Space radiation environment multi-model coupling simulation method and device and computer equipment

Abstract

The application provides a space radiation environment multi-model coupling simulation method and device and computer equipment, relates to the technical field of computer simulation, and the simulation method comprises the following steps: dividing a simulation time range into a plurality of simulation time points in a continuous distribution according to a simulation granularity; instantiating each initial orbit task parameter into a first simulation object, traversing all the first simulation objects at each simulation time point, and obtaining a current state parameter of each first simulation object at the current simulation time point; obtaining a plurality of space radiation environment model initial parameters according to an initial position and the initial orbit task parameter, instantiating each space radiation environment model initial parameter into a second simulation object, traversing all the second simulation objects according to the current state parameter of each first simulation object at the current simulation time, and calculating quantization data of the space radiation environment model. The application can realize multi-task orbit and multi-model high coupling simultaneous calculation, and improves the calculation efficiency.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of computer simulation, in particular to a space radiation environment multi-model coupling simulation method and device, computer equipment and a computer readable storage medium. BACKGROUND

[0002] Due to the action of the earth's own magnetic field, the charged particles (mainly composed of negatively charged electrons and positively charged protons) moving in the universe will be captured by the earth's magnetic field, and will do reciprocating motion in the earth's magnetic field while accompanying cyclotron and drift motion. These charged particles come from cosmic rays and neutron decay, and high-energy charged particles will continuously supplement into the earth's magnetic field, while these charged particles will escape from the magnetic field or be consumed by the action of the earth's neutral atmosphere, and the high-energy charged particles in the earth's magnetic field form a dynamic balance, which is called the earth's radiation belt.

[0003] Electronic circuits and electronic devices on artificial satellites will be hit by high-energy particles when the satellite's orbit passes through the earth's radiation belt, causing failure or damage to the satellite's electrical system and resulting in mission failure.

[0004] A plurality of radiation belt quantification models have been developed in the prior art to describe and quantify the radiation environment around the earth. In the past, the space radiation environment model calculation method is generally to separately calculate the satellite orbit operation data file to obtain an orbit data file, use different space radiation environment simulation calculation models to separately calculate the radiation environment data again for the orbit operation data file, and obtain a radiation environment data file, and then perform subsequent analysis or calculation. Such a calculation method has low coupling degree, cannot realize simultaneous calculation of satellite orbit and radiation environment and output or display of results, has many calculation steps, is inconvenient for users to use, is not user-friendly for primary users, requires users to have relevant industry knowledge and work experience, has low efficiency, requires setting parameters, reading and saving a large number of result files at each step, and reduces the calculation efficiency, and cannot realize multi-task simultaneous calculation and efficient calculation of orbit and model. SUMMARY

[0005] The problem solved by the present application is that the existing space radiation environment model calculation method has low coupling degree, which affects the calculation efficiency.

[0006] To solve the above problems, the present application provides a space radiation environment multi-model coupling simulation method, comprising:

[0007] obtaining a simulation time range and a simulation granularity,

[0008] dividing the simulation time range into a plurality of simulation time points according to the simulation granularity;

[0009] To acquire the satellite's initial position and initial orbital parameters in space.

[0010] Each initial orbital mission parameter is instantiated as a first simulation object. At each simulation moment, all first simulation objects are traversed to obtain the current state parameters of each first simulation object at the current simulation moment.

[0011] Based on the initial position and the initial orbital mission parameters, multiple initial parameters of the space radiation environment model are obtained. Each initial parameter of the space radiation environment model is instantiated into a second simulation object. Based on the current state parameters of each first simulation object at the current simulation time, all second simulation objects are traversed to calculate the quantized data of the space radiation environment model.

[0012] Optionally, the simulation time range is calculated using the simulation start time and the simulation end time, and both the simulation start time and the simulation end time are in integer Julian days.

[0013] Optionally, the step of traversing all the first simulation objects at each simulation moment and obtaining the current state parameters of each first simulation object at the current simulation moment includes: starting from the simulation start moment, traversing all the first simulation objects one by one at each simulation moment and obtaining the current state parameters of each first simulation object at the current simulation moment, until the simulation end moment.

[0014] Optionally, obtaining the initial position and initial orbital mission parameters of the satellite in space includes: obtaining the satellite orbital elements at the start of the simulation, and obtaining the initial position and initial orbital mission parameters of the satellite in space based on the satellite orbital elements.

[0015] Optionally, the initial orbital mission parameters include the initial orbital mission position, and the initial orbital mission position is represented by the initial position information in the J2000 geocentric inertial frame.

[0016] Optionally, the current state parameters of the first simulation object include current location information expressed in latitude, longitude, and altitude.

[0017] Optionally, the space radiation environment model includes a proton model of the Earth's radiation belts or an electron model of the Earth's radiation belts.

[0018] The advantage of the space radiation environment multi-model coupled simulation method described in this invention compared with the prior art is that: this invention provides a space radiation environment multi-model coupled simulation method that can realize the simultaneous calculation of multiple mission orbits and multiple models with high coupling, thereby improving the calculation efficiency.

[0019] To address the above problems, the present invention also provides a multi-model coupled simulation device for space radiation environment, characterized in that it comprises:

[0020] The acquisition unit is used to acquire the simulation time range and simulation granularity.

[0021] The acquisition unit is also used to acquire the initial position and initial orbital mission parameters of the satellite in space.

[0022] A segmentation unit, configured to divide the simulation time range into multiple continuously distributed simulation moments according to the simulation granularity.

[0023] The calculation unit is configured to instantiate each of the initial orbital mission parameters into a first simulation object, traverse all the first simulation objects at each simulation moment, and obtain the current state parameters of each first simulation object at the current simulation moment.

[0024] The computing unit is further configured to obtain multiple initial parameters of the space radiation environment model based on the initial position and the initial orbital mission parameters, instantiate each initial parameter of the space radiation environment model into a second simulation object, and traverse all the second simulation objects according to the current state parameters of each first simulation object at the current simulation time to calculate the quantized data of the space radiation environment model.

[0025] The space radiation environment multi-model coupling simulation device and the space radiation environment multi-model coupling simulation method described in this invention have the same advantages over the prior art, and will not be repeated here.

[0026] To address the aforementioned problems, the present invention also provides a computer device, including a computer-readable storage medium storing a computer program and a processor, wherein the computer program is read and executed by the processor to implement the aforementioned multi-model coupled simulation method for space radiation environment.

[0027] The advantages of the computer equipment and the multi-model coupled simulation method for the space radiation environment described in this invention are the same as those of the prior art, and will not be repeated here.

[0028] To address the aforementioned problems, the present invention also provides a computer-readable storage medium storing a computer program, which is read and executed by a processor to implement the aforementioned multi-model coupled simulation method for space radiation environment.

[0029] The advantages of the computer-readable storage medium and the multi-model coupled simulation method for space radiation environment described in this invention compared to the prior art are the same, and will not be repeated here. Attached Figure Description

[0030] Figure 1 This is an application environment diagram of the multi-model coupling simulation method for space radiation environment in this embodiment of the invention;

[0031] Figure 2 This is a flowchart of the multi-model coupled simulation method for space radiation environment in an embodiment of the present invention;

[0032] Figure 3 This is a schematic diagram of the three-level logical relationship of the multi-model coupling simulation method for space radiation environment in this embodiment of the invention;

[0033] Figure 4 This is a structural diagram of the multi-model coupled simulation device for space radiation environment in an embodiment of the present invention;

[0034] Figure 5 This is an internal structural diagram of a computer device in an embodiment of the present invention. Detailed Implementation

[0035] The technical solutions in the embodiments of this application will be clearly and thoroughly described below with reference to the accompanying drawings.

[0036] In the description of the embodiments in this application, the term "some embodiments" means that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same implementation or instance. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0037] Figure 1 This diagram illustrates the application environment of the multi-model coupled simulation method for space radiation environment in this embodiment. (Refer to...) Figure 1 This industrial control computer (ICC) cross-machine restoration method is applied to an ICC cross-machine restoration system. The ICC cross-machine restoration system includes a terminal 110 and a server 120. The terminal 110 and server 120 are connected via a network. The terminal 110 can be a desktop terminal or a mobile terminal; the mobile terminal can be at least one of a mobile phone, tablet computer, or laptop computer. The server 120 can be a standalone server or a server cluster consisting of multiple servers.

[0038] like Figure 2 As shown, in one embodiment, a multi-model coupled simulation method for space radiation environment is provided. This embodiment mainly applies this method to the above-mentioned... Figure 1 Let's take terminal 110 (or server 120) as an example. (Refer to...) Figure 2 The multi-model coupled simulation method for the space radiation environment specifically includes the following steps:

[0039] Step 210: Obtain the simulation time range and simulation granularity.

[0040] Step 220: Divide the simulation time range into multiple continuously distributed simulation moments according to the simulation granularity;

[0041] Step 230: Obtain the satellite's initial position and initial orbital parameters in space.

[0042] Step 240: Instantiate each of the initial orbital mission parameters into a first simulation object, and traverse all the first simulation objects at each simulation moment to obtain the current state parameters of each first simulation object at the current simulation moment;

[0043] Step 250: Based on the initial position and the initial orbital mission parameters, obtain multiple initial parameters of the space radiation environment model, instantiate each initial parameter of the space radiation environment model into a second simulation object, and traverse all the second simulation objects according to the current state parameters of each first simulation object at the current simulation time to calculate the quantized data of the space radiation environment model.

[0044] In some embodiments, in step 210, the simulation time range is calculated using the simulation start time and the simulation end time, and both the simulation start time and the simulation end time are in integer Julian days. Thus, using continuous real numbers to represent time facilitates calculation.

[0045] In this embodiment, the simulation start time and simulation end time are obtained by converting the initial Gregorian calendar year, month, day, hour, minute, and second into integer Julian days.

[0046] In some embodiments, step 240, which involves traversing all the first simulation objects at each simulation moment and obtaining the current state parameters of each first simulation object at the current simulation moment, includes: starting from the simulation start moment, traversing all the first simulation objects one by one at each simulation moment and obtaining the current state parameters of each first simulation object at the current simulation moment, until the simulation end moment.

[0047] In some embodiments, step 230, obtaining the initial position and initial orbital mission parameters of the satellite in space, includes: obtaining the satellite orbital elements at the start of the simulation, and obtaining the initial position and initial orbital mission parameters of the satellite in space based on the satellite orbital elements.

[0048] In some embodiments, the initial orbital mission parameters include an initial orbital mission position, and the initial orbital mission position is represented by initial position information in the J2000 geocentric inertial frame.

[0049] The J2000 geocentric inertial frame is defined as a celestial reference coordinate system using the celestial equator and equinox at the time J2000 (12:00 on January 1, 2000). The origin of the J2000 coordinate system coincides with the Earth's center of mass. The X-axis points to the mean vernal equinox at the time J2000, the Z-axis points to the North Pole, and the Y-axis, X-axis, and Z-axis form a right-handed rectangular coordinate system, which is an inertial coordinate system.

[0050] In some embodiments, the current state parameters of the first simulation object include current location information expressed in latitude, longitude, and altitude.

[0051] In this embodiment, latitude, longitude, and altitude are generated in the WGS-84 centroid coordinate system, with the origin coinciding with the Earth's center of mass. Its Z-axis points to the conventional polar direction as defined by the International Bureau of Time in 1984, the X-axis points to the intersection of the conventional meridian and the conventional equator, and the Y-axis forms a right-handed rectangular coordinate system with the X and Z axes.

[0052] In this embodiment, the latitude, longitude, and altitude in the WGS-84 centroid coordinate system are obtained by transforming the geocentric J2000 coordinate system through the geocentric-ground-fixed coordinate system. The geocentric-ground-fixed coordinate system is defined as having its origin coinciding with the Earth's centroid, the Z-axis pointing to the Earth's North Pole, the X-axis pointing to the intersection of the equator and the Greenwich Meridian, and the Y-axis, X-axis, and Z-axis forming a right-handed rectangular coordinate system.

[0053] In some embodiments, the space radiation environment model includes a proton model of the Earth's radiation belts or an electron model of the Earth's radiation belts.

[0054] like Figure 3 As shown, this embodiment provides a multi-model coupled simulation method for space radiation environment, comprising three levels. The first level is the simulation time set, which iterates through each simulation time step by step from the start time to the end time. The second level is the orbital task set, where the user can initialize multiple orbital task parameters. This method instantiates these initialized orbital task parameters into multiple first simulation objects, iterates through all first simulation objects during calculation, and updates the latest state of each first simulation. The third level is the space radiation environment model set. Within the second level, this level initializes all space radiation environment models based on the initialization data of the multiple orbital task parameters, instantiates them according to their initialization information, and calculates the quantitative characterization data of the space radiation environment models based on the latest state of the first simulations within the second level. This method enables highly coupled simultaneous calculation of multiple mission orbits and multiple models, improving computational efficiency.

[0055] like Figure 4 As shown, another embodiment of the present invention also provides a multi-model coupled simulation device for space radiation environment, comprising:

[0056] Step 410, acquisition unit, the acquisition unit is used to acquire the simulation time range and simulation granularity.

[0057] The acquisition unit is also used to acquire the initial position and initial orbital mission parameters of the satellite in space.

[0058] Step 420, Segmentation unit, the segmentation unit is used to divide the simulation time range into multiple continuously distributed simulation moments according to the simulation granularity.

[0059] Step 430: The calculation unit instantiates each of the initial orbital mission parameters into a first simulation object, traverses all the first simulation objects at each simulation moment, and obtains the current state parameters of each first simulation object at the current simulation moment.

[0060] The computing unit is further configured to obtain multiple initial parameters of the space radiation environment model based on the initial position and the initial orbital mission parameters, instantiate each initial parameter of the space radiation environment model into a second simulation object, and traverse all the second simulation objects according to the current state parameters of each first simulation object at the current simulation time to calculate the quantized data of the space radiation environment model.

[0061] The space radiation environment multi-model coupling simulation device and the space radiation environment multi-model coupling simulation method described in this embodiment have the same advantages over the prior art, and will not be repeated here.

[0062] In one embodiment, a computer device is provided, including a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, it implements the steps of the above-described multi-model coupled simulation method for space radiation environment.

[0063] Figure 5 An internal structural diagram of a computer device in one embodiment is shown. Specifically, this computer device may be... Figure 1 Terminal 110 (or server 120) in the middle. For example... Figure 5As shown, the computer device includes a processor, memory, network interface, input device, and display screen connected via a system bus. The memory includes non-volatile storage media and internal memory. The non-volatile storage media stores an operating system and may also store computer programs. When executed by the processor, these programs enable the processor to implement a multi-model coupled simulation method for space radiation environments. The internal memory may also store computer programs, which, when executed by the processor, enable the processor to perform the same simulation method. The display screen can be an LCD screen or an e-ink screen. The input device can be a touch layer covering the display screen, buttons, a trackball, or a touchpad mounted on the device's casing, or an external keyboard, touchpad, or mouse.

[0064] In one embodiment, a computer-readable storage medium is provided, on which a computer program is stored, which, when executed by a processor, implements the steps of the above-described multi-model coupled simulation method for space radiation environment.

[0065] Those skilled in the art will understand that all or part of the processes in the above embodiments can be implemented by a computer program instructing related hardware. The program can be stored in a non-volatile computer-readable storage medium, and when executed, it can include the processes of the embodiments described above. Any references to memory, storage, databases, 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. By way of illustration and not limitation, RAM is available in various forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), dual data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous link DRAM (SLDRAM), RAMbus direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and RAMbus dynamic RAM (RDRAM), etc.

[0066] While the present invention has been disclosed above, its scope of protection is not limited thereto. Those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present invention, and all such changes and modifications will fall within the scope of protection of the present invention.

Claims

1. A method for coupling simulation of space radiation environment multi-models, characterized in that, The method comprises the following steps: acquiring a simulation time range and a simulation granularity, dividing the simulation time range into a plurality of simulation time points according to the simulation granularity; acquiring initial positions and initial orbit mission parameters of a satellite in space, instantiating each initial orbit mission parameter as a first simulation object, traversing all the first simulation objects at each simulation time point, and acquiring a current state parameter of each first simulation object at the current simulation time point; acquiring a plurality of initial parameters of a space radiation environment model according to the initial positions and the initial orbit mission parameters, instantiating each initial parameter of the space radiation environment model as a second simulation object, traversing all the second simulation objects according to the current state parameter of each first simulation object at the current simulation time, and calling a space radiation environment model corresponding to each second simulation object to calculate quantization data of the space radiation environment model.

2. The space radiation environment multi-model coupled simulation method of claim 1, wherein, The simulation time range is calculated by a simulation start time and a simulation end time, and the simulation start time and the simulation end time are both in units of integer Julian days.

3. The space radiation environment multi-model coupled simulation method of claim 2, wherein, The step of traversing all the first simulation objects at each simulation time point and acquiring a current state parameter of each first simulation object at the current simulation time point comprises the following steps: starting from the simulation start time, traversing all the first simulation objects one by one at each simulation time point, acquiring a current state parameter of each first simulation object at the current simulation time point, and ending at the simulation end time.

4. The method of claim 2, wherein, The step of acquiring initial positions and initial orbit mission parameters of a satellite in space comprises the following steps: acquiring satellite orbit elements at the simulation start time, and acquiring initial positions and initial orbit mission parameters of a satellite in space according to the satellite orbit elements.

5. The method of claim 1, wherein, The initial orbit mission parameters comprise an initial orbit mission position, and the initial orbit mission position is represented by initial position information in a J2000 Earth-centered inertial system.

6. The space radiation environment multi-model coupled simulation method of claim 5, wherein, The current state parameter of the first simulation object comprises current position information represented by longitude, latitude and altitude.

7. The method of claim 1, wherein, The space radiation environment model comprises a proton model of the Earth's radiation belt or an electron model of the Earth's radiation belt.

8. A space radiation environment multi-model coupling simulation device, characterized in that, The method comprises the following steps: an acquiring unit configured to acquire a simulation time range and a simulation granularity, the acquiring unit is further configured to acquire initial positions and initial orbit mission parameters of a satellite in space, a dividing unit configured to divide the simulation time range into a plurality of simulation time points according to the simulation granularity, a calculating unit configured to instantiate each initial orbit mission parameter as a first simulation object, traverse all the first simulation objects at each simulation time point, and acquire a current state parameter of each first simulation object at the current simulation time point, The computing unit is further configured to obtain a plurality of initial parameters of space radiation environment models according to the initial position and the initial orbit mission parameters, instantiate each of the initial parameters of the space radiation environment models as a second simulation object, traverse all the second simulation objects according to a current state parameter of each of the first simulation objects at the current simulation time, and calculate quantization data of the space radiation environment models.

9. A computer device, comprising: The computer readable storage medium storing the computer program is read and run by the processor, and the space radiation environment multi-model coupling simulation method according to any one of claims 1-7 is realized.

10. A computer-readable storage medium, characterized in that, The computer readable storage medium stores a computer program, and the computer program is read and run by the processor, and the space radiation environment multi-model coupling simulation method according to any one of claims 1-7 is realized.

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