CN113361004A - Method and device for popularizing space dynamics knowledge based on analog simulation - Google Patents

Method and device for popularizing space dynamics knowledge based on analog simulation Download PDF

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CN113361004A
CN113361004A CN202110534958.9A CN202110534958A CN113361004A CN 113361004 A CN113361004 A CN 113361004A CN 202110534958 A CN202110534958 A CN 202110534958A CN 113361004 A CN113361004 A CN 113361004A
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王宇
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Abstract

The invention discloses a method and a device for popularizing space dynamics knowledge based on analog simulation, wherein a three-dimensional digital earth model is constructed and used as a background frame for popularizing space dynamics knowledge; establishing an in-orbit satellite database, and representing the instant orbit information of the in-orbit satellite through the number of orbits; establishing a satellite class, constructing an orbit radical character string conversion function through the satellite class, solving a near angle by adopting a Newton method and solving the current time position of the in-orbit satellite; and determining the number of the materialization classes according to the number of the on-orbit satellites, respectively calculating the positions and the orbits of the on-orbit satellites, and transmitting the positions and the orbit data of the on-orbit satellites to a background frame for real-time display. The invention is beneficial to understanding and mastering of people on the aerospace dynamics knowledge, is beneficial to culturing more aerospace talents and promotes the development of aerospace careers in China.

Description

Method and device for popularizing space dynamics knowledge based on analog simulation
Technical Field
The invention relates to the technical field of computer simulation, in particular to a method and a device for popularizing space dynamics knowledge based on simulation.
Background
With the rapid development of aerospace industry in China, projects such as satellite launching, manned aerospace, moon and mars detection are already in the view of the whole population. The inventor finds that many students are constantly asking about messages about the aerospace cause, and reminds that the child also has been deeply interested in the affairs, and most people can generate more or less curious psychology at a certain stage.
The enlightenment education is the gold period for cultivating interests, if the aerospace related knowledge is intuitively displayed to the public (particularly students), more talents willing to engage in aerospace career will be inevitable in the future, more space industry experts will appear in the society, and the enlightenment education is more beneficial to cultivating individual talents like Erlomask, thereby promoting the development of the civil and aerospace industry. The stable talents inflow and the industry foundation are taken as the guarantee, so that the progress of China from the aerospace big country to the aerospace strong country can be better promoted. However, the complexity of space dynamic computation and space information description can hinder the popularization of knowledge in the space field. A technical scheme beneficial to popularization of the space dynamics knowledge is urgently needed.
Disclosure of Invention
Therefore, the invention provides a method and a device for popularizing the space dynamics knowledge based on analog simulation, so that people can understand and master the space dynamics knowledge and the development of the space industry in China is promoted.
In order to achieve the above object, in a first aspect, the present invention provides a method for popularizing knowledge of space dynamics based on simulation, including the following steps:
constructing a three-dimensional digital earth model, and taking the three-dimensional digital earth model as a background frame for popularizing the space dynamics knowledge;
establishing an in-orbit satellite database, and representing the instant orbit information of the in-orbit satellite through the number of orbits;
establishing a satellite class, constructing an orbit radical character string conversion function through the satellite class, solving a near angle by adopting a Newton method and solving the current time position of the in-orbit satellite;
and determining the number of the materialization classes according to the number of the on-orbit satellites, respectively calculating the positions and the orbits of the on-orbit satellites, and transmitting the positions and the orbit data of the on-orbit satellites to a background frame for real-time display.
As a preferable scheme of the method for popularizing the space dynamics knowledge based on simulation, the three-dimensional digital Earth model adopts a 3D Earth in open source codes of WorldWind, OSSIMPlanet, Gps3D, Earth3D or Apache EChats.
As a preferable scheme of the method for popularizing the space dynamics knowledge based on the simulation, the number of the tracks comprises the long radius of the tracks, epoch time, track inclination angle, ascension of the ascending intersection point, perigee angular distance, mean perigee angle and number of turns per day.
As a preferred scheme of the method for popularizing the space dynamics knowledge based on analog simulation, the attribute parameters of the satellite class comprise a satellite norad code, a name, epoch time, current time, orbit inclination, ascension, eccentricity, perigee angular distance, mean perigee angle, number of turns per day, semi-major axis and eccentricity angle;
the satellite class comprises methods of constructivity, attribute display, Newton method for solving a near angle, a frame x coordinate, a frame y coordinate, a frame z coordinate, an integrated position and an orbit function.
As an optimal scheme of the method for popularizing the space dynamics knowledge based on simulation, a formula for solving the approach angle by a Newton method is as follows:
E-esinE＝M
f(E)＝(E-esinE)-M
Figure BDA0003069246410000021
in the formula, E is a deflection angle, M is a mean approach point angle, and E is a natural constant.
As an optimal scheme of the method for popularizing the space dynamics knowledge based on analog simulation, a formula for solving the current time position of the orbiting satellite is as follows:
Figure BDA0003069246410000022
Figure BDA0003069246410000023
Figure BDA0003069246410000031
in the formula (I), the compound is shown in the specification,
Figure BDA0003069246410000032
indicating the current time-of-day position of the orbiting satellite,
Figure BDA0003069246410000033
denotes the first intermediate quantity introduced, without actual meaning,
Figure BDA0003069246410000034
and representing the introduced second intermediate quantity, without actual meaning, E is a near angle, E is a natural constant, a is the long radius of the orbit, omega is the ascension of the ascending intersection point, omega is the angular distance of the near place, and i is the inclination angle of the orbit.
As an optimal scheme of the space dynamics knowledge popularization method based on simulation, the space dynamics knowledge popularization game is developed by adopting the space dynamics knowledge popularization method based on simulation, and the space dynamics knowledge popularization game comprises parameter setting, launching and orbit entering, orbit changing and deep space exploration.
In a second aspect, a device for popularizing knowledge of space dynamics based on simulation is provided, which includes:
the background frame module is used for constructing a three-dimensional digital earth model and taking the three-dimensional digital earth model as a background frame for popularizing the space dynamics knowledge;
the on-orbit satellite module is used for establishing an on-orbit satellite database and expressing the instant orbit information of the on-orbit satellite through the number of orbits;
the satellite module is used for establishing a satellite class, constructing an orbit radical character string conversion function through the satellite class, solving a near angle by adopting a Newton method and solving the current time position of the in-orbit satellite;
and the operation display module is used for determining the number of the materialization classes according to the number of the on-orbit satellites, respectively calculating the positions and the orbits of the on-orbit satellites, and transmitting the position and orbit data of the on-orbit satellites to the background frame for real-time display.
In a third aspect, there is provided a computer readable storage medium having stored therein program code for the method for popularizing knowledge of simulation-based space dynamics of the first aspect or any possible implementation thereof.
In a fourth aspect, there is provided an electronic device comprising a processor coupled with a storage medium, the processor executing instructions in the storage medium to cause the electronic device to perform the method for popularizing knowledge based on simulation simulations of space dynamics of the first aspect or any possible implementation thereof.
The invention has the following advantages: constructing a three-dimensional digital earth model, and taking the three-dimensional digital earth model as a background frame for popularizing the space dynamics knowledge; establishing an in-orbit satellite database, and representing the instant orbit information of the in-orbit satellite through the number of orbits; establishing a satellite class, constructing an orbit radical character string conversion function through the satellite class, solving a near angle by adopting a Newton method and solving the current time position of the in-orbit satellite; and determining the number of the materialization classes according to the number of the on-orbit satellites, respectively calculating the positions and the orbits of the on-orbit satellites, and transmitting the positions and the orbit data of the on-orbit satellites to a background frame for real-time display. The invention is beneficial to understanding and mastering of people on the aerospace dynamics knowledge, is beneficial to culturing more aerospace talents and promotes the development of aerospace careers in China.
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In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. It should be apparent that the drawings in the following description are merely exemplary, and that other embodiments can be derived from the drawings provided by those of ordinary skill in the art without inventive effort.
The structures, ratios, sizes, and the like shown in the present specification are only used for matching with the contents disclosed in the specification, so that those skilled in the art can understand and read the present invention, and do not limit the conditions for implementing the present invention, so that the present invention has no technical significance, and any structural modifications, changes in the ratio relationship, or adjustments of the sizes, without affecting the functions and purposes of the present invention, should still fall within the scope of the present invention.
Fig. 1 is a schematic flow chart of a method for popularizing knowledge of space dynamics based on simulation provided in embodiment 1 of the present invention;
fig. 2 is a satellite display interface of the method for popularizing knowledge of space dynamics based on simulation provided in embodiment 1 of the present invention;
fig. 3 is a satellite Norad code query interface of the method for popularizing knowledge of space dynamics based on simulation provided in embodiment 1 of the present invention;
fig. 4 is a query result interface of the method for popularizing knowledge of space dynamics based on simulation provided in embodiment 1 of the present invention;
fig. 5 is a schematic diagram of a device for popularizing knowledge of space dynamics based on simulation provided in embodiment 2 of the present invention.
Detailed Description
The present invention is described in terms of particular embodiments, other advantages and features of the invention will become apparent to those skilled in the art from the following disclosure, and it is to be understood that the described embodiments are merely exemplary of the invention and that it is not intended to limit the invention to the particular embodiments disclosed. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Example 1
Referring to fig. 1, an embodiment 1 of the present invention provides a method for popularizing knowledge of space dynamics based on simulation, including the following steps:
s1, constructing a three-dimensional digital earth model, and taking the three-dimensional digital earth model as a background frame for popularizing the space dynamics knowledge;
s2, establishing an on-orbit satellite database, and representing the instant orbit information of the on-orbit satellite through the number of orbits;
s3, establishing a satellite class, constructing an orbit radical character string conversion function through the satellite class, solving a near angle by adopting a Newton method and solving the current time position of the in-orbit satellite;
and S4, determining the number of the materialization classes according to the number of the orbiting satellites, respectively calculating the positions and the orbits of the orbiting satellites, and transmitting the positions and the orbit data of the orbiting satellites to a background frame for real-time display.
In this embodiment, the three-dimensional digital Earth model may adopt a 3D Earth in WorldWind, OSSIMPlanet, Gps3D, Earth3D, or Apache ECharts open source code. The three-dimensional digital earth model selects open-source digital earth as a background frame, preferably 3D earth in Apache EChats open-source codes, Apache EChats is a data visualization chart library based on JavaScript, provides a data visualization chart which is intuitive, vivid, interactive and customizable, and codes based on JavaScript can be directly used under HTML web pages.
In this embodiment, the number of orbits is a parameter necessary for describing a celestial body or a spacecraft under the action of newton's law of motion and newton's law of universal gravitation, and determining the orbit of the spacecraft when the spacecraft moves on the keplerian orbit. The number of the tracks comprises the long radius of the tracks, epoch time, track inclination angle, ascension at the ascending intersection point, perigee angular distance, average perigee angle and number of turns per day. Specifically, a user menu type query and application is provided through establishing an on-orbit satellite database. The difficulty is that the real-time track information needs to be obtained through measurement of a large number of observation devices, can be obtained through establishing a cooperation mechanism or cooperating with an industry research institution, and can be obtained through open source data in the research and development test stage.
In this embodiment, the attribute parameters of the satellite class include a satellite norad code, a name, epoch time, current time, an orbit inclination angle, a rising intersection declination, an eccentricity, a perigee angular distance, a mean perigee angle, a number of turns per day, a semi-major axis, and an eccentricity angle;
the satellite class comprises methods of constructivity, attribute display, Newton method for solving a near angle, a frame x coordinate, a frame y coordinate, a frame z coordinate, an integrated position and an orbit function.
Specifically, a satellite class is established, which includes 12 attributes and 8 methods (1 of which is a construction method, and the specific implementation code is as follows:
Figure BDA0003069246410000061
in the embodiment, an orbit radical character string conversion function is constructed through satellite classes, the orbit radical character string is decomposed, corresponding items are taken and converted into required attributes,
Figure BDA0003069246410000073
for the parameter array after the root number decomposition, the implementation code is as follows:
Figure BDA0003069246410000071
in this embodiment, because the approximate angle E is relatively convenient to use during conversion, the number of the tracks is directly given, but the approximate angle E is obtained by computing the mean-near-point angle M and needs to be obtained by iteration through a newton method, and the formula for solving the approximate angle by the newton method is as follows:
E-esinE＝M
f(E)＝(E-esinE)-M
Figure BDA0003069246410000072
in the formula, E is a deflection angle, M is a mean approach point angle, and E is a natural constant.
Specifically, the implementation code for solving the deflection angle by the newton method is as follows:
Figure BDA0003069246410000081
in this embodiment, the formula for solving the current time position of the orbiting satellite is:
Figure BDA0003069246410000082
Figure BDA0003069246410000083
Figure BDA0003069246410000084
in the formula (I), the compound is shown in the specification,
Figure BDA0003069246410000085
indicating the current time-of-day position of the orbiting satellite,
Figure BDA0003069246410000086
denotes the first intermediate quantity introduced, without actual meaning,
Figure BDA0003069246410000087
and representing the introduced second intermediate quantity, without actual meaning, E is a near angle, E is a natural constant, a is the long radius of the orbit, omega is the ascension of the ascending intersection point, omega is the angular distance of the near place, and i is the inclination angle of the orbit.
Specifically, solving the current time position implementation code of the orbiting satellite is as follows:
Figure BDA0003069246410000088
Figure BDA0003069246410000091
in the embodiment, an astronomical dynamics knowledge popularization game development based on simulation is adopted, and the astronomical dynamics knowledge popularization game comprises parameter setting, launching and orbit entering, orbit changing and deep space exploration. In order to increase the interest, the method can be developed into a space dynamics knowledge popularization game. The system can obtain points or other rewards by completing tasks set by simple parameters at the initial stage, then gradually increase the difficulty under the promotion condition, and increase the tasks of launching orbit entry, changing orbit, deep space exploration and the like, and can pay proper attention to the well completed users and relevant units of the aerospace industry such as part of schools, research institutions, civil enterprises and the like.
Referring to fig. 2, the satellite display interface for the method for popularizing the space dynamics knowledge based on the simulation of the invention comprises a group of synchronous satellite displays, a group of Beidou satellite displays, a group of Galileo satellites displays and two optional satellites displays. FIG. 3 is a satellite Norad code query interface of an implementation process, and FIG. 4 is an example of a satellite query result of the implementation process.
In conclusion, the three-dimensional digital earth model is constructed and used as a background frame for popularizing the space dynamics knowledge; establishing an in-orbit satellite database, and representing the instant orbit information of the in-orbit satellite through the number of orbits; establishing a satellite class, constructing an orbit radical character string conversion function through the satellite class, solving a near angle by adopting a Newton method and solving the current time position of the in-orbit satellite; and determining the number of the materialization classes according to the number of the on-orbit satellites, respectively calculating the positions and the orbits of the on-orbit satellites, and transmitting the positions and the orbit data of the on-orbit satellites to a background frame for real-time display. The invention is beneficial to understanding and mastering of people on the aerospace dynamics knowledge, is beneficial to culturing more aerospace talents and promotes the development of aerospace careers in China.
Example 2
Referring to fig. 5, an embodiment 2 of the present invention provides an apparatus for popularizing knowledge of space dynamics based on simulation, including:
the background frame module 1 is used for constructing a three-dimensional digital earth model and taking the three-dimensional digital earth model as a background frame for popularizing the space dynamics knowledge;
the in-orbit satellite module 2 is used for establishing an in-orbit satellite database and expressing the instant orbit information of the in-orbit satellite through the number of orbits;
the satellite module 3 is used for establishing a satellite class, constructing an orbit radical character string conversion function through the satellite class, solving a near angle by adopting a Newton method and solving the current time position of the in-orbit satellite;
and the operation display module 4 is used for determining the number of the materialization classes according to the number of the on-orbit satellites, respectively calculating the positions and the orbits of the on-orbit satellites, and transmitting the position and orbit data of the on-orbit satellites to a background frame for real-time display.
It should be noted that, because the contents of information interaction, execution process, and the like between the modules/units of the space dynamics knowledge popularization device based on simulation are based on the same concept as the method embodiment in embodiment 1 of the present application, the technical effects brought by the contents are the same as the method embodiment of the present application, and specific contents can be referred to the description in method embodiment 1 shown in the foregoing of the present application.
Example 3
Embodiment 3 of the present invention provides a computer-readable storage medium, where a program code of a simulation-based space dynamics knowledge popularization method is stored in the computer-readable storage medium, where the program code includes instructions for executing the simulation-based space dynamics knowledge popularization method of embodiment 1 or any possible implementation manner of the method.
The computer-readable storage medium can be any available medium that can be accessed by a computer or a data storage device, such as a server, a data center, etc., that incorporates one or more of the available media. The usable medium may be a magnetic medium (e.g., floppy disk, hard disk, magnetic tape), an optical medium (e.g., DVD), or a semiconductor medium (e.g., Solid State Disk (SSD)), among others.
Example 4
Embodiment 4 of the present invention provides an electronic device, where the electronic device includes a processor, the processor is coupled to a storage medium, and when the processor executes an instruction in the storage medium, the electronic device is enabled to execute the method for popularizing the space dynamics knowledge based on simulation in embodiment 1 or any possible implementation manner thereof.
Specifically, the processor may be implemented by hardware or software, and when implemented by hardware, the processor may be a logic circuit, an integrated circuit, or the like; when implemented in software, the processor may be a general-purpose processor implemented by reading software code stored in a memory, which may be integrated in the processor, located external to the processor, or stand-alone.
In the above embodiments, the implementation may be wholly or partially realized by software, hardware, firmware, or any combination thereof. When implemented in software, may be implemented in whole or in part in the form of a computer program product. The computer program product includes one or more computer instructions. When loaded and executed on a computer, cause the processes or functions described in accordance with the embodiments of the invention to occur, in whole or in part. The computer may be a general purpose computer, a special purpose computer, a network of computers, or other programmable device. The computer instructions may be stored in a computer readable storage medium or transmitted from one computer readable storage medium to another, for example, from one website site, computer, server, or data center to another website site, computer, server, or data center via wired (e.g., coaxial cable, fiber optic, Digital Subscriber Line (DSL)) or wireless (e.g., infrared, wireless, microwave, etc.).
It will be apparent to those skilled in the art that the modules or steps of the present invention described above may be implemented by a general purpose computing device, they may be centralized on a single computing device or distributed across a network of multiple computing devices, and alternatively, they may be implemented by program code executable by a computing device, such that they may be stored in a storage device and executed by a computing device, and in some cases, the steps shown or described may be performed in an order different than that described herein, or they may be separately fabricated into individual integrated circuit modules, or multiple ones of them may be fabricated into a single integrated circuit module. Thus, the present invention is not limited to any specific combination of hardware and software.
Although the invention has been described in detail above with reference to a general description and specific examples, it will be apparent to one skilled in the art that modifications or improvements may be made thereto based on the invention. Accordingly, such modifications and improvements are intended to be within the scope of the invention as claimed.

Claims (10)

1. The method for popularizing the space dynamics knowledge based on simulation is characterized by comprising the following steps of:
constructing a three-dimensional digital earth model, and taking the three-dimensional digital earth model as a background frame for popularizing the space dynamics knowledge;
establishing an in-orbit satellite database, and representing the instant orbit information of the in-orbit satellite through the number of orbits;
establishing a satellite class, constructing an orbit radical character string conversion function through the satellite class, solving a near angle by adopting a Newton method and solving the current time position of the in-orbit satellite;
and determining the number of the materialization classes according to the number of the on-orbit satellites, respectively calculating the positions and the orbits of the on-orbit satellites, and transmitting the positions and the orbit data of the on-orbit satellites to a background frame for real-time display.
2. The method of claim 1, wherein the three-dimensional digital Earth model is a 3D Earth in WorldWind, OSSIMPlanet, Gps3D, Earth3D, or Apache ECharts open source code.
3. The method of popularizing knowledge of space dynamics based on simulation according to claim 1, wherein the number of orbits includes a major radius of the orbit, epoch time, orbit inclination, ascension at the point of ascent, perigee angular separation, mean perigee angle and turns per day.
4. The method of popularizing knowledge of space dynamics based on simulation according to claim 1, wherein the attribute parameters of the satellite class include a satellite norad code, a name, an epoch time, a current time, an orbit inclination, a rising-crossing right ascension, an eccentricity, a perigee angle distance, a mean perigee angle, a number of turns per day, a semi-major axis, and an eccentricity angle;
the satellite class comprises methods of constructivity, attribute display, Newton method for solving a near angle, a frame x coordinate, a frame y coordinate, a frame z coordinate, an integrated position and an orbit function.
5. The method of popularizing knowledge of space dynamics based on simulation as claimed in claim 4, wherein the formula of the off-angle by Newton method is:
E-e sin E＝M
f(E)＝(E-e sin E)-M
Figure FDA0003069246400000011
in the formula, E is a deflection angle, M is a mean approach point angle, and E is a natural constant.
6. The method of popularizing knowledge of space dynamics based on simulation according to claim 1, wherein the formula for solving the current time position of the orbiting satellite is:
Figure FDA0003069246400000021
Figure FDA0003069246400000022
Figure FDA0003069246400000023
in the formula (I), the compound is shown in the specification,
Figure FDA0003069246400000024
indicating the current time-of-day position of the orbiting satellite,
Figure FDA0003069246400000025
denotes the first intermediate quantity introduced, without actual meaning,
Figure FDA0003069246400000026
and representing the introduced second intermediate quantity, without actual meaning, E is a near angle, E is a natural constant, a is the long radius of the orbit, omega is the ascension of the ascending intersection point, omega is the angular distance of the near place, and i is the inclination angle of the orbit.
7. The method for popularizing knowledge of space dynamics based on simulation as claimed in any one of claims 1 to 6, wherein the method for popularizing knowledge of space dynamics based on simulation is adopted to develop the game for popularizing knowledge of space dynamics, and the game for popularizing knowledge of space dynamics comprises parameter setting, launching and orbit entering, orbit changing and deep space exploration.
8. The device is popularized to space dynamics knowledge based on simulation, which is characterized by comprising:
the background frame module is used for constructing a three-dimensional digital earth model and taking the three-dimensional digital earth model as a background frame for popularizing the space dynamics knowledge;
the on-orbit satellite module is used for establishing an on-orbit satellite database and expressing the instant orbit information of the on-orbit satellite through the number of orbits;
the satellite module is used for establishing a satellite class, constructing an orbit radical character string conversion function through the satellite class, solving a near angle by adopting a Newton method and solving the current time position of the in-orbit satellite;
and the operation display module is used for determining the number of the materialization classes according to the number of the on-orbit satellites, respectively calculating the positions and the orbits of the on-orbit satellites, and transmitting the position and orbit data of the on-orbit satellites to the background frame for real-time display.
9. A computer-readable storage medium, characterized in that the computer-readable storage medium has stored therein a program code of the method for popularizing knowledge of space dynamics based on simulation according to any one of claims 1 to 7.
10. An electronic device comprising a processor coupled with a storage medium, wherein the processor, when executing instructions in the storage medium, causes the electronic device to perform the simulation-based space dynamics knowledge popularization method of any one of claims 1 to 7.
CN202110534958.9A 2021-05-17 2021-05-17 Method and device for popularizing space dynamics knowledge based on analog simulation Withdrawn CN113361004A (en)

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115320891A (en) * 2022-10-12 2022-11-11 北京航天驭星科技有限公司 Near-circle nominal orbit control method based on virtual satellite
CN116109782A (en) * 2023-04-12 2023-05-12 中科星图测控技术股份有限公司 Digital space scene visualization system and method for GEO orbit visual angle

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115320891A (en) * 2022-10-12 2022-11-11 北京航天驭星科技有限公司 Near-circle nominal orbit control method based on virtual satellite
CN116109782A (en) * 2023-04-12 2023-05-12 中科星图测控技术股份有限公司 Digital space scene visualization system and method for GEO orbit visual angle
CN116109782B (en) * 2023-04-12 2023-07-07 中科星图测控技术股份有限公司 Digital space scene visualization system and method for GEO orbit visual angle

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