CN114662286A - Parameterized modeling method and device for satellite platform, electronic equipment and storage medium - Google Patents
Parameterized modeling method and device for satellite platform, electronic equipment and storage medium Download PDFInfo
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Abstract
The application discloses a parametric modeling method, a parametric modeling device, electronic equipment and a storage medium for a satellite platform, wherein the parametric modeling method comprises the following steps: the method comprises the steps of obtaining functional components for constructing a satellite platform model and attribute information corresponding to each functional component, wherein parameters of the functional components are determined based on a data parameter table of satellite platform data, the satellite platform model is generated by adopting an analog simulation technology based on the parameters of the functional components and the attribute information, the components and the parameters are separately configured, and then different attribute information is configured for the functional components to assemble simulation models of the same type and different models, so that the reusability and the modeling efficiency of the models are improved.
Description
Technical Field
The application relates to the technical field of satellite modeling, in particular to a parameterized modeling method and device for a satellite platform, electronic equipment and a storage medium.
Background
Space system tests are important for development, launching, testing and evaluation of space equipment, due to the limitation of conditions such as politics, expenses and time, the space system tests are mostly carried out in a simulation environment, and a satellite system is an indispensable part for carrying out the space system tests. The satellite system modeling comprises platform modeling and load modeling, and the satellite has the characteristics of multiple types, multiple components and complex technology.
Satellite modeling methods in the related art are poor in reusability of directional modeling for specific satellite models, lack of data standardization and low in modeling efficiency.
Disclosure of Invention
In view of the above problems, the present application provides a method, an apparatus, an electronic device, and a storage medium for parametric modeling of a satellite platform, so as to improve efficiency and reusability of satellite modeling.
In a first aspect, an embodiment of the present application provides a parameterized modeling method for a satellite platform, including: acquiring functional components for constructing a satellite platform model and attribute information corresponding to each functional component, wherein parameters of the functional components are determined based on a data parameter table of satellite platform data; and generating the satellite platform model by adopting an analog simulation technology based on the parameters of the functional components and the attribute information.
In a second aspect, an embodiment of the present application provides a parameterized modeling apparatus for a satellite platform, including: the acquisition module is used for acquiring functional components for constructing a satellite platform model and attribute information corresponding to each functional component, wherein parameters of the functional components are determined based on a data parameter table of satellite platform data. And the generating module is used for generating the satellite platform model by adopting an analog simulation technology based on the parameters of the functional components and the attribute information.
In a third aspect, an embodiment of the present application provides an electronic device, including: at least one processor and memory; the processor is configured to execute a computer program stored in the memory to implement the method for parametric modeling of a satellite platform as described in any one of the embodiments of the first aspect.
In a fourth aspect, an embodiment of the present application provides a computer storage medium, where the computer storage medium stores one or more programs, and the one or more programs are executable by an electronic device as described in the third aspect to implement the method for parameterizing a satellite platform as described in any one of the embodiments of the first aspect.
According to the parametric modeling method, the parametric modeling device, the electronic equipment and the storage medium for the satellite platform, the data parameter table after being sorted by the scattered open source information generation system can be utilized, data in the data parameter table provides required parameters for the functional components of the satellite platform, the satellite platform model is obtained by adopting an analog simulation technology according to the functional components and the parameter information corresponding to the functional components, the components with different functions are packaged according to the data parameter table, and then the required satellite platform model is formed, so that the efficiency of satellite modeling and the reusability of the model are improved.
It should be understood that the statements in this section do not necessarily identify key or critical features of the embodiments of the present application, nor do they limit the scope of the present application. Other features of the present application will become apparent from the following description.
Drawings
The present application will be described in more detail hereinafter on the basis of embodiments and with reference to the accompanying drawings.
Fig. 1 is a schematic flowchart illustrating a parametric modeling method for a satellite platform according to an embodiment of the present application;
fig. 2 is a schematic flow chart illustrating another parametric modeling method for a satellite platform proposed in an embodiment of the present application;
fig. 3 shows a schematic flowchart of step S220 of a parametric modeling method for a satellite platform according to an embodiment of the present application;
fig. 4 shows a schematic flowchart of step S230 of a parametric modeling method for a satellite platform according to an embodiment of the present application;
fig. 5 shows another schematic flow chart of the step S230 of the parametric modeling method for a satellite platform proposed in an embodiment of the present application;
FIG. 6 illustrates a satellite system model proposed in an embodiment of the present application;
FIG. 7 illustrates a satellite platform assembly diagram as set forth in an embodiment of the present application;
fig. 8 shows a block diagram of a satellite platform parameterized modeling apparatus proposed in an embodiment of the present application;
fig. 9 shows a block diagram of an electronic device proposed in an embodiment of the present application for executing a method for parameterised modelling of a satellite platform according to an embodiment of the present application;
fig. 10 illustrates a computer-readable storage medium proposed in an embodiment of the present application for storing or carrying a computer-readable storage medium for implementing a parametric modeling method for a satellite platform according to an embodiment of the present application.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to examples and accompanying drawings, and the exemplary embodiments and descriptions thereof are only used for explaining the present invention and are not meant to limit the present invention.
In the related technology, the satellite modeling method for the single-unit test is usually oriented modeling for specific satellite models, and the problem of poor reusability exists. In the system test, because the tested objects have the characteristics of multiple types, complex interaction, emerging performance and attention to overall efficiency test, modeling granularity of each object needs to be consistent as much as possible and high reusability so as to facilitate smooth and efficient simulation operation of the system test. In addition, data required by satellite modeling is numerous and complex, parameters are required to be not subjected to standardized carding, and the efficiency and reusability of system-oriented test modeling cannot be guaranteed.
In order to solve the above problems, the applicant has found through long-term research and provides a method, an apparatus, an electronic device, and a storage medium for parametric modeling of a satellite platform, which are provided in the embodiments of the present application, to obtain parameter data of a corresponding functional component through a data parameter table of satellite platform data, and generate a satellite platform model by using an analog simulation technique based on required functional components and parameter information, so as to implement separate configuration of the components and parameters, and further configure different parameter information for the functional components to assemble simulation models of the same type and different models, so as to improve reusability and modeling efficiency of the model. The satellite platform parametric modeling method is described in detail in the following embodiments.
The following is introduced for an application scenario of the satellite platform parametric modeling method provided by the embodiment of the present application:
referring to fig. 1, fig. 1 is a schematic flowchart of a parametric modeling method for a satellite platform provided in an embodiment of the present invention, in this embodiment, the parametric modeling method for a satellite platform may be applied to the parametric modeling device 800 for a satellite platform and the electronic device 200 (fig. 9) shown in fig. 8, where the electronic device may be a smart phone, a tablet computer, a desktop computer, or the like, which is not limited herein, and the following describes the flowchart shown in fig. 1 in detail, and the parametric modeling method for a satellite platform may include steps S110 to S120.
Step S110: the method comprises the steps of obtaining functional components for constructing a satellite platform model and attribute information corresponding to each functional component, wherein parameters of the functional components are determined based on a data parameter table of satellite platform data.
In this embodiment of the application, when the electronic device obtains the functional component and the attribute information of the satellite platform model, the functional component and the attribute information may be packaged and set correspondingly according to a parameter of the functional component. Illustratively, one functional component may be correspondingly provided with one or more attribute information. The satellite platform data can be supplemented based on component parameter requirements by mainly extracting a core and using a searchable parameter as a standard data parameter table basis by taking a mainstream satellite platform of a typical satellite type as a main extraction core. The functional components can be obtained by extracting data of the data parameter table according to the appearance structure, the main bearing structure, the technical characteristics of the satellite and the application condition of the satellite, and can be configured according to the use requirements after a plurality of functional components corresponding to the main structure of the satellite are established. It should be noted that the satellite main body structure may include: structure, power, thermal control, measurement and control, data management, attitude, track control, propulsion, etc., without limitation.
Step S120: and generating a satellite platform model by adopting an analog simulation technology based on the functional components and the attribute information.
In the embodiment of the application, in the electronic device, after a user confirms to select a corresponding functional component, attribute information correspondingly configured to the functional component can be correspondingly added, and the satellite functional component can be correspondingly configured according to requirements of practical application and the like to construct spacecrafts corresponding to different models.
In some embodiments, after the functional components are assembled through simulation to build the satellite platform model, simulation test can be performed on the satellite platform model, and for example, simulation test can be performed through physical angles such as force, electricity, heat, light and the like.
In the embodiment, different satellite platform data are extracted through a parameterized modeling method to obtain a data parameter table, the data of the data parameter table corresponds to the functional components, the functional components are configured with different attribute information, after the functional components are confirmed, the functional components are adjusted according to the attribute information, and then the functional components are configured with different attribute parameters to assemble simulation models of the same type and different models, so that the modeling efficiency and reusability of the satellite are improved.
Referring to fig. 2, fig. 2 is a schematic flowchart of another parametric modeling method for a satellite platform, which is applied to an electronic device and includes steps S210 to S230.
Step S210: satellite platform data is acquired based on the open source information.
In the embodiment of the application, the open source information may include satellite platform data related to a sun synchronous orbit, a geosynchronous orbit, and the like, which may be obtained according to a source such as a website, and the like. In addition, the same orbit also has multiple satellite platform data, illustratively, geosynchronous orbits, with different average launch masses, thruster powers, and platform sizes, etc. The electronic device may collect the currently existing data to obtain various satellite platform data.
Exemplary platform typical parameters for a sun-synchronous orbit are shown in table 1:
TABLE 1
Step S220: a data parameter table is determined based on the satellite platform data.
In the embodiment of the application, after the electronic device obtains the data of each different satellite platform, the data can be stored, and the data parameter table is established after the obtained satellite platform data is correspondingly classified.
Step S230: and confirming the parameters of the functional components corresponding to the functions of the satellite platform based on the data parameter table.
In the embodiment of the application, the electronic device can determine the functions of the satellite platform 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.
In this embodiment, different satellite platform data is acquired through the open source information, the data parameter table is determined according to the satellite platform data, and parameters required by the functional components of different required orbits can be determined through the data parameter table.
It should be noted that satellite platforms with different orbits may have some common data items, and these common data items are constructed into a standard parameter table, wherein the standard parameter table may not change with different platform types, and the standard parameter table may satisfy the requirements of different types of platforms to establish the standard table, and each type of platform may find the required corresponding parameters therein.
Referring to fig. 3, fig. 3 is another schematic flow chart of a satellite platform parametric modeling method provided in the embodiment of the present application in step S220. Applied to the electronic device, determining the data parameter table based on the satellite platform data may include step S310.
Step S310: the data parameter table is validated based on data in the satellite platform data for the on-orbit state of the satellite and data required for modeling of the satellite platform components.
In the embodiment of the application, firstly, parameters related to the on-orbit state in satellite platform data are selected, then parameters related to component modeling are selected according to a satellite platform component, and a standardized data parameter table is generated, so that modeling parameters required by main functions are sorted and confirmed.
In the embodiment, on the basis of the selection of the satellite platform data parameters, the data capable of establishing the satellite platform functional component is confirmed by combining the satellite functions, so that the applicability of different types of spacecrafts to the satellite platform component can be improved, the input parameter quantity is reduced after screening, the reusability is better, and the modeling efficiency is further improved.
Referring to fig. 4, fig. 4 is a schematic flowchart illustrating a satellite platform parametric modeling method in step S230 according to an embodiment of the present application. The method is applied to the electronic device, and the step of confirming the parameter of the functional component corresponding to the satellite platform function based on the data parameter table may include steps S410 to S430.
Step S410: and classifying the data parameter table based on the satellite platform function to obtain each parameter group.
Step S420: parameters of the corresponding functional component are identified based on the parameter set.
Step S430: and establishing each functional component based on analog simulation calculation, wherein the attribute information of each functional component can be adjusted, and the functional components comprise: the system comprises a track power component, an attitude control component, a measurement and control data transmission component, a data smoothing component, a temperature smoothing component and an energy balance component.
In the embodiment of the application, the electronic equipment classifies the acquired data parameter table based on functional analysis to obtain parameters of each component corresponding to different functions, and combines different required functional components to establish a satellite platform model, wherein the satellite platform model is mainly used for modeling functions of a satellite in-orbit running state, processing and distributing various instructions and the like, and comprises an orbit dynamics subsystem, an attitude control subsystem, a measurement and control subsystem, a data transmission subsystem, a power supply subsystem and the like. The attribute information of each functional component can be adjusted after being selected by a user, for example, the user inputs different data, or the user selects an attribute information selection bar with different configurations.
For example, referring to fig. 6, fig. 6 is a satellite system model provided in an embodiment of the present application, in the embodiment, an orbit dynamics component is used to implement a real-time extrapolation calculation of a satellite orbit, and an orbit extrapolation algorithm includes disomic, J2, J234, HPOP, SGP4, and the like, and meanwhile, various types of spatial visibility simulations are completed.
The attitude control component can be used for calculating the attitude of the satellite entity according to the attitude instruction and resolving the attitude quaternion under different coordinate systems.
The measurement and control data transmission assembly can be used for simulating the receiving and transmitting functions of satellite remote measurement, remote control and data transmission, simulating measurement and control data transmission link establishment, data transmission time delay and the like.
The data balance component can be used for calculating corresponding energy and data constraint conditions, sending the corresponding energy and data constraint conditions to the load system and the measurement and control data transmission system, and influencing the functions of the load system and the measurement and control data transmission system.
The temperature balance assembly can be used for simulating external heat flow and internal heat flow of the whole star, establishing a temperature field state equation and resolving the temperature state of the equipment node of the whole star.
The energy balance assembly can be used for simulating the battery array, the storage battery and the charge-discharge logic control function of the power supply subsystem, and the calculation of the load balance state of the whole satellite is realized.
Referring to fig. 5, fig. 5 is another schematic flow chart of a satellite platform parametric modeling method in step S230 according to an embodiment of the present application. The method is applied to the electronic device, and the method can further include steps S510 to S520, where the parameters of the functional component corresponding to the satellite platform function are determined based on the data parameter table.
Step S510: and acquiring input data and output data of the satellite platform in the data parameter table.
In the embodiment of the present application, the input data and the output data may be dynamically changing data in the satellite system model.
In the satellite platform, after the orbit dynamics component acquires the input data, the output data thereof may be used as the input data of other components, wherein the input data and the output data of each component construct interface connection transmission data to perform corresponding configuration processing according to the modeling requirements of the satellite.
Step S520: parameters of the functional component are determined based on the input data and the output data.
In this embodiment, the input data of the electronic device may complete the collection of various data through the network, and the electronic device confirms the parameters of the corresponding functional components according to the input data and the output data of the satellite, that is, confirms the functional use of the satellite model through data interaction.
It should be noted that the function components are divided according to functions of the satellite platform, the input data is used for assigning values to the function components and carrying out parameterization, parameter items of the same function component of satellites of the same type and different models are basically the same, specific parameter values are different, and the parameter values can be input data.
Referring to fig. 6, the satellite platform model mainly has an information interaction interface with the satellite load model and the ground system model to obtain input data and output data.
In some embodiments, the satellite platform model inputs externally: time information, ephemeris information, a ground system remote control injection instruction, ground system state information (including ground station position information, antenna pointing information, target motion information, target attitude information and the like), load working state and working mode and load imaging data volume.
In other embodiments, the satellite platform model outputs externally: position attitude pointing information of the satellite platform, link availability status and link margin, payload and telemetered download data.
In some embodiments, the functional components include: the orbit dynamics assembly, wherein, the parameterized modeling method of the satellite platform further comprises:
and acquiring the position and speed information of the current orbit of the satellite in the input data.
In the embodiment of the application, after the satellite passes a system time step, the position and speed information of the satellite at the next moment can be calculated and predicted according to the satellite orbit dynamics and the kinematics algorithm model.
The expression of the orbit dynamics component algorithm is as follows:
f＝fp+Δg+d+fl+fh+fsr；
wherein r is the vector of the satellite, r is the position vector of the satellite, f is the perturbation acceleration, fpIs thrust acceleration of satellite engine, Δ g is perturbation acceleration of earth gravity, d is perturbation acceleration of air resistance, flPerturbation of acceleration of moon's gravitational force, fsrThe solar light pressure perturbation acceleration is obtained.
It should be noted that the track simulation model completes the track forecasting and simulation functions. The orbit simulation model adopts a Cowell method to solve a spacecraft motion differential equation, wherein a DE405 model of JPL is adopted for calculating three-body gravitation, an JGM3 model is adopted for an earth gravitational field, an American standard atmospheric model is adopted for an atmospheric perturbation part, a standard light pressure section algorithm is adopted for light pressure, and an RKF78 is adopted for an integrator, so that higher precision is obtained. The orbit control part uses a limited thrust mode and can respectively select two types of orbit control analysis results of inertia keeping and orbit keeping.
In the embodiment of the application, the satellite is regarded as a mass point, and the motion of the satellite under the action of the gravity of the earth and other perturbation factors (such as sunlight pressure, atmospheric resistance and the like) is calculated, so that the simulation of the normal motion state of the orbit, the illumination and the measurement and control visibility can be realized. Orbital extrapolation calculations support methods of two, J2, J234, HPOP, SGP4, and the like. In addition, various space visibility simulations can be simultaneously completed, a motor-driven rail transfer simulation function with speed pulses as input is supported, an external motor-driven rail transfer instruction can be received by a user, and the instruction is sequentially processed by electronic equipment.
In the above embodiment, the input data may be the track prediction model support tle, the track six elements, the position and the speed of the ECI coordinate system, and the like, and the other inputs include the track change time and the speed pulse. The output data can be a high-precision orbit prediction result output by an orbit prediction model, and comprises information of six elements of position speed, satellite point longitude and latitude, real-time orbit and the like of a satellite in different coordinate systems, and meanwhile, the visibility calculation of the satellite on sunlight, a ground station and the like can be calculated and output.
Referring to fig. 7, fig. 7 is an assembly diagram of a satellite platform assembly according to an embodiment of the present disclosure.
In fig. 7, a satellite simulation model Amos3 is constructed by selecting a satellite framework model component, a satellite target feature component, a satellite orbital motion component, a satellite power supply component, and a satellite maneuver planning behavior component. Meanwhile, each component can be configured with different attribute parameters, namely each component can select or input and fill configuration information to adjust the satellite model.
It should be noted that, in the present application, the attitude control component, the measurement and control data transmission component, the data smoothing component, the temperature smoothing component, and the energy smoothing component may be correspondingly constructed according to the satellite modeling requirement, and are not repeated one by one.
Referring to fig. 8, fig. 8 is a view illustrating a parametric modeling apparatus for a satellite platform 800 according to the present application, including: an obtaining module 810 and a generating module 820, wherein:
the obtaining module 810 is configured to obtain functional components used for building a satellite platform model and attribute information corresponding to each functional component, where parameters of the functional components are determined based on a data parameter table of satellite platform data.
And a generating module 820, configured to generate a satellite platform model by using an analog simulation technique based on the parameter and attribute information of the functional component.
In some embodiments, the satellite platform parametric modeling apparatus 800 further includes: the device comprises a first acquisition module, a first confirmation module and a second confirmation module, wherein:
the first acquisition module is used for acquiring satellite platform data based on the open source information.
A first validation module to determine a data parameter table based on the satellite platform data.
And the second confirmation module is used for confirming the parameters of the functional components corresponding to the functions of the satellite platform based on the data parameter table.
In some embodiments, the first confirmation module comprises: a sub-validation module, wherein:
and the sub-confirmation module is used for confirming the data parameter table based on the data of the on-orbit state of the satellite in the satellite platform data and the data required by the modeling of the satellite platform assembly.
In some embodiments, the second confirmation module comprises: the classification module, the third confirmation module and the establishment adjustment module, wherein:
and the classification module is used for classifying the data parameter table based on the satellite platform function to obtain each parameter group.
And the third confirming module is used for confirming the parameters of the corresponding functional components based on the parameter group.
The device comprises an establishing and adjusting module and a control module, wherein the establishing and adjusting module is used for establishing each functional component based on analog simulation calculation, and the attribute information of each functional component can be adjusted, and the functional components comprise: the system comprises a track power component, an attitude control component, a measurement and control data transmission component, a data smoothing component, a temperature smoothing component and an energy balance component.
In some embodiments, the second confirmation module further comprises: data acquisition module and subassembly confirm the module, wherein:
and the data acquisition module is used for acquiring input data and output data of the satellite platform in the data parameter table.
A component validation module to determine parameters of the functional component based on the input data and the output data.
In some embodiments, the satellite platform parametric modeling apparatus 800 further includes: a motion data validation module for a satellite, wherein:
and the motion data confirmation module of the satellite is used for confirming the motion data of the satellite based on the orbital dynamics algorithm in the orbital power assembly.
In some embodiments, the satellite platform parametric modeling apparatus 800 further includes: a satellite position confirmation module, wherein:
a satellite position confirmation module for confirming the position of the satellite based on the orbital power assembly.
In some embodiments, the satellite position confirmation module is further configured to confirm a satellite high-precision orbit prediction result based on the parameters input by the orbit dynamics algorithm, where the prediction result includes six elements, namely, position speed, satellite point longitude and latitude, and real-time orbit of the satellite in different coordinate systems.
It should be noted that the device embodiment in the present application corresponds to the foregoing method embodiment, and specific principles in the device embodiment may refer to the contents in the foregoing method embodiment, which is not described herein again.
In several embodiments provided in this embodiment, the coupling between the modules may be electrical, mechanical or other type of coupling.
In addition, functional modules in the embodiments of the present invention may be integrated into one processing module, or each of the modules may exist alone physically, or two or more modules are integrated into one module. The integrated module can be realized in a hardware mode, and can also be realized in a software functional module mode.
Referring to fig. 9, fig. 9 is a block diagram of an electronic device 200 capable of executing the above method for parameterizing satellite platform according to the embodiment of the present disclosure, where the electronic device 200 may be a smart phone, a tablet computer, a computer, or a portable computer.
The electronic device 200 also includes a processor 202 and a memory 204. The memory 204 stores programs that can execute the content of the foregoing embodiments, and the processor 202 can execute the programs stored in the memory 204.
Processor 202 may include, among other things, one or more cores for processing data and a message matrix unit. The processor 202 interfaces with various components throughout the electronic device 200 using various interfaces and circuitry to perform various functions of the electronic device 200 and process data by executing or executing instructions, programs, code sets, or instruction sets stored in the memory 204 and invoking data stored in the memory 204. Alternatively, the processor 202 may be implemented in hardware using at least one of Digital Signal Processing (DSP), Field-Programmable Gate Array (FPGA), and Programmable Logic Array (PLA). The processor 202 may integrate one or a combination of a Central Processing Unit (CPU), a Graphics Processing Unit (GPU), a modulation decoder, and the like. Wherein, the CPU mainly processes an operating system, a user interface, an application program and the like; the GPU is used for rendering and drawing display content; the modem is used to handle wireless communications. It is to be understood that the modulation decoder described above may not be integrated into the processor, but may be implemented by a communication chip.
The Memory 204 may include a Random Access Memory (RAM) or a Read-Only Memory (Read-Only Memory). The memory 204 may be used to store instructions, programs, code sets, or instruction sets. Memory 204 may include a program storage area and a data storage area, where the program storage area may store instructions for implementing an operating system, instructions for implementing at least one function (e.g., instructions for a user to obtain a random number), instructions for implementing the various method embodiments described below, and the like. The stored data area may also store data (e.g., random numbers) created by the terminal in use, and the like.
The electronic device 200 may further include a network module for receiving and transmitting electromagnetic waves, and implementing interconversion between the electromagnetic waves and the electrical signals, so as to communicate with a communication network or other devices, for example, an audio playing device. The network module may include various existing circuit elements for performing these functions, such as an antenna, a radio frequency transceiver, a digital signal processor, an encryption/decryption chip, a Subscriber Identity Module (SIM) card, memory, and so forth. The network module may communicate with various networks such as the internet, an intranet, a wireless network, or with other devices via a wireless network. The wireless network may comprise a cellular telephone network, a wireless local area network, or a metropolitan area network. The screen can display the interface content and perform data interaction.
Referring to fig. 10, a block diagram of a computer-readable storage medium according to an embodiment of the present application is shown. The computer-readable storage medium 900 has stored therein a program code 910, and the program code 910 can be called by a processor to execute the method described in the above method embodiments.
The computer-readable storage medium 900 may be an electronic memory such as a flash memory, an EEPROM (electrically erasable programmable read only memory), an EPROM, a hard disk, or a ROM. Alternatively, the computer-readable storage medium includes a non-volatile computer-readable storage medium. The computer readable storage medium 900 has storage space for program code 910 to perform any of the method steps of the method described above. The program code 910 can be read from or written to one or more computer program products. The program code 910 may be compressed, for example, in a suitable form.
Embodiments of the present application also provide a computer program product or computer program comprising computer instructions stored in a computer-readable storage medium. The processor of the computer device reads the computer instructions from the computer readable storage medium, and the processor executes the computer instructions to cause the computer device to execute the satellite platform parametric modeling method described in the above various alternative implementations.
The above embodiments are only used to illustrate the technical solutions of the present application, and not to limit the same; although the present application has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; such modifications and substitutions do not necessarily depart from the spirit and scope of the corresponding technical solutions in the embodiments of the present application.
Claims (10)
1. A parametric modeling method for a satellite platform, the method comprising:
acquiring functional components for constructing a satellite platform model and attribute information corresponding to each functional component, wherein parameters of the functional components are determined based on a data parameter table of satellite platform data;
and generating the satellite platform model by adopting an analog simulation technology based on the parameters of the functional components and the attribute information.
2. The method of claim 1, further comprising:
acquiring the satellite platform data based on open source information;
determining a data parameter table based on the satellite platform data;
and confirming the parameters of the functional components corresponding to the functions of the satellite platform based on the data parameter table.
3. The method of claim 2, wherein determining a table of data parameters based on the satellite platform data comprises:
and confirming a data parameter table based on the data of the on-orbit state of the satellite in the satellite platform data and the data required by the modeling of the satellite platform component.
4. The method of claim 2, wherein said identifying parameters of said functional components corresponding to satellite platform functions based on said data parameter table comprises:
classifying the data parameter table based on the satellite platform function to obtain each parameter group;
confirming the corresponding parameters of the functional components based on the parameter groups;
and establishing each functional component based on analog simulation calculation, wherein the attribute information of each functional component can be adjusted, and the functional components comprise: the system comprises a track power component, an attitude control component, a measurement and control data transmission component, a data smoothing component, a temperature smoothing component and an energy balance component.
5. The method of claim 2, wherein said identifying parameters of said functional components corresponding to satellite platform functions based on said data parameter table comprises:
acquiring input data and output data of the satellite platform in the data parameter table;
determining parameters of the functional component based on the input data and the output data.
6. The method of claim 5, further comprising: confirming motion data of the satellite based on an orbit dynamics algorithm in the orbit power assembly, wherein the expression of the orbit dynamics algorithm is as follows:
f＝fp+Δg+d+fl+fh+fsr；
wherein r is the vector of the satellite, r is the position vector of the satellite, f is the perturbation acceleration, fpIs thrust acceleration of satellite engine, Δ g is perturbation acceleration of earth gravity, d is perturbation acceleration of air resistance, flPerturbation of acceleration of moon's gravitational force, fsrThe solar light pressure perturbation acceleration is obtained.
7. The method of claim 6, further comprising: confirming a position of a satellite based on the orbital power assembly, comprising:
and confirming a satellite high-precision orbit forecasting result based on the parameters input by the orbit dynamics algorithm, wherein the forecasting result comprises six elements of position and speed, satellite point longitude and latitude, real-time orbit and the like of the satellite in different coordinate systems.
8. A parametric modeling apparatus for a satellite platform, the apparatus comprising:
the system comprises an acquisition module, a data processing module and a data processing module, wherein the acquisition module is used for acquiring functional components for constructing a satellite platform model and attribute information corresponding to each functional component, and parameters of the functional components are determined based on a data parameter table of satellite platform data;
and the generating module is used for generating the satellite platform model by adopting an analog simulation technology based on the parameters of the functional components and the attribute information.
9. An electronic device, comprising:
one or more processors;
a memory;
one or more programs, wherein 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 configured to perform the method of parametric modeling of a satellite platform of any of claims 1-7.
10. A computer-readable storage medium having program code stored thereon, the program code being invoked by one or more processors to perform the method of parameterised modeling of a satellite platform according to any of claims 1 to 7.
Priority Applications (1)
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