the solution order of each model at the same time point is determined. Subsequently, an instruction distribution model and an instruction execution model are established. Finally, based on the time-driven software operation framework, solutions are carried out at each time point to complete the simulation of the spacecraft system driven by the time-event hybrid.

Description

Technical Field

[0001] The present invention belongs to the field of aerospace technology, and specifically, relates to a simulation method, system and device for a spacecraft system driven by a time-event hybrid. Background Technique

[0002] At present, most spacecraft simulation systems usually adopt a pre-resolution method for task processing. In this method, data such as the orbit and attitude of a satellite are calculated based on the set parameters or tasks when the software starts. During the operation, the task simulation is driven based on the simulation time. The process is only the application and processing of the pre-resolved simulation data, for two-dimensional or three-dimensional visual display, and the generation of various data reports. This method can ensure the smooth visual simulation of the system in the early environment where the computer computing power was not strong and the algorithm efficiency was low. However, with the development of computer hardware systems and the development of high-efficiency computing methods such as parallel computing, the advantages of the pre-resolution method are no longer prominent. And because a large amount of simulation data is generated by software pre-resolution, the simulation process is only a time-based data display. Users cannot intervene in real time during the simulation process, making it difficult to realize the simulation of spacecraft systems highly dependent on time, such as the on-board system, and unable to meet the current user's requirements for spacecraft simulation systems.

[0003] Time-driven is based on time as a benchmark, and the task is solved at each time point. After obtaining the result, the calculation of the next time point is carried out. Time-driven has high stability, but at the same time has a high calculation cost and poor efficiency, making it difficult to meet the real-time simulation requirements of complex space missions; Event-driven is based on events as a benchmark, and the occurrence of events drives the change of the simulation state. The simulation efficiency is higher, but there are restrictions on the simulation content and the stability is poor. Summary of the Invention

[0004] In view of the above problems, in order to achieve real-time and efficient simulation of space missions while meeting the need for users to intervene in real time, the present invention combines a time-driven software operation framework and an event-driven software operation framework, and proposes a simulation method, system and device for a spacecraft system driven by a time-event hybrid.

[0005] The present invention is realized through the following technical solutions:

[0006] A simulation method for a spacecraft system driven by a time-event hybrid: The method specifically includes the following steps:

[0007] Step 1, combine time-driven and event-driven to design a simulation framework;

[0008] Step 2, establish a control instruction set: divide the control instruction set into a normal instruction set and a dynamic instruction set according to the urgency of the event occurrence;

[0009] Step 3: Establish component models of the spacecraft simulation system and determine the solution sequence of each model at the same time point;

[0010] Step 4: Establish an instruction distribution model and an instruction execution model;

[0011] Step 5: Based on the time-driven software operation framework, perform solutions at each time point to complete the spacecraft system simulation driven by a hybrid of time and events.

[0012] Furthermore, in Step 1,

[0013] Based on the time-driven software operation framework, establish a time system. The time system is responsible for establishing and maintaining a unified time reference and time conversion. Each component of the spacecraft system performs solutions under the unified time reference maintained by the time system;

[0014] Based on the event-driven concept, especially for events (especially unexpected events), within the scope of the simulation, the simulation time is not considered. The state of the spacecraft system is directly updated with the results of the event occurrence and the task solution is completed. At the same time, the software internally dynamically marks the completion status of the event and plans for possible future events until the simulation is completed.

[0015] Furthermore, in Step 2,

[0016] The ordinary instruction set contains events that can be predicted or occur according to a plan, and the dynamic instruction set contains unexpected events or emergency events;

[0017] The ordinary instruction set consists of instruction execution time, instruction ID, instruction execution component name, instruction name, task name, and instruction content. The instruction is executed after reaching the instruction execution time, and the time-driven priority is higher than the event-driven;

[0018] The instruction content in the dynamic instruction set does not contain the instruction execution time. When the instruction is input into the system, it is immediately executed, interrupting the time update. After the instruction execution is completed, the time and simulation are updated according to the time-driven. The priority of the event-driven is higher than the time-driven.

[0019] Furthermore, the instruction contains time information and event information, and the simulation is driven through the distribution and execution of the instruction. Specifically:

[0020] At the start of the simulation, the simulation system distributes the control instructions to the corresponding module components according to the instruction content; during the simulation operation, new control instructions are input into the system in real time and distributed in real time; the module components execute the control instructions to implement the hybrid drive method;

[0021] The control instructions can be added in real time by the system interface and external interfaces, or can be sent and called by other components within the software.

[0022] Further, in step 3,

[0023] The component model of the spacecraft simulation system includes other spacecraft systems, satellite systems, and satellite subsystems;

[0024] The satellite system includes a multi-mode thruster calculation model, an attitude and orbit calculation model, an orbital dynamics propulsion and orbit calculation model, an attitude control model, a latitude, longitude, and altitude environment calculation model, and an attitude and orbit control plan model;

[0025] The satellite subsystem includes an antenna pointing control model, a transmitter and receiver calculation model, a sensor calculation model, a carrier-to-interference ratio and multi-beam antenna calculation model, and a ground coverage calculation model;

[0026] The other spacecraft systems include an inert combination simulation task analysis model, a rocket navigation model, a routing model, a drawing control model, and a mission planning model;

[0027] The solution sequence is to first perform calculations on other systems, then perform calculations on the satellite system, and finally perform calculations on the satellite subsystem.

[0028] Further, in step 4,

[0029] The instruction distribution model sorts the existing control instructions. If it is a control instruction in the ordinary instruction set, the control instruction will be sorted and sent to the corresponding execution model at the beginning of the simulation; if it is a control instruction in the dynamic instruction set, sorting will start when the instruction is input, and at the same time, it will be sent to the execution model; the instruction distribution model distributes the instructions to the instruction execution lists of the corresponding components according to two different distribution logics:

[0030] If the instruction has an affiliated task name, the instruction will be distributed to the specific module corresponding to the task name;

[0031] If the instruction does not have an affiliated task name, the sub-component to which the instruction belongs will be judged according to the filled instruction execution component name;

[0032] The instruction execution model is responsible for the execution of the instructions. For the control instructions in the ordinary instruction set, corresponding actions will be taken according to the instruction content when the instruction reaches its execution, and the control component model realizes the instruction function; for the control instructions in the dynamic instruction set, the instructions will be executed immediately after being sent. After the instruction execution is completed, the instruction execution model marks the instruction execution status.

[0033] Further, in step 5,

[0034] Step 5.1, after the spacecraft system simulation starts, based on the current simulation time, each component of the spacecraft system performs calculations and state updates according to the solution sequence:

[0035] Solutions for other systems of the spacecraft: For mission solutions at the system level in the spacecraft system or solutions for equipment other than satellites;

[0036] Solutions for satellite systems: Calculate the orbit and attitude of the satellite, including: solutions for multi-mode thrusters of the satellite, calculation of satellite attitude and orbit, recursive calculation of orbital dynamics and orbital propulsion calculation, attitude control calculation, calculation of sub-satellite point, longitude, latitude, altitude, etc., and attitude and orbit control calculation;

[0037] Solutions for satellite subsystems: Calculate for on-board payloads and corresponding tasks, including: antenna pointing control solution, status update of payloads such as transmitters and receivers, sensor calculation, calculation of on-board communication link performance, and calculation of ground coverage;

[0038] Step 5.2, after completing the solutions for all tasks of the spacecraft system and the status update of components at the current moment, control the time system to perform time update according to the time step and perform the solutions for the next moment;

[0039] Step 5.3, after reaching the simulation moment, the time system stops time update, thereby stopping the solutions of the spacecraft system and completing the simulation.

[0040] A simulation system for a spacecraft system driven by a time-event hybrid:

[0041] The system includes a driving module, a control module, a solving module, and a simulation module;

[0042] The driving module combines time-driven and event-driven to design a simulation framework;

[0043] The control module establishes a control instruction set: divides the control instruction set into a normal instruction set and a dynamic instruction set according to the urgency of the event occurrence;

[0044] The solving module establishes component models of the spacecraft simulation system and determines the solving order of each model at the same time point;

[0045] The simulation module establishes an instruction distribution model and an instruction execution model; based on the time-driven software operation framework, performs solutions at each time point to complete the simulation of the spacecraft system driven by a time-event hybrid.

[0046] An electronic device includes a memory and a processor. The memory stores a computer program, and when the processor executes the computer program, the steps of the above method are implemented.

[0047] A computer-readable storage medium is used to store computer instructions, and when the computer instructions are executed by a processor, the steps of the above method are implemented.

[0048] Advantages of the present invention

[0049] To meet the requirements of real-time and efficient simulation for complex aerospace systems, a simulation method for spacecraft systems based on hybrid time-event-driven is proposed and established by combining the time-driven framework and the event-driven framework. Based on time-driven and considering the impact of events, a time-based control instruction is proposed, which consists of time information and event information. Through the distribution and execution of instruction information, hybrid time-event-driven can be achieved. Based on this method, the spacecraft simulation system can realize the real-time simulation of complex aerospace systems, and at the same time, when the user intervenes in the simulation system in a timely manner, it can meet the user's requirements while satisfying the real-time simulation requirements of the system. BRIEF DESCRIPTION OF THE DRAWINGS

[0050] Figure 1 It is the solution sequence of the spacecraft system simulation component model of the present invention.

[0051] Figure 2 It is the hybrid time-event-driven method of the spacecraft simulation system SpaceSim. DETAILED DESCRIPTION OF THE INVENTION

[0052] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0053] Combined with Figure 1 and Figure 2 .

[0054] A simulation method for spacecraft systems based on hybrid time-event-driven:

[0055] The method specifically includes the following steps:

[0056] Step 1, design a simulation framework by combining time-driven and event-driven; combine time-driven and event-driven to meet the current user's requirements for the spacecraft simulation system.

[0057] Based on the time-driven software operation framework, solve at each time point: establish a time system, which is responsible for establishing and maintaining a unified time reference and time conversion, and each component of the spacecraft system is solved under the unified time reference maintained by the time system;

[0058] Based on the event-driven concept, consider the impact of events on the change of the model state: Based on events, especially unexpected events, within the scope of simulation, the simulation time is not considered. Instead, directly update the state of the spacecraft system with the results of the event occurrence and complete the mission solution. At the same time, the software internally dynamically marks the completion status of the event and plans for possible future events until the simulation is completed.

[0059] Taking the time-driven framework as the benchmark, perform the solution and simulation of the spacecraft system at discrete time points. At the same time, for events, mainly sudden emergency events, consider the event-driven concept, directly perform the mission solution and update the model state with the results of the event occurrence. After the event occurs, mark the results of the event occurrence, and at the same time continue to use time-driven to update the spacecraft system.

[0060] Time-driven and event-driven are coupled with each other. Events can occur sequentially in the order of time. At the same time, events can also affect the update of time. The rollback and revisit of time can be controlled by the priority of the events.

[0061] Step 2, establish a control instruction set: Divide the control instruction set into a normal instruction set and a dynamic instruction set according to the urgency of the event occurrence;

[0062] The normal instruction set includes events that can be predicted or occur according to the plan, and the dynamic instruction set includes unexpected events or emergency events;

[0063] The normal instruction set consists of instruction execution time, instruction ID, instruction execution component name, instruction name, task name, and instruction content. The instruction is executed after reaching the instruction execution time, and the time-driven priority is higher than the event-driven;

[0064] The instruction content in the dynamic instruction set does not contain the instruction execution time. When the instruction is input into the system, it is immediately executed, interrupting the time update. After the instruction execution is completed, the time and simulation are updated according to the time-driven. The priority of the event-driven is higher than the time-driven.

[0065] The introduction of the dynamic instruction set makes the system have better flexibility and real-time performance to adapt to various unexpected events and the rapid response to user needs.

[0066] Implement a simulation method for a spacecraft system based on a hybrid drive of time and events in the form of control instructions. The instructions contain time information and event information, and the simulation is driven through the distribution and execution of the instructions. Specifically:

[0067] At the beginning of the simulation, the simulation system distributes the control instructions to the corresponding module components according to the instruction content; during the simulation operation, new control instructions can be input into the system in real time and distributed in real time; the module components execute the control instructions to implement the hybrid drive method;

[0068] Control instructions can be added in real time by the system interface and external interfaces, or other components within the software can send instructions to call each other. The information composition of the control instructions is shown in the following table:

[0069] Table 1 Instruction Composition

[0070]

[0071] Step 3: Establish the component models of the spacecraft simulation system and determine the solution order of each model at the same time point; ensure the orderly solution of the system.

[0072] The component models of the spacecraft simulation system include other spacecraft systems, satellite systems, and satellite subsystems;

[0073] The satellite system includes a multi-mode thruster calculation model, an attitude and orbit calculation model, an orbital dynamics propulsion and orbit calculation model, an attitude control model, a latitude, longitude, and altitude environment calculation model, and an attitude and orbit control plan model;

[0074] The satellite subsystem includes an antenna pointing control model, a transmitter and receiver calculation model, a sensor calculation model, a carrier-to-interference ratio and multi-beam antenna calculation model, and a ground coverage calculation model;

[0075] The other spacecraft systems include an inert combination simulation task analysis model, a rocket navigation model, a routing model, a drawing control model, and a mission planning model;

[0076] The solution order is as Figure 1 shown, which is to first perform other system calculations, then satellite system calculations, and finally satellite subsystem calculations.

[0077] Step 4: Establish an instruction distribution model and an instruction execution model;

[0078] The instruction distribution model sorts the existing control instructions. If it is a control instruction in the ordinary instruction set, the control instruction is sorted and sent to the corresponding execution model at the beginning of the simulation; if it is a control instruction in the dynamic instruction set, sorting starts when the instruction is input and is sent to the execution model at the same time; the instruction distribution model distributes the instructions to the instruction execution lists of the corresponding components according to two different distribution logics:

[0079] If the instruction has an affiliated task name, the instruction is distributed to the specific module corresponding to the task name;

[0080] If the instruction does not have an affiliated task name, the sub-component to which the instruction belongs is judged according to the filled instruction execution component name;

[0081] The instruction execution model is responsible for the execution of instructions. For the control instructions in the ordinary instruction set, corresponding actions will be taken according to the instruction content when the instruction reaches the execution stage, and the control component model realizes the instruction functions; for the control instructions in the dynamic instruction set, the instructions will be executed immediately after being issued. After the instruction execution is completed, the instruction execution model marks the instruction execution status.

[0082] The driving process of the system is as Figure 2 shown.

[0083] Step 5: Based on the time-driven software operation framework, solve at each time point to complete the simulation of the spacecraft system with hybrid time-event drive.

[0084] Step 5.1: After the spacecraft system simulation starts, based on the current simulation time, each component of the spacecraft system performs calculations and state updates according to the solution sequence:

[0085] Calculation of other spacecraft systems: For the system-level task calculation in the spacecraft system or the calculation of equipment other than satellites; such as multi-satellite combined simulation task analysis, rocket and navigation calculation, routing calculation, drawing control, mission planning, etc.

[0086] Calculation of satellite systems: Mainly calculate the orbit and attitude of the satellite, including: calculation of multi-mode thrusters of the satellite, satellite attitude orbit calculation, orbit dynamics recursion and orbit propulsion calculation, attitude control calculation, calculation of sub-satellite point, longitude, latitude and altitude, and attitude orbit control calculation, etc.;

[0087] Calculation of satellite subsystems: Mainly calculate the on-board payloads and corresponding tasks, including: calculation of antenna pointing control, state update of payloads such as transmitters and receivers, sensor calculation, calculation of on-board communication link performance, and calculation of ground coverage, etc.;

[0088] Step 5.2: After completing the calculation of all tasks of the spacecraft system at the current moment and the state update of the components, control the time system to perform time update according to the time step and perform the calculation of the next moment;

[0089] Step 5.3: After reaching the simulation time, the time system stops time update, thereby stopping the calculation of the spacecraft system and completing the simulation.

[0090] A spacecraft system simulation system with hybrid time-event drive:

[0091] The system includes a driving module, a control module, a solving module and a simulation module;

[0092] The driving module combines time drive and event drive to design a simulation framework;

[0093] The control module establishes a control instruction set: the control instruction set is divided into a normal instruction set and a dynamic instruction set according to the urgency of the event occurrence;

[0094] The solution module establishes a component model of the spacecraft simulation system and determines the solution order of each model at the same time point;

[0095] The simulation module establishes an instruction distribution model and an instruction execution model; based on the time-driven software operation framework, it performs solutions at each time point to complete the time-event hybrid-driven spacecraft system simulation.

[0096] An electronic device includes a memory and a processor. The memory stores a computer program, and when the processor executes the computer program, the steps of the above method are implemented.

[0097] A computer-readable storage medium is used to store computer instructions, and when the computer instructions are executed by a processor, the steps of the above method are implemented.

[0098] The memory in the embodiments of the present application may be a volatile memory or a non-volatile memory, or may include both volatile and non-volatile memories. Among them, the non-volatile memory may be a read only memory (ROM), a programmable ROM (PROM), an erasable PROM (EPROM), an electrically erasable PROM (EEPROM), or a flash memory. The volatile memory may be a random access memory (RAM), which is used as an external cache. By way of example but not limitation, many forms of RAM are available, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDR SDRAM), enhanced SDRAM (ESDRAM), synchlink DRAM (SLDRAM), and direct rambus RAM (DR RAM). It should be noted that the memory for the method described in the present invention is intended to include, but not be limited to, these and any other suitable types of memory.

[0099] In the above embodiments, it can be implemented in whole or in part by software, hardware, firmware, or any combination thereof. When implemented using software, it can be implemented in whole or in part in the form of a computer program product. The computer program product includes one or more computer instructions. When the computer instructions are loaded and executed on a computer, the processes or functions described in the embodiments of the present application are generated in whole or in part. The computer can be a general-purpose computer, a special-purpose computer, a computer network, or other programmable devices. The computer instructions can be stored in a computer-readable storage medium or transmitted from one computer-readable storage medium to another. For example, the computer instructions can be transmitted from one website, computer, server, or data center to another website, computer, server, or data center via wired means such as coaxial cable, optical fiber, digital subscriber line (DSL), or wireless means such as infrared, wireless, microwave, etc. The computer-readable storage medium can be any available medium that can be accessed by a computer or a data storage device such as a server or data center that includes one or more integrated available media. The available medium can be a magnetic medium such as a floppy disk, hard disk, magnetic tape, an optical medium such as a high-density digital video disc (DVD), or a semiconductor medium such as a solid state disc (SSD), etc.

[0100] In the implementation process, the steps of the above method can be completed by the integrated logic circuit of the hardware in the processor or the instructions in the form of software. The steps of the method disclosed in combination with the embodiments of the present application can be directly embodied as being executed by the hardware processor, or executed by a combination of the hardware and software modules in the processor. The software module can be located in a mature storage medium in the art such as random access memory, flash memory, read-only memory, programmable read-only memory, or electrically erasable programmable memory, register, etc. This storage medium is located in the memory, and the processor reads the information in the memory and combines its hardware to complete the steps of the above method. To avoid repetition, it will not be described in detail here.

[0101] It should be noted that the processor in the embodiments of the present application may be an integrated circuit chip with signal processing capabilities. In the implementation process, the steps of the above method embodiments can be completed by the integrated logic circuit in the hardware of the processor or instructions in the form of software. The above-mentioned processor may be a general-purpose processor, a digital signal processor (DSP), an application-specific integrated circuit (ASIC), a field-programmable gate array (FPGA), or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components. It can implement or execute the various methods, steps, and logic block diagrams disclosed in the embodiments of the present application. The general-purpose processor may be a microprocessor or the processor may also be any conventional processor, etc. The steps of the method disclosed in combination with the embodiments of the present application can be directly embodied as being executed and completed by a hardware decoding processor, or executed and completed by a combination of hardware and software modules in the decoding processor. The software module may be located in a mature storage medium in the art such as a random access memory, a flash memory, a read-only memory, a programmable read-only memory, or an electrically erasable programmable memory, a register, etc. This storage medium is located in the memory, and the processor reads the information in the memory and combines its hardware to complete the steps of the above method.

[0102] The above has introduced in detail a time-event hybrid-driven spacecraft system simulation method, system, and device proposed by the present invention, and expounded on the principle and implementation manner of the present invention. The description of the above embodiments is only used to help understand the method and its core idea of the present invention; at the same time, for those of ordinary skill in the art, according to the idea of the present invention, there will be changes in the specific implementation manner and application scope. In summary, the content of this specification should not be construed as a limitation to the present invention.

Claims

1. A simulation method for a spacecraft system driven by a hybrid of time events, characterized in that: The method specifically includes the following steps: Step 1, combine time-driven and event-driven to design a simulation framework; Based on the time-driven software operation framework, establish a time system, which is responsible for establishing and maintaining a unified time reference and time conversion. Each component of the spacecraft system is solved under the unified time reference maintained by the time system; Based on the event-driven idea, the events include unexpected events. Without considering the simulation time within the scope of the simulation, directly update the state of the spacecraft system with the results of the event occurrence and complete the task calculation. At the same time, the software internally dynamically marks the completion status of the event and plans possible future events until the simulation is completed; Step 2, establish a control instruction set: divide the control instruction set into a normal instruction set and a dynamic instruction set according to the urgency of the event occurrence; The normal instruction set contains events that can be predicted or occur according to a plan, and the dynamic instruction set contains unexpected events or emergency events; The normal instruction set consists of instruction execution time, instruction ID, instruction execution component name, instruction name, task name, and instruction content. The instruction is executed after reaching the instruction execution time, and the time-driven priority is higher than the event-driven; The instruction content in the dynamic instruction set does not contain the instruction execution time. When the instruction is input into the system, the instruction is immediately executed, interrupting the time update. After the instruction execution is completed, the time and simulation are updated according to the time-driven. The priority of the event-driven is higher than the time-driven; Step 3, establish a component model of the spacecraft simulation system and determine the solution order of each model at the same time point; Step 4, establish an instruction distribution model and an instruction execution model; Step 5, based on the time-driven software operation framework, perform calculations at each time point to complete the simulation of the spacecraft system driven by a hybrid of time events.

2. The method according to claim 1, characterized in that: The instruction contains time information and event information, and realizes the driving of the simulation through the distribution and execution of the instruction. Specifically: At the beginning of the simulation, the simulation system distributes the control instructions to the corresponding module components according to the instruction content; during the simulation operation, new control instructions are input into the system in real time and distributed in real time; the module components execute the control instructions to realize the hybrid driving method; The control instructions can be added in real time by the system interface and external interfaces, or can be sent and called by other components inside the software.

3. The method according to claim 2, wherein: In step 3, The component model of the spacecraft simulation system includes other spacecraft systems, satellite systems, and satellite subsystems; The satellite system includes a multi-mode thruster calculation model, an attitude orbit calculation model, an orbit dynamics propulsion and orbit calculation model, an attitude control model, a latitude, longitude, altitude and other environment calculation models, and an attitude and orbit control plan model; The satellite subsystem includes an antenna pointing control model, a transmitter-receiver calculation model, a sensor calculation model, a carrier-to-interference ratio and multi-beam antenna calculation model, and a ground coverage calculation model; The other spacecraft systems include an inert combination simulation task analysis model, a rocket navigation model, a routing model, a drawing control model, and a task planning model; The solution sequence is to first perform calculations for other systems, then for the satellite system, and finally for the satellite subsystems.

4. The method according to claim 3, wherein: In step 4, The instruction distribution model sorts the existing control instructions. If it is a control instruction in the ordinary instruction set, the control instruction is sorted and sent to the corresponding execution model at the beginning of the simulation; if it is a control instruction in the dynamic instruction set, sorting starts when the instruction is input and is sent to the execution model simultaneously; the instruction distribution model distributes the instructions to the instruction execution lists of the corresponding components according to two different distribution logics: If the instruction has an associated task name, the instruction is distributed to the specific module corresponding to the task name; If the instruction does not have an associated task name, the sub-component to which the instruction belongs is determined based on the filled-in instruction execution component name; The instruction execution model is responsible for executing the instructions. For control instructions in the ordinary instruction set, corresponding actions will be taken according to the instruction content when the instruction reaches its execution, and the control component model realizes the instruction function; for control instructions in the dynamic instruction set, the instruction is executed immediately after it is sent, and the instruction execution model marks the instruction execution status after the instruction execution is completed.

5. The method according to claim 4, wherein: In step 5, Step 5.1, after the spacecraft system simulation starts, based on the current simulation time, each component of the spacecraft system performs calculations and state updates according to the solution sequence: Calculation for other spacecraft systems: For mission calculations at the system level in the spacecraft system or calculations for equipment other than satellites; Calculation for the satellite system: Calculates the orbit and attitude of the satellite, including: calculation of the satellite's multi-mode thrusters, satellite attitude orbit calculation, orbit dynamics recursion and orbit propulsion calculation, attitude control calculation, calculation of sub-satellite point and longitude / latitude / altitude, etc., and attitude orbit control calculation; Calculation for satellite subsystems: Performs calculations for on-board payloads and corresponding tasks, including: antenna pointing control calculation, state update of transmitter and receiver payloads, sensor calculation, calculation of on-board communication link performance, and calculation of ground coverage; Step 5.2, after completing the calculations for all tasks of the spacecraft system and the state updates of the components at the current moment, the control time system updates the time according to the time step and proceeds to the calculations for the next moment; Step 5.3, after reaching the simulation time, the time system stops the time update, thereby stopping the calculations of the spacecraft system and completing the simulation.

6. A spacecraft system simulation system driven by a hybrid of time and events, characterized in that: The system includes a driving module, a control module, a solution module, and a simulation module; The driving module combines time-driven and event-driven to design the simulation framework; Based on the time-driven software operation framework, a time system is established. The time system is responsible for establishing and maintaining a unified time reference and time conversion. Each component of the spacecraft system performs calculations under the unified time reference maintained by the time system; Based on the event-driven concept, the events include unexpected events. During the simulation range, the simulation time is not considered, and the state of the spacecraft system is directly updated with the results of the event occurrence and the task calculations are completed. At the same time, the software internally dynamically marks the completion status of the events and plans for possible future events until the simulation is completed; The control module establishes a control instruction set: The control instruction set is divided into a normal instruction set and a dynamic instruction set according to the urgency of the event occurrence; The normal instruction set includes events that can be predicted or occur according to a plan, and the dynamic instruction set includes unexpected events or emergency events; The normal instruction set consists of instruction execution time, instruction ID, instruction execution component name, instruction name, task name, and instruction content. The instruction is executed after reaching the instruction execution time, and the time-driven priority is higher than the event-driven; The instruction content in the dynamic instruction set does not contain the instruction execution time. The instruction is immediately executed when input into the system, the interruption time is updated, and the time and simulation are updated according to the time-driven after the instruction execution is completed. The priority of the event-driven is higher than the time-driven; The solution module establishes a component model of the spacecraft simulation system and determines the solution order of each model at the same time point; The simulation module establishes an instruction distribution model and an instruction execution model; Based on the time-driven software operation framework, the solution is carried out at each time point to complete the spacecraft system simulation with mixed time-event drive.

7. An electronic device, comprising a memory and a processor, the memory storing a computer program, characterized in that, When the processor executes the computer program, it implements the steps of the method described in any one of claims 1 to 5.

8. A computer-readable storage medium for storing computer instructions, characterized in that, When the computer instruction is executed by the processor, it implements the steps of the method described in any one of claims 1 to 5.

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