Model-based spaceflight launching system overall design method

Abstract

The invention discloses a model-based spaceflight launching system overall design method, which comprises the following steps: based on launching task types, establishing a launching system model, obtaining the number of launching tasks required to be completed by launching a rocket in unit time, generating constraint conditions among the tasks, and constructing a launching prediction model, in the launch prediction model, a task scheduling algorithm is constructed, a scheduling scheme is dynamically generated by taking minimization of task completion time, minimization of weighted lag time, minimization of fuel consumption, maximization of launch success rate and minimization of environmental influence as a comprehensive target, and in the process of dynamically generating the scheduling scheme, a dynamic detection model is constructed; detecting the scheduling scheme in real time; through modeling and prediction methods, the number of tests and the degree of dependence on empirical formulas are reduced, so that the design period is shortened, factors such as the flight process of the rocket, the engine combustion condition and meteorological condition changes are comprehensively considered, and the design result better conforms to the actual condition.

Description

Technical Field

[0001] The invention relates to a rocket launch mission planning technology, and in particular to a model-based overall design method for a space launch system. Background Art

[0002] Aerospace technology is a high-tech space technology currently used to explore and utilize outer space.

[0003] The design and optimization of space launch systems is a complex process involving the intersection of multiple disciplines and fields. Traditional space launch system design methods often rely on empirical formulas and test data, resulting in long design cycles and low efficiency. At the same time, in the process of seeking balance and optimization between multiple goals, there is a lack of scientific methods and tools, making it difficult to fully consider various influencing factors and dynamic change processes.

[0004] Therefore, there is an urgent need for a model-based overall design method for a space launch system to solve the technical problems existing in the above-mentioned prior art. Summary of the invention

[0005] The present invention overcomes the deficiencies of the prior art and provides a model-based overall design method for a space launch system.

[0006] To achieve the above object, the technical solution adopted by the present invention is: a model-based overall design method for a space launch system, the method comprising:

[0007] Based on the launch mission type, a launch system model is established, with input data including the rocket's mass, size, aerodynamics, thermodynamics, and operating environment parameters;

[0008] Obtain the number of launch tasks required to launch a rocket in a unit of time, generate constraints between tasks, and build a launch prediction model to predict the iterations between tasks;

[0009] In the launch prediction model, a task scheduling algorithm is constructed, and a scheduling plan is dynamically generated with the comprehensive goals of minimizing task completion time, minimizing weighted lag time, minimizing fuel consumption, maximizing launch success rate, and minimizing environmental impact;

[0010] In the process of dynamically generating scheduling plans, a dynamic detection model is built to perform real-time detection on the scheduling plans, and a dynamic synchronization cycle is set to coordinate the iterations between tasks.

[0011] In a preferred embodiment of the present invention, the launch system model includes using a multi-body dynamics model to describe the flight process of the rocket, using a thermodynamic model to predict the combustion of the rocket engine, and using an environmental model to simulate changes in meteorological conditions during the launch process.

[0012] In a preferred embodiment of the present invention, the constraints include: tasks are carried out in sequence according to predetermined tasks; preparation time is required for each task link before starting a new task; each task link can only be used by one task at a time; the time for each task is determined, and there is no transmission time between adjacent tasks; tasks are not allowed to be interrupted; a task can only be started after all tasks before it are completed; task iteration; a task can only be performed on a certain type or a certain task link.

[0013] In a preferred embodiment of the present invention, the prediction process of the emission prediction model includes:

[0014] S1, initialize the launch task sequence and set the task execution order according to the task constraints;

[0015] S2, simulate the task execution process and calculate the state changes of each task at each time step, including the start, progress and end of the task;

[0016] S3, detect the task iteration situation, when the task iteration is found, update the task status according to the iteration probability and iteration rule;

[0017] S4, evaluate the impact of iteration on the task sequence and calculate the new task execution time and resource requirements;

[0018] S5, repeating steps S2 to S4 until all tasks are completed or the preset upper limit of the number of iterations is reached;

[0019] S6. Output prediction results, including task execution time, resource usage, and potential iteration risks.

[0020] In a preferred embodiment of the present invention, the task scheduling algorithm obtains a scheduling scheme between tasks based on the parallelism and iteration conditions between tasks. The calculation expression of the task scheduling algorithm is:

[0021]

[0022] Where, T i represents the completion time of the i-th task; j The weight system representing the weighted delay of the jth task; D j represents the weighted delay time of the jth task; L represents the fuel consumption; S represents the success rate; P represents the penalty coefficient of launch failure; E represents the environmental impact index; and n represents the number of tasks.

[0023] In a preferred embodiment of the present invention, the dynamic detection model collects various operating data of the launch system in real time through a monitoring system, including the status of the rocket, the progress of task execution, resource consumption and environmental parameters, and detects the current scheduling plan based on the real-time collected data; including: checking whether the tasks are executed in a predetermined order and time and evaluating the completion of the tasks; during the detection process, if it is found that the execution of a task between tasks affects the progress or resource allocation of other tasks, the task status is updated according to the iteration probability and iteration rules, and the execution order or resource allocation of the tasks is adjusted.

[0024] In a preferred embodiment of the present invention, the dynamic synchronization period is dynamically adjusted based on the complexity of the transmission task, the system response speed and the resource scheduling requirements.

[0025] In a preferred embodiment of the present invention, the dynamic detection model also includes a fault prediction and diagnosis module, which predicts potential fault points by analyzing the operating data collected in real time, and issues a warning signal before the fault occurs, while providing a fault diagnosis report and repair suggestions.

[0026] In a preferred embodiment of the present invention, a computer device includes a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the steps of the method when executing the computer program.

[0027] In a preferred embodiment of the present invention, a computer-readable storage medium stores a computer program, and the computer program implements the steps of the method when executed by a processor.

[0028] The present invention solves the defects existing in the background technology and has the following beneficial effects:

[0029] (1) Through modeling and prediction methods, the number of experiments and the degree of reliance on empirical formulas are reduced, thereby shortening the design cycle. Comprehensive considerations are given to factors such as the rocket's flight process, engine combustion conditions, and changes in meteorological conditions, making the design results more in line with actual conditions. Through task scheduling algorithms and dynamic detection models, a balance and optimization between multiple objectives are achieved, thereby improving the overall performance of the design.

[0030] (2) By optimizing task scheduling and real-time monitoring, the launch process is made more efficient, stable, and safer, the number of tests and the degree of reliance on empirical formulas are reduced, the design cost is reduced, the design cycle is shortened, and the design efficiency is improved, providing strong support for the rapid response and flexible adjustment of the space launch system. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art are briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative work.

[0032] Figure 1 is a flow chart of the overall design of a space launch system based on a model according to a preferred embodiment of the present invention;

[0033] Figure 2 It is a flow chart of the prediction process of the emission prediction model of the preferred embodiment of the present invention. DETAILED DESCRIPTION

[0034] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0035] In the following description, many specific details are set forth to facilitate a full understanding of the present invention, but the present invention may also be implemented in other ways different from those described herein. Therefore, the protection scope of the present invention is not limited to the specific embodiments disclosed below.

[0036] like Figure 1 As shown, a model-based overall design method for a space launch system comprises:

[0037] Based on the launch mission type, a launch system model is established, and data including the rocket's mass, size, aerodynamics, thermodynamics and operating environment parameters are input; among them, launch mission types include but are not limited to: special launch, piggyback launch, wartime launch, commercial launch, and scientific research launch.

[0038] Furthermore, the launch system model includes using a multi-body dynamics model to describe the flight process of the rocket, using a thermodynamic model to predict the combustion of the rocket engine, and using an environmental model to simulate changes in meteorological conditions during the launch process.

[0039] Furthermore, when building a launch system model, it is necessary to accurately input the rocket's mass, size, aerodynamic characteristics, thermodynamic parameters, and operating environment (such as wind speed, temperature, humidity, etc.) data. These data can be obtained through sensor measurement, historical data analysis, and simulation. At the same time, the input data needs to be preprocessed, such as denoising, calibration, and format unification, to ensure the accuracy of the model.

[0040] The launch system model can be built based on physical principles, empirical formulas or machine learning algorithms. For example, a multi-body dynamics model can be used to describe the flight process of a rocket, a thermodynamic model can be used to predict the combustion of a rocket engine, and an environmental model can be used to simulate changes in meteorological conditions during the launch process.

[0041] Obtain the number of launch tasks required to launch a rocket in a unit of time, generate constraints between tasks, and build a launch prediction model to predict the iterations between tasks;

[0042] In this process, it is necessary to clarify the constraints between the various launch missions, such as time windows, resource limitations, mission priorities, etc. These constraints can be generated through mission planning software, expert systems or manual intervention.

[0043] The launch prediction model can use time series analysis, machine learning algorithms, or physical model prediction methods to predict the iterations between tasks. The selection of prediction algorithms should be based on the specific mission characteristics and requirements.

[0044] Furthermore, the constraints include: tasks are carried out in sequence according to predetermined tasks; the preparation time required for each task link before starting a new task; each task link can only be used by one task at a time; the time for each task is determined, and there is no transmission time between adjacent tasks; tasks are not allowed to be interrupted; a task can only be started after all tasks before it are completed; task iteration; a task can only be performed on a certain type or a certain task link.

[0045] For multi-task serial scheduling, since the resources of the transmission system are only occupied by one task at the same time, there is no problem of multiple tasks competing for the same resources at the same time, so the transmission system will not be locked.

[0046] Furthermore, if Figure 2 As shown, the prediction process of the emission prediction model includes:

[0047] S1, initialize the launch task sequence and set the task execution order according to the task constraints;

[0048] S2, simulate the task execution process and calculate the state changes of each task at each time step, including the start, progress and end of the task;

[0049] S3, detect the task iteration situation, when the task iteration is found, update the task status according to the iteration probability and iteration rule;

[0050] S4, evaluate the impact of iteration on the task sequence and calculate the new task execution time and resource requirements;

[0051] S5, repeating steps S2 to S4 until all tasks are completed or the preset upper limit of the number of iterations is reached;

[0052] S6. Output prediction results, including task execution time, resource usage, and potential iteration risks.

[0053] In the launch prediction model, a task scheduling algorithm is constructed, and a scheduling plan is dynamically generated with the comprehensive goals of minimizing task completion time, minimizing weighted lag time, minimizing fuel consumption, maximizing launch success rate, and minimizing environmental impact.

[0054] Furthermore, the task scheduling algorithm obtains a scheduling scheme between tasks based on the parallelism and iteration conditions between tasks. The calculation expression of the task scheduling algorithm is:

[0055]

[0056] Where, T i represents the completion time of the i-th task; j The weight system representing the weighted delay of the jth task; D j represents the weighted delay time of the jth task; L represents the fuel consumption; S represents the success rate; P represents the penalty coefficient of launch failure; E represents the environmental impact index; and n represents the number of tasks.

[0057] Furthermore, the task scheduling algorithm aims to minimize the combination of task completion time and weighted delay time. At the same time, it is also possible to consider adding optimization goals such as minimizing fuel consumption, maximizing launch success rate, and minimizing environmental impact to form a multi-objective optimization problem.

[0058] Scheduling algorithms can use greedy algorithms, dynamic programming, genetic algorithms, particle swarm optimization and other strategies to generate scheduling solutions. When choosing a scheduling strategy, factors such as algorithm complexity, solution quality and computing time need to be considered.

[0059] During the launch process, due to the existence of various uncertain factors, such as weather changes, equipment failures, etc., the scheduling algorithm needs to be able to adjust the scheduling plan in real time to ensure the smooth progress of the launch mission.

[0060] In the process of dynamically generating scheduling plans, a dynamic detection model is built to perform real-time detection on the scheduling plans, and a dynamic synchronization cycle is set to coordinate the iterations between tasks.

[0061] Furthermore, the dynamic detection model collects various operating data of the launch system in real time through the monitoring system, including the status of the rocket, the progress of task execution, resource consumption and environmental parameters, and detects the current scheduling plan based on the real-time collected data; including: checking whether the tasks are executed in the predetermined order and time and evaluating the completion of the tasks; during the detection process, if it is found that the execution of a task between tasks affects the progress or resource allocation of other tasks, the task status is updated according to the iteration probability and iteration rules, and the execution order or resource allocation of the tasks is adjusted.

[0062] Furthermore, the dynamic synchronization period is dynamically adjusted based on the complexity of the transmission task, the system response speed and the resource scheduling requirements.

[0063] The dynamic detection model needs to set a series of detection indicators, such as task progress, resource consumption, system status, etc., to monitor the execution of the scheduling plan in real time.

[0064] In order to ensure the coordination and consistency of the iterations between tasks, it is necessary to set a synchronization cycle so that each task is carried out according to the predetermined time node. The synchronization mechanism can be implemented by clock synchronization, event synchronization, etc.

[0065] When an abnormal situation or fault is detected, the dynamic detection model needs to be able to trigger the corresponding fault handling mechanism, such as task rescheduling, system recovery, etc., to ensure the smooth progress of the launch mission.

[0066] It should be further explained that the synchronization period is a key parameter to ensure the coordinated and synchronous operation of various tasks in the space launch system. In traditional methods, the synchronization period is often fixed, which may lead to incoordination between tasks or waste of resources when the complexity of the task changes or the system response speed fluctuates. The model-based overall design method of the space launch system can more effectively cope with these changes by dynamically adjusting the synchronization period.

[0067] The core of the dynamic adjustment mechanism is to monitor and evaluate the complexity of the launch mission, the system response speed and resource scheduling requirements in real time. When the complexity of the mission increases, the system may need longer time to process and coordinate the relationship between the tasks. At this time, the synchronization cycle should be extended accordingly to ensure that each task has enough time to complete its execution and iteration. On the contrary, when the complexity of the mission decreases, the synchronization cycle can be shortened accordingly to improve the overall operation efficiency of the system.

[0068] The system response speed is also an important factor affecting the synchronization cycle. If the system response speed is fast, the coordination and synchronization between tasks can be completed more quickly and efficiently, and the synchronization cycle can be shortened accordingly. On the contrary, if the system response speed is slow, a longer synchronization cycle is required to ensure the coordination and synchronization between tasks.

[0069] In addition, resource scheduling requirements are also factors that need to be considered when dynamically adjusting the synchronization cycle. When resources are tight, the system may need to optimize resource allocation by extending the synchronization cycle to avoid resource conflicts and waste. When resources are abundant, the synchronization cycle can be appropriately shortened to improve the overall operating efficiency of the system.

[0070] By dynamically adjusting the synchronization cycle, the coordination and synchronization between tasks can be ensured, conflicts and waiting time between tasks can be reduced, and the overall performance of the launch system can be improved. The dynamic adjustment of the synchronization cycle can be flexibly adjusted according to resource scheduling requirements, avoiding resource conflicts and waste, and improving resource utilization efficiency.

[0071] When the system responds quickly, the overall operating efficiency of the system can be further improved by shortening the synchronization cycle. Dynamic adjustment of the synchronization cycle can make the launch system better adapt to launch tasks of different complexity and response speed, and improve the adaptability and flexibility of the system.

[0072] The dynamic detection model also includes a fault prediction and diagnosis module, which predicts potential fault points by analyzing the real-time collected operating data, and issues a warning signal before the fault occurs, while providing a fault diagnosis report and repair suggestions.

[0073] A computer device includes a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the steps of the method when executing the computer program. Specifically, the computer device may be a server, and the computer device includes a processor, a memory, a network interface, and a database connected via a system bus. The processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system, a computer program, and a database. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The database of the computer device is used to store data during rocket launch. The network interface of the computer device is used to communicate with an external terminal via a network connection. When the computer program is executed by the processor, a model-based overall design method for a space launch system is implemented.

[0074] A computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, the steps of the method are implemented. Specifically, the computer device may be a terminal, and the computer device includes a processor, a memory, a network interface, a display screen, and an input device connected through a system bus. The processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system and a computer program. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The network interface of the computer device is used to communicate with an external terminal through a network connection. When the computer program is executed by the processor, a model-based overall design method for a space launch system is implemented. The display screen of the computer device may be a liquid crystal display screen or an electronic ink display screen, and the input device of the computer device may be a touch layer covered on the display screen, or a key, trackball or touchpad provided on the housing of the computer device, or an external keyboard, touchpad or mouse.

[0075] When the present invention is used, a launch system model is constructed based on the launch mission type (such as manned space flight, satellite launch, etc.), and the rocket's mass, size, aerodynamic characteristics (such as drag coefficient, lift coefficient, etc.), thermodynamic parameters (such as combustion chamber temperature, pressure, etc.) and operating environment parameters (such as wind speed, wind direction, temperature, humidity, etc.) are input.

[0076] A multi-body dynamics model is used to describe the flight process of the rocket, including the rocket's attitude control, orbit planning, etc. A thermodynamic model is used to predict the combustion of the rocket engine to ensure stable engine performance. An environmental model is used to simulate changes in meteorological conditions during the launch process to provide a basis for launch decisions.

[0077] According to the number of launch tasks to be completed in a unit time, the constraints between tasks are generated. The constraints include the order of task execution, the dependencies between tasks, resource restrictions, etc., and a launch prediction model is constructed to predict the iterations between tasks. The prediction process includes initializing the task sequence, simulating the task execution process, detecting the task iterations, and evaluating the impact of iterations. The prediction results are output, including task execution time, resource usage, potential iteration risks, etc.

[0078] In the launch prediction model, a task scheduling algorithm is constructed. The algorithm takes minimizing the task completion time, weighted lag time, fuel consumption, maximizing the launch success rate and minimizing the environmental impact as the comprehensive goal. It takes into account the parallelism and iteration between tasks and dynamically generates a scheduling plan. The scheduling plan can be adjusted and optimized according to the actual situation.

[0079] In the process of dynamically generating scheduling plans, a dynamic detection model is built to collect real-time operating data of the launch system through the monitoring system, including the status of the rocket, mission execution progress, resource consumption, and environmental parameters. Based on the real-time collected data, the current scheduling plan is detected and evaluated.

[0080] When conflicts or resource allocation problems are found between tasks, the task status is updated and adjusted according to the iteration probability and iteration rules, and the dynamic synchronization cycle is dynamically adjusted based on the complexity of the launch task, the system response speed and the resource scheduling requirements.

[0081] Through modeling and prediction methods, the number of experiments and the reliance on manual calculations are reduced. At the same time, through optimization of task scheduling and real-time monitoring, the design cycle is shortened and the design efficiency is improved.

[0082] The impact of factors such as the rocket's flight process, engine combustion conditions, and changes in meteorological conditions on the launch mission are fully considered. Through precise mathematical models and simulation methods, the rocket's flight trajectory, engine performance, and risks during the launch process can be accurately predicted. This provides a scientific basis and strong support for launch decisions.

[0083] Through methods and tools such as task scheduling algorithms and dynamic detection models, balance and optimization between multiple goals are achieved. At the same time, through methods such as real-time monitoring and adjustment of scheduling schemes, design results can be flexibly adjusted and optimized according to actual conditions. This improves the overall performance and reliability of the design and reduces the difficulty of optimization.

[0084] Those skilled in the art can understand that all or part of the processes in the above-mentioned embodiment methods can be completed by instructing the relevant hardware through a computer program, and the computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it can include the processes of the embodiments of the above-mentioned methods. Among them, any reference to memory, storage, database or other media used in the embodiments provided in this application can include non-volatile and / or volatile memory. Non-volatile memory can include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM) or flash memory. Volatile memory can include random access memory (RAM) or external cache memory. As an illustration and not limitation, RAM is available in many forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous link (Synchlink) DRAM (SLDRAM), memory bus (Rambus) direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM).

[0085] The technical features of the above embodiments may be combined arbitrarily. To make the description concise, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0086] The above is based on the ideal embodiment of the present invention. Through the above description, relevant personnel can make various changes and modifications without departing from the technical concept of the present invention. The technical scope of the present invention is not limited to the content in the specification, and the technical scope must be determined according to the scope of the claims.

Claims

1. A model-based overall design method for a space launch system, characterized in that: The method comprises: Based on the launch mission type, a launch system model is established, with input data including the rocket's mass, size, aerodynamics, thermodynamics, and operating environment parameters; Obtain the number of launch tasks required to launch a rocket in a unit of time, generate constraints between tasks, and build a launch prediction model to predict the iterations between tasks; In the launch prediction model, a task scheduling algorithm is constructed, and a scheduling plan is dynamically generated with the comprehensive goals of minimizing task completion time, minimizing weighted lag time, minimizing fuel consumption, maximizing launch success rate, and minimizing environmental impact; In the process of dynamically generating scheduling plans, a dynamic detection model is built to perform real-time detection on the scheduling plans, and a dynamic synchronization cycle is set to coordinate the iterations between tasks.

2. The model-based space launch system overall design method according to claim 1, characterized in that: The launch system model includes a multi-body dynamics model to describe the flight process of the rocket, a thermodynamic model to predict the combustion of the rocket engine, and an environmental model to simulate the changes in meteorological conditions during the launch process.

3. The model-based space launch system overall design method according to claim 1, characterized in that: The constraints include: tasks are carried out in sequence according to predetermined tasks; preparation time is required for each task link before starting a new task; each task link can only be used by one task at a time; the time for each task is determined, and there is no transmission time between adjacent tasks; tasks are not allowed to be interrupted; a task can only be started after all tasks before it are completed; task iteration; a task can only be performed on a certain type or task link.

4. A model-based space launch system overall design method according to claim 1 or 3, characterized in that: The prediction process of the emission prediction model includes: S1, initialize the launch task sequence and set the task execution order according to the task constraints; S2, simulate the task execution process and calculate the state changes of each task at each time step, including the start, progress and end of the task; S3, detect the task iteration situation, when the task iteration is found, update the task status according to the iteration probability and iteration rule; S4, evaluate the impact of iteration on the task sequence and calculate the new task execution time and resource requirements; S5, repeating steps S2 to S4 until all tasks are completed or the preset upper limit of the number of iterations is reached; S6. Output prediction results, including task execution time, resource usage, and potential iteration risks.

5. The model-based space launch system overall design method according to claim 1, characterized in that: The task scheduling algorithm is based on the parallelism and iteration of each task to obtain the scheduling scheme between each task. The calculation expression of the task scheduling algorithm is: Where, T i represents the completion time of the i-th task; λ j The weight system representing the weighted delay of the jth task; D j represents the weighted delay time of the jth task; L represents the fuel consumption; S represents the success rate; P represents the penalty coefficient of launch failure; E represents the environmental impact index; and n represents the number of tasks.

6. The model-based space launch system overall design method according to claim 1, characterized in that: The dynamic detection model collects various operating data of the launch system in real time through the monitoring system, including the status of the rocket, the progress of mission execution, resource consumption and environmental parameters, and detects the current scheduling plan based on the real-time collected data; These include: checking that tasks are performed in the intended sequence and timing and evaluating task completion; During the detection process, if it is found that the execution of a task affects the progress or resource allocation of other tasks, the task status is updated according to the iteration probability and iteration rules, and the execution order or resource allocation of the tasks is adjusted.

7. The model-based space launch system overall design method according to claim 1, characterized in that: The dynamic synchronization period is dynamically adjusted based on the complexity of the transmission task, the system response speed and the resource scheduling requirements.

8. The model-based space launch system overall design method according to claim 1, characterized in that: The dynamic detection model also includes a fault prediction and diagnosis module, which predicts potential fault points by analyzing the real-time collected operating data, and issues a warning signal before the fault occurs, while providing a fault diagnosis report and repair suggestions.

9. A computer device comprising a memory, a processor and a computer program stored in the memory and executable on the processor, characterized in that: When the processor executes the computer program, the steps of the method according to any one of claims 1 to 8 are implemented.

10. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the steps of the method according to any one of claims 1 to 8 are implemented.

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