Parameterized Modeling Method, Device, Electronic Device and Storage Medium for Satellite Platform

Abstract

The present application discloses a parametric modeling method, device, electronic device and storage medium for a satellite platform, including: obtaining functional components for constructing a satellite platform model and attribute information corresponding to each of the functional components, wherein the parameters of the functional components are determined based on a data parameter table of satellite platform data, generating the satellite platform model by using simulation technology based on the parameters of the functional components and the attribute information, realizing separate configuration of components and parameters, and further assembling simulation models of the same type but different models by configuring different attribute information for the functional components, so as to improve the reusability of the model and the modeling efficiency.

Description

Technical Field

[0001] The present application relates to the technical field of satellite modeling, and particularly relates to a satellite platform parametric modeling method, device, electronic device, and storage medium. Background Art

[0002] Space system tests are crucial for the development, launch, testing, and evaluation of space equipment. Due to limitations in politics, funds, time, etc., space system tests are mostly carried out in a simulation environment, and the satellite system is an indispensable part of conducting space system tests. Satellite system modeling includes platform modeling and payload modeling. Satellites have the characteristics of various types, numerous components, and complex technologies.

[0003] Satellite modeling methods in related technologies often involve oriented modeling for specific satellite models, with poor reusability, and problems such as lack of data standardization and low modeling efficiency. Summary of the Invention

[0004] In view of the above problems, the present application provides a satellite platform parametric modeling method, device, electronic device, and storage medium to improve satellite modeling efficiency and reusability.

[0005] In a first aspect, an embodiment of the present application provides a satellite platform parametric modeling method, including: obtaining functional components for constructing a satellite platform model, and attribute information corresponding to each of the functional components, where parameters of the functional components are determined based on a data parameter table of satellite platform data; generating the satellite platform model by using simulation technology based on the parameters of the functional components and the attribute information.

[0006] In a second aspect, an embodiment of the present application provides a satellite platform parametric modeling device, including: an obtaining module, configured to obtain functional components for constructing a satellite platform model, and attribute information corresponding to each of the functional components, where parameters of the functional components are determined based on a data parameter table of satellite platform data; a generating module, configured to generate the satellite platform model by using simulation technology based on the parameters of the functional components and the attribute information.

[0007] In a third aspect, an embodiment of the present application provides an electronic device, which includes: at least one processor and a memory; the processor is configured to execute a computer program stored in the memory to implement the satellite platform parametric modeling method described in any implementation manner of the first aspect.

[0008] In a fourth aspect, an embodiment of the present application provides a computer storage medium, which stores one or more programs, and the one or more programs can be executed by the electronic device described in the third aspect to implement the satellite platform parametric modeling method described in any implementation manner of the first aspect.

[0009] The parametric modeling method, device, electronic device and storage medium for a satellite platform provided by the embodiments of the present application can generate a sorted data parameter table by using scattered open-source information. The data in the data parameter table provides the required parameters for the functional components of the satellite platform. According to the functional components and the corresponding parameter information, simulation technology is used to obtain the satellite platform model, realizing the encapsulation of components with different functions according to the data parameter table, and then forming the required satellite platform model, so as to improve the efficiency of satellite modeling and the reusability of the model.

[0010] It should be understood that the content described in this part is not intended to identify the key or important features of the embodiments of the present application, nor is it used to limit the scope of the present application. Other features of the present application will become easily understood through the following description. Brief Description of the Drawings

[0011] Hereinafter, the present application will be described in more detail based on the embodiments with reference to the drawings.

[0012] Figure 1 It shows a schematic flow chart of a parametric modeling method for a satellite platform proposed in an embodiment of the present application;

[0013] Figure 2 It shows a schematic flow chart of another parametric modeling method for a satellite platform proposed in an embodiment of the present application;

[0014] Figure 3 It shows a schematic flow chart of a process in step S220 of a parametric modeling method for a satellite platform proposed in an embodiment of the present application;

[0015] Figure 4 It shows a schematic flow chart of a process in step S230 of a parametric modeling method for a satellite platform proposed in an embodiment of the present application;

[0016] Figure 5 It shows another schematic flow chart of a process in step S230 of a parametric modeling method for a satellite platform proposed in an embodiment of the present application;

[0017] Figure 6 It shows a satellite system model proposed in an embodiment of the present application;

[0018] Figure 7 It shows an assembly drawing of satellite platform components proposed in an embodiment of the present application;

[0019] Figure 8 It shows a structural block diagram of a parametric modeling device for a satellite platform proposed in an embodiment of the present application.

[0020] Figure 9The block diagram of an electronic device for implementing the satellite platform parametric modeling method according to an embodiment of the present application is shown;

[0021] Figure 10 A computer-readable storage medium for storing or carrying an implementation of the satellite platform parametric modeling method according to an embodiment of the present application is shown. Detailed implementation manners

[0022] To make the objectives, technical solutions and advantages of the present invention clearer and more understandable, the present invention will be further described in detail below in conjunction with embodiments and the accompanying drawings. The illustrative embodiments and descriptions thereof of the present invention are only used to explain the present invention and are not intended to limit the present invention.

[0023] In the related art, satellite modeling methods for single-unit tests are often oriented to specific satellite models for directional modeling, resulting in poor reusability. Due to the characteristics of the objects under test in system tests, such as a large variety, complex interactions, emergence, and a greater focus on overall effectiveness verification, the modeling of each object requires as consistent modeling granularity and high reusability as possible to ensure the smooth and efficient operation of system test simulations. In addition, the data required for satellite modeling is extensive, and there is no standardized sorting of which parameters are needed, making it impossible to guarantee the efficiency and reusability of system test-oriented modeling.

[0024] To solve the above problems, the applicant has discovered through long-term research and proposed a satellite platform parametric modeling method, device, electronic device, and storage medium provided in the embodiments of the present application. By obtaining the parameter data of the corresponding functional components through the data parameter table of the satellite platform data, and using simulation technology based on the required functional components and parameter information to generate a satellite platform model, the separation of component and parameter configuration is realized. Furthermore, different parameter information can be configured for the functional components to assemble simulation models of the same type but different models, so as to improve the reusability and modeling efficiency of the models. Among them, the satellite platform parametric modeling method will be described in detail in the subsequent embodiments.

[0025] The application scenarios of the satellite platform parametric modeling method provided in the embodiments of the present application are introduced below:

[0026] Please refer to Figure 1 , Figure 1 which is a schematic flowchart of a satellite platform parametric modeling method provided in an embodiment of the present application. In this embodiment, the satellite platform parametric modeling method can be applied to a satellite platform parametric modeling device 800 and an electronic device 200 ( Figure 8 ) as shown in Figure 9 . The electronic device can be a smart phone, a tablet computer, a desktop computer, etc., which is not limited herein. Below, Figure 1The following describes the process in detail. The parametric modeling method for the satellite platform may include steps S110 to S120.

[0027] Step S110: Obtain the functional components for constructing the satellite platform model and the corresponding attribute information of each functional component. Among them, the parameters of the functional components are determined based on the data parameter table of the satellite platform data.

[0028] In the embodiment of the present application, when the electronic device obtains the functional components and attribute information of the satellite platform model, the functional components and attribute information may be encapsulated and set according to the parameters of the functional components. Exemplarily, one functional component may be correspondingly provided with one or more attribute information. Among them, the satellite platform data may be based on the mainstream satellite platforms of typical satellite types, extracting the core and queryable parameters as the basis of the standardized data parameter table, and then supplementing based on the component parameter requirements. The functional components can be obtained by extracting the data in the data parameter table according to the external shape structure, main load-bearing structure, satellite technical characteristics, and satellite application conditions. After establishing multiple functional components corresponding to the satellite main body structure, the functional components can be configured according to the usage requirements. It should be noted that the satellite main body structure may include: structure, power supply, thermal control, measurement and control, data management, attitude, orbit control, propulsion, etc., which are not limited herein.

[0029] Step S120: Generate a satellite platform model based on the functional components and attribute information by using simulation technology.

[0030] In the embodiment of the present application, in the electronic device, after the user confirms and selects the corresponding functional component, the attribute information configured corresponding to the functional component can be correspondingly added, and the satellite functional components can be configured accordingly according to actual application requirements, etc., to construct different types of spacecraft. The simulation technology can be configured in the electronic device through software, etc. After configuring the functional components for each required satellite component one by one and adding their attribute information, the parameter information is correspondingly configured, filled, and written to construct the required satellite platform model.

[0031] In some embodiments, after assembling the functional components through simulation to establish a satellite platform model, the satellite platform model can be subjected to simulation testing. Exemplarily, simulation tests can be carried out from physical aspects such as force, electricity, heat, and light.

[0032] In this embodiment, through the parametric modeling method, different satellite platform data are extracted to obtain a data parameter table, and the data in the data parameter table are configured corresponding to the functional components. The functional components are configured with different attribute information. After confirming the functional components, the functional components are adjusted according to the attribute information, and then different attribute parameters are configured for the functional components to assemble simulation models of the same type but different models, improving the modeling efficiency and reusability of the satellite.

[0033] Please refer to Figure 2 , Figure 2 , which is a schematic flowchart of another satellite platform parametric modeling method provided by an embodiment of the present application, applied to an electronic device. The satellite platform parametric modeling method may include steps S210 to S230.

[0034] Step S210: Obtain satellite platform data based on open-source information.

[0035] In the embodiment of the present application, the open-source information may include satellite platform data associated with sun-synchronous orbits, geosynchronous orbits, etc., which can be obtained from sources such as websites. The present application does not limit it. The common platforms corresponding to different orbits have different satellite platform data. In addition, there are also multiple satellite platform data for the same orbit. Exemplarily, taking the geosynchronous orbit as an example, it has different average launch masses, different thruster powers, and platform sizes, etc. The electronic device can collect the existing data to obtain various different satellite platform data.

[0036] Exemplarily, the typical parameters of the platform in the sun-synchronous orbit are shown in Table 1:

[0037]

[0038] Table 1

[0039] Step S220: Determine a data parameter table based on the satellite platform data.

[0040] In the embodiment of the present application, after the electronic device obtains various different satellite platform data, it can store the data, and after classifying the obtained satellite platform data correspondingly, establish a data parameter table.

[0041] Step S230: Confirm the parameters of the functional components corresponding to the satellite platform functions based on the data parameter table.

[0042] In the embodiment of the present application, the electronic device can determine the satellite platform functions according to the parameter types in the data parameter table, and classify the data of different functions to obtain the functional components corresponding to the parameter types.

[0043] In this embodiment, different satellite platform data are obtained through open-source information, a data parameter table is confirmed according to the satellite platform data, and the parameters required for the functional components of different required orbits can be determined through the data parameter table.

[0044] It should be noted that satellite platforms in different orbits may have some common data items. These common data items are constructed into a standard parameter table. The standard parameter table does not need to change with the different types of platforms and can meet the establishment of standard tables for different types of platforms. Each type of platform can find the corresponding parameters it needs in it.

[0045] Please refer to Figure 3 , Figure 3 which is another schematic flowchart in step S220 of the satellite platform parametric modeling method provided in the embodiment of the present application. Applied to an electronic device, determining the data parameter table based on satellite platform data may include step S310.

[0046] Step S310: Confirm the data parameter table based on the data of the satellite's on-orbit state in the satellite platform data and the data required for modeling the satellite platform components.

[0047] In the embodiment of the present application, first, select the parameters related to the on-orbit state in the satellite platform data, and then select the parameters associated with component modeling according to the satellite platform components and generate a standardized data parameter table to sort out and confirm the modeling parameters required for the main functions.

[0048] In this embodiment, by combining the satellite functions on the basis of selecting the satellite platform data parameters, the data of the satellite platform functional components can be established, which can improve the applicability of different models of spacecraft to the satellite platform components. And after screening, the number of input parameters is reduced, with better reusability and further improving the modeling efficiency.

[0049] Please refer to Figure 4 , Figure 4 which is a schematic flowchart in step S230 of a satellite platform parametric modeling method provided in the embodiment of the present application. Applied to an electronic device, confirming the parameters of the functional components corresponding to the satellite platform functions based on the data parameter table may include steps S410 to S430.

[0050] Step S410: Classify the data parameter table based on the satellite platform functions to obtain each parameter group.

[0051] Step S420: Confirm the parameters of the corresponding functional components based on the parameter group.

[0052] Step S430: And establish each functional component based on simulation calculations. The attribute information of each functional component can be adjusted. The functional components include: orbital power components, attitude control components, TT&C and data transmission components, data smoothing components, temperature smoothing components, and energy balance components.

[0053] In the embodiments of the present application, the electronic device classifies the obtained data parameter table based on functional analysis to obtain the parameters of each component corresponding to different functions, and combines the required different functional components to establish a satellite platform model. The satellite platform model is mainly used to model functions such as the on-orbit operation state of the satellite, processing and distributing various instructions, including orbital dynamics, attitude control, TT&C subsystem, data transmission subsystem, power subsystem, etc. The attribute information of each functional component can be adjusted after being selected by the user. For example, the user inputs different data, or the user selects the attribute information selection bar with different configurations.

[0054] Exemplarily, the satellite platform model can refer to Figure 6 , Figure 6 which is a satellite system model provided by the embodiments of the present application. In this embodiment, the orbital dynamics component is used to implement real-time extrapolation calculation of the satellite orbit. The orbit extrapolation algorithms include two-body, J2, J234, HPOP, SGP4, etc., and various space visibility simulations are completed at the same time.

[0055] The attitude control component can be used to calculate the attitude of the satellite entity according to the attitude instruction and solve the attitude quaternion in different coordinate systems.

[0056] The TT&C and data transmission component can be used to simulate the functions of satellite telemetry, remote control, and data transmission, and simulate the establishment of TT&C and data transmission links, data transmission delay, etc.

[0057] The data balance component can be used to calculate the corresponding energy and data constraint conditions and send them to the payload system and the TT&C and data transmission systems, and affect the latter's functions.

[0058] The temperature balance component can be used to simulate the external heat flux and internal heat flux of the satellite body, establish the state equation of the temperature field, and solve the temperature state of the equipment nodes of the entire satellite.

[0059] The energy balance component can be used to simulate the functions of the battery array, battery, charge and discharge logic control of the power subsystem of the satellite, and realize the calculation of the load balance state of the entire satellite.

[0060] Please refer to Figure 5 , Figure 5 which is another flow schematic diagram in step S230 of a satellite platform parametric modeling method provided by the embodiments of the present application. Applied to an electronic device, based on the data parameter table, the parameters of the functional components corresponding to the satellite platform functions are confirmed, and it may further include steps S510 to S520.

[0061] Step S510: Obtain the input data and output data of the satellite platform in the data parameter table.

[0062] In the embodiments of the present application, the input data and output data may be the various dynamically changing data in the satellite system model.

[0063] Exemplarily, in a satellite platform, after the orbital dynamics component obtains input data, its output data can be used as the input data for other components. Among them, the input data and output data of each component are connected through an interface to transmit data, so as to perform corresponding configuration processing according to the modeling requirements of the satellite.

[0064] Step S520: Determine the parameters of the functional component based on the input data and output data.

[0065] In the embodiment of the present application, the input data of the electronic device can complete the acquisition of various data through the network. The electronic device determines the parameters of the corresponding functional component according to the input data and output data of the satellite, that is, through data interaction, the functional use of the satellite model is confirmed.

[0066] It should be noted that the functional components are divided according to the functions of the satellite platform. The input data is used to assign values to the functional components and perform parameterization. The parameter items of the same functional component of satellites of the same type but different models are basically the same, and the specific parameter values are different. These parameter values can be input data.

[0067] Refer to Figure 6 , the satellite platform model mainly has information interaction interfaces with the satellite payload model and the ground system model to obtain input data and output data.

[0068] In some embodiments, the satellite platform model externally inputs: time information, ephemeris information, ground system remote control upload instructions, ground system status information (including ground station position information, antenna pointing information, target motion information, target attitude information, etc.), payload working status and working mode, payload imaging data volume.

[0069] In some other embodiments, the satellite platform model externally outputs: the position and attitude pointing information of the satellite platform, the link available status and link margin, and the downlink data of the payload and telemetry.

[0070] In some embodiments, the functional components include: an orbital dynamics component. Among them, the satellite platform parametric modeling method further includes:

[0071] Obtain the position and velocity information of the satellite's current orbit in the input data.

[0072] In the embodiment of the present application, after the satellite passes through a system time step, the position and velocity information of the satellite at the next moment can be calculated and predicted according to the satellite orbital dynamics and kinematics algorithm model.

[0073] Among them, the expression of the orbital dynamics component algorithm is:

[0074]

[0075] f=f p +Δg+d+f l +f h +f sr ;

[0076] Among them, r is the satellite's radius vector, r is the satellite's position vector, f is the perturbation acceleration, and f p is the thrust acceleration of the satellite engine, Δg is the earth's gravitational perturbation acceleration, d is the air resistance perturbation acceleration, f l is the lunar gravitational perturbation acceleration, f sr is the perturbation acceleration due to sunlight pressure.

[0077] It should be noted that the orbit simulation model performs orbit prediction and simulation functions. It uses the Cowell method to solve the differential equations of spacecraft motion. The three-body gravity calculations utilize JPL's DE405 model, the Earth's gravitational field utilizes the JGM3 model, the atmospheric perturbations utilize the US Standard Atmosphere Model, the light pressure utilizes the Standard Light Pressure Cross Section algorithm, and the RKF78 integrator for high accuracy. The orbit control component utilizes a finite thrust method, with two types of orbit control analysis options: inertial hold and orbit hold.

[0078] In an embodiment of the present application, by treating the satellite as a point mass and calculating its motion under the action of the earth's gravity and other perturbations (such as solar pressure, atmospheric resistance, etc.), it is possible to include orbital normal motion state simulation, illumination and measurement and control visibility simulation. Orbital extrapolation calculation supports methods such as two-body, J2, J234, HPOP, SGP4. In addition, various types of space visibility simulations can be completed simultaneously while supporting the maneuvering trajectory simulation function with speed pulses as input. The user can receive external maneuvering trajectory instructions, and the electronic equipment processes the instructions sequentially.

[0079] It should be noted that in the above embodiment, the input data can be the orbit prediction model supporting TLE, the six orbit elements, the position and velocity in the ECI coordinate system, and other inputs include the orbit change time and velocity pulse. The output data can be the orbit prediction model outputting high-precision orbit prediction results, including information such as the satellite's position and velocity in different coordinate systems, the longitude and latitude of the sub-satellite point, and the six real-time orbit elements. At the same time, the satellite's visibility to sunlight, ground stations, etc. can be calculated and output.

[0080] See also Figure 7 , Figure 7 This is an assembly diagram of a satellite platform component provided in an embodiment of the present application.

[0081] exist Figure 7In [the content], the satellite simulation model Amos3 is constructed by selecting the satellite frame model component, the satellite target feature component, the satellite orbital motion component, the satellite power supply component, and the satellite maneuver planning behavior component. At the same time, different attribute parameters can be configured for each component, that is, each component can select or input configuration information to adjust the satellite model.

[0082] It should be noted that in this application, the attitude control component, the TT&C and data transmission component, the data smoothing component, the temperature smoothing component, and the energy smoothing component can be constructed accordingly according to the satellite modeling requirements as needed. This application will not elaborate on them one by one.

[0083] Please refer to Figure 8 , Figure 8 which is a satellite platform parametric modeling device provided by this application. The satellite platform parametric modeling device 800 includes: an acquisition module 810 and a generation module 820, where:

[0084] The acquisition module 810 is used to acquire the functional components for constructing the satellite platform model and the corresponding attribute information of each functional component. Among them, the parameters of the functional components are determined based on the data parameter table of the satellite platform data.

[0085] The generation module 820 is used to generate the satellite platform model by using simulation technology based on the parameters and attribute information of the functional components.

[0086] In some embodiments, the satellite platform parametric modeling device 800 further includes: a first acquisition module, a first confirmation module, and a second confirmation module, where:

[0087] The first acquisition module is used to acquire satellite platform data based on open source information.

[0088] The first confirmation module is used to determine the data parameter table based on the satellite platform data.

[0089] The second confirmation module is used to confirm the parameters of the functional components corresponding to the satellite platform functions based on the data parameter table.

[0090] In some embodiments, the first confirmation module includes: a sub-confirmation module, where:

[0091] The sub-confirmation module is used to confirm the data parameter table based on the data of the satellite's on-orbit state in the satellite platform data and the data required for satellite platform component modeling.

[0092] In some embodiments, the second confirmation module includes: a classification module, a third confirmation module, and an establishment and adjustment module, where:

[0093] The classification module is used to classify the data parameter table based on the satellite platform functions to obtain each parameter group.

[0094] A third confirmation module, configured to confirm parameters of corresponding functional components based on a parameter group.

[0095] An establishment and adjustment module, configured to establish each functional component based on simulation calculations, and the attribute information of each functional component can be adjusted, where the functional components include: an orbital power component, an attitude control component, a measurement, control, and data transmission component, a data smoothing component, a temperature smoothing component, and an energy balance component.

[0096] In some embodiments, the second confirmation module further includes: a data acquisition module and a component confirmation module, where:

[0097] The data acquisition module is configured to acquire input data and output data of a satellite platform in a data parameter table.

[0098] The component confirmation module is configured to determine parameters of functional components based on the input data and the output data.

[0099] In some embodiments, the satellite platform parametric modeling device 800 further includes: a satellite motion data confirmation module, where:

[0100] The satellite motion data confirmation module is configured to confirm satellite motion data based on an orbital dynamics algorithm in the orbital power component.

[0101] In some embodiments, the satellite platform parametric modeling device 800 further includes: a satellite position confirmation module, where:

[0102] The satellite position confirmation module is configured to confirm the position of the satellite based on the orbital power component.

[0103] In some embodiments, the satellite position confirmation module is further configured to confirm a high-precision orbit prediction result of the satellite based on parameters input by the orbital dynamics algorithm, where the prediction result includes information such as the position and velocity of the satellite in different coordinate systems, the longitude and latitude of the sub-satellite point, and the six elements of the real-time orbit.

[0104] It should be noted that the device embodiments in this application correspond to the foregoing method embodiments. For the specific principles in the device embodiments, reference may be made to the content in the foregoing method embodiments, and details are not described herein again.

[0105] In several embodiments provided in this embodiment, the coupling between modules may be electrical, mechanical, or other forms of coupling.

[0106] In addition, in each embodiment of the present invention, each functional module can be integrated into one processing module, or each module can exist physically alone, or two or more modules can be integrated into one module. The above integrated module can be implemented in the form of hardware or in the form of a software functional module.

[0107] Please refer to Figure 9 , Figure 9 which is a structural block diagram of an electronic device 200 capable of executing the above satellite platform parametric modeling method provided by an embodiment of the present application. The electronic device 200 can be a smart phone, a tablet computer, a computer, a portable computer, or other devices.

[0108] The electronic device 200 further includes a processor 202 and a memory 204. Among them, a program that can execute the content in the foregoing embodiments is stored in the memory 204, and the processor 202 can execute the program stored in the memory 204.

[0109] Among them, the processor 202 can include one or more cores for processing data and a message matrix unit. The processor 202 connects various parts within the entire electronic device 200 using various interfaces and lines. By running or executing instructions, programs, code sets, or instruction sets stored in the memory 204, and by calling data stored in the memory 204, the processor 202 executes various functions of the electronic device 200 and processes data. Optionally, the processor 202 can be implemented in at least one hardware form of digital signal processing (DSP), field-programmable gate array (FPGA), or programmable logic array (PLA). The processor 202 can integrate a combination of one or several of a central processing unit (CPU), a graphics processing unit (GPU), and a modem decoder. Among them, the CPU mainly processes the operating system, user interface, and application programs, etc.; the GPU is responsible for rendering and drawing the display content; the modem is used to process wireless communication. It can be understood that the above modem decoder can also be not integrated into the processor and be implemented separately through a communication chip.

[0110] The memory 204 may include a Random Access Memory (RAM), or may also include a Read-Only Memory. The memory 204 can be used to store instructions, programs, codes, code sets, or instruction sets. The memory 204 may include a program storage area and a data storage area. The program storage area may store instructions for implementing an operating system, instructions for implementing at least one function (such as instructions for a user to obtain a random number), instructions for implementing the following various method embodiments, etc. The data storage area may also store data created during the use of the terminal (such as random numbers), etc.

[0111] The electronic device 200 may further include a network module and a screen. The network module is used to receive and send electromagnetic waves, realize the mutual conversion between electromagnetic waves and electrical signals, so as to communicate with a communication network or other devices, such as communicating with an audio playback device. The network module may include various existing circuit elements for performing these functions, such as antennas, radio frequency transceivers, digital signal processors, encryption / decryption chips, subscriber identity module (SIM) cards, memories, and so on. The network module can communicate with various networks such as the Internet, enterprise intranets, wireless networks, or communicate with other devices through a wireless network. The above-mentioned wireless network may include a cellular phone network, a wireless local area network, or a metropolitan area network. The screen can display interface content and perform data interaction.

[0112] Please refer to Figure 10 , which shows a structural block diagram of a computer-readable storage medium provided by an embodiment of the present application. Program code 910 is stored in the computer-readable storage medium 900, and the program code 910 can be called by a processor to execute the method described in the above method embodiments.

[0113] The computer-readable storage medium 900 may be an electronic memory such as a flash memory, an Electrically Erasable Programmable Read-Only Memory (EEPROM), an EPROM, a hard disk, or a ROM. Optionally, the computer-readable storage medium includes a non-transitory computer-readable storage medium. The computer-readable storage medium 900 has a storage space for the program code 910 for executing any method step in the above method. These program code 910 can be read out from or written into one or more computer program products. The program code 910 can be compressed in an appropriate form, for example.

[0114] The embodiments of the present application also provide a computer program product or a computer program. The computer program product or the computer program includes computer instructions, and the computer instructions are stored in a computer-readable storage medium. A processor of a computer device reads the computer instructions from the computer-readable storage medium, and the processor executes the computer instructions, so that the computer device executes the satellite platform parametric modeling method described in the foregoing various optional implementation manners.

[0115] The foregoing embodiments are only used to illustrate the technical solutions of the present application, rather than to limit them; although the present application has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions recorded in the foregoing embodiments, or perform equivalent replacements for some of the technical features; and these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the various embodiments of the present application.

Claims

1. A parametric modeling method for satellite platforms, characterized in that The method includes: Obtaining functional components for constructing a satellite platform model, and attribute information corresponding to each of the functional components, wherein the parameters of the functional components are determined based on a data parameter table of satellite platform data, and the functional components include: an orbital power component, an attitude control component, a TT&C and data transmission component, a data smoothing component, a temperature smoothing component, and an energy balance component; Generating the satellite platform model by using simulation technology based on the parameters of the functional components and the attribute information; The method further includes: Obtaining the satellite platform data based on open-source information; Determining a data parameter table based on the satellite platform data; Confirming the parameters of the functional components corresponding to the satellite platform functions based on the data parameter table; The determining the data parameter table based on the satellite platform data includes: Confirming a data parameter table based on the data of the satellite's on-orbit state in the satellite platform data and the data required for modeling the satellite platform components. Among them, there are common data items for satellite platforms in different orbits. Constructing the common data items into a standard parameter table, which does not change with the different types of platforms, can meet the establishment of a standard table for different types of platforms. Each type of platform can find the corresponding parameters it needs in the standard parameter table. Selecting the parameters related to the on-orbit state in the satellite platform data, and then selecting the parameters associated with component modeling according to the satellite platform components and generating a standardized data parameter table; The confirming the parameters of the functional components corresponding to the satellite platform functions based on the data parameter table includes: Obtaining the input data and output data of the satellite platform in the data parameter table, wherein the input data and output data are the dynamically changing data in the satellite system model. After the orbital dynamics component obtains the input data, the output data of the orbital dynamics component is used as the input data of other components, and the input data and output data of each component are connected through an interface to transmit data; Determining the parameters of the functional components based on the input data and output data.

2. The method according to claim 1, wherein The confirming the parameters of the functional components corresponding to the satellite platform functions based on the data parameter table includes: Classifying the data parameter table based on the satellite platform functions to obtain each parameter group; Confirming the parameters of the corresponding functional components based on the parameter group; And establishing each of the functional components based on simulation calculations, and the attribute information of each functional component can be adjusted.

3. The method according to claim 1, wherein The method further includes: Confirming the motion data of the satellite based on the orbital dynamics algorithm in the orbital power component, and the expression of the orbital dynamics algorithm is: f = f p +Δg + d + f l + f h + f sr ; Among them, \(r\) is the radius vector of the satellite, \(\vec{r}\) is the position vector of the satellite, \(\vec{f}\) is the perturbation acceleration, \(\vec{f}\) p is the thrust acceleration of the satellite engine, \(\Delta\vec{g}\) is the perturbation acceleration of the Earth's gravity, \(\vec{d}\) is the perturbation acceleration of the air resistance, \(\vec{f}\) l is the perturbation acceleration of the lunar gravity, \(\vec{f}\) sr is the perturbation acceleration of the solar radiation pressure.

4. The method according to claim 3, wherein The method further includes: Confirming the position of the satellite based on the orbital power component, including: Confirming the high-precision orbit prediction result of the satellite based on the parameters input by the orbital dynamics algorithm, wherein the prediction result includes the position and velocity of the satellite in different coordinate systems, the longitude and latitude of the sub-satellite point, and the six elements of the real-time orbit.

5. A satellite platform parametric modeling device, characterized in that, The device includes: An acquisition module, configured to acquire functional components for constructing a satellite platform model and attribute information corresponding to each of the functional components. The parameters of the functional components are determined based on a data parameter table of satellite platform data. The functional components include: an orbital power component, an attitude control component, a TT&C and data transmission component, a data smoothing component, a temperature smoothing component, and an energy balance component; A generation module, configured to generate the satellite platform model by using simulation technology based on the parameters of the functional components and the attribute information; The apparatus further includes: A first acquisition module, configured to acquire the satellite platform data based on open-source information; A first confirmation module, configured to determine a data parameter table based on the satellite platform data. There are common data items for satellite platforms in different orbits. The common data items are constructed into a standard parameter table, which does not change with different platform types and can meet the establishment of a standard table for different types of platforms. Each type of platform can find the corresponding parameters it needs in the standard parameter table; A second confirmation module, configured to confirm the parameters of the functional components corresponding to the satellite platform functions based on the data parameter table; The first confirmation module includes: A sub-confirmation module, configured to confirm the data parameter table based on the data of the satellite's on-orbit state in the satellite platform data and the data required for satellite platform component modeling; The second confirmation module includes: A data acquisition module, configured to acquire the input data and output data of the satellite platform in the data parameter table. The input data and output data are the dynamically changing data in the satellite system model. After the orbital dynamics component acquires the input data, the output data of the orbital dynamics component is used as the input data of other components. The input data and output data of each component are connected through an interface to transmit data; A component confirmation module, configured to determine the parameters of the functional components based on the input data and output data.

6. An electronic device, characterized in that, It includes: One or more processors; A memory; One or more programs, where the one or more programs are stored in the memory and configured to be executed by the one or more processors. The one or more programs are configured to execute the satellite platform parametric modeling method according to any one of claims 1-4.

7. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores program code, and the program code can be called by one or more processors to execute the satellite platform parametric modeling method according to any one of claims 1-4.

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