A space-time consistency control method suitable for a low-orbit mega constellation visualization system
By defining latitude and longitude concepts and time alignment mechanisms on a visual 3D programming platform, the coordinate transformation and time alignment problems of existing platforms are solved, enabling high-precision visual simulation of low-Earth orbit mega-constellations and improving the flexibility and accuracy of aerospace applications.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- SHANGHAI UNIV
- Filing Date
- 2023-04-11
- Publication Date
- 2026-05-29
AI Technical Summary
Existing visualization 3D programming platforms lack the ability to transform coordinate systems related to the physical world, cannot achieve flexibility in latitude and longitude concepts, and cannot align objects at different times in terms of time latitude, which limits their application in the aerospace field.
On the visual 3D programming platform, the concepts of latitude and longitude are defined, and the mutual conversion between the J2000 coordinate system, the latitude and longitude coordinate system and the 3D spatial local coordinate system is realized. An independent time system is established through the time acceleration coefficient. Combined with the SGP4 orbit prediction model and the Earth rotation simulation, time alignment and coordinate transformation are realized.
It enables satellite time-latitude alignment at different times, adds simulation of Earth's rotation and perturbation interference, and improves the accuracy and flexibility of low-Earth orbit mega-constellation simulation, meeting the visualization needs of actual satellite networks.
Smart Images
Figure CN116418433B_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of data computing, and in particular to a spatiotemporal consistency control method applicable to low-Earth orbit mega-constellation visualization systems. Background Technology
[0002] In recent years, the construction of low-Earth orbit (LEO) satellite constellations, exemplified by constellations like Starlink and OneNet, has fueled a global surge in LEO satellite constellation development, leading to a growing demand for satellite visualization and simulation. Due to their sheer size, rapid on-orbit operation, complex network layouts, and frequent routing and forwarding, mega-LEO constellations require simulation experiments on visualization platforms to verify and demonstrate their feasibility and computational effectiveness. To achieve a proportional mapping from the physical world to the virtual world, a 3D visualization programming platform was independently developed, and motion calculation methods at the mechanistic level were studied to complete accurate visualization simulations of LEO satellite constellations. This is of great significance for the online monitoring of satellite constellation operations.
[0003] Currently common visualization 3D programming platforms such as Unity3D and 3DMax only have a 3D spatial coordinate system within the engine platform, lacking the mutual conversion between common coordinate systems in the physical world, which reduces the flexibility for visualization mechanism calculations; in terms of the time dimension, they cannot directly align objects at different times, which limits their application in actual aerospace scenarios; and they have significant limitations in terms of model size accuracy, resulting in certain errors compared to objects in the physical world. Summary of the Invention
[0004] In view of the aforementioned deficiencies in existing technologies, the technical problem to be solved by this invention is that common visualization 3D programming platforms lack the transformation of coordinate systems related to the physical world, lack the concept of latitude and longitude, lack flexibility in the calculation of visualization mechanisms, and cannot align objects at different times in terms of time latitude, which would limit their application in the aerospace field. This invention provides a spatiotemporal consistency control method applicable to low-Earth orbit mega-constellation visualization systems. It defines the concept of latitude and longitude in the 3D space of the visualization 3D programming platform and realizes the mutual transformation between the J2000 coordinate system, the latitude and longitude elevation coordinate system, and the 3D local coordinate system. It also considers the time alignment problem, ensuring that satellites at different times can easily achieve time latitude alignment operations. Furthermore, it adds operations such as Earth rotation, perturbation interference, and automated import, making it more suitable for online simulation scenarios of low-Earth orbit mega-constellations.
[0005] To achieve the above objectives, this invention provides a spatiotemporal consistency control method applicable to low-Earth orbit mega-constellation visualization systems, comprising the following steps:
[0006] On a visual 3D programming platform, an independent time system is established based on a time acceleration factor;
[0007] Obtain the TLE ephemeris data of all satellites under a certain constellation, determine the starting operating time reference based on the time alignment function, and calculate the time distance between the satellite and the operating time reference;
[0008] Based on TLE ephemeris data, record epoch time, and satellite orbit time, the SGP4 orbit prediction model is used to calculate the spatial position of each satellite in real time.
[0009] Establish the latitude and longitude relationships within the visualization 3D programming platform, perform coordinate system transformation, and calculate the 3D world space coordinates of each satellite;
[0010] Based on the Earth's rotation period, the Earth's rotation is simulated and globally scaled according to a certain ratio;
[0011] Based on the operating time, the Earth's rotation angle and the positions of all satellites are updated in real time to showcase the massive low-Earth orbit constellation network.
[0012] Furthermore, based on the time acceleration factor, an independent time system is established, specifically including the following steps:
[0013] Based on the user interface, the time acceleration factor δ is obtained at this time, and its value ranges from 1 to 500.
[0014] Then, based on the time Δτ between the current frame and the previous frame, the accelerated time increment of the current frame is calculated.
[0015] Furthermore, the accelerated time increment for the current frame is calculated using the following conversion formula:
[0016]
[0017] Where t is the system time of the current frame after acceleration, t0 is the system time before the current frame, δ is the time acceleration coefficient, and Δτ is the time between the current frame and the previous frame.
[0018] Furthermore, the TLE ephemeris data of all satellites in a certain constellation is obtained, and the starting operating time reference is determined according to the time alignment function. The specific steps include:
[0019] Obtain the ephemeris data of all satellites to get the record epoch time for each satellite;
[0020] Based on the time alignment function, the starting time of operation is obtained, and the time distance between each satellite and the starting time is calculated.
[0021] Furthermore, based on the time alignment function, the starting operating time is obtained, and the time distance between each satellite and the operating time is calculated. The calculation formula is as follows:
[0022] e = max(e0, e1, e2, ...)
[0023] Δt i =ee i
[0024] Where e is the initial operating time, e0, e1, and η2 are the epoch times of different satellites, and Δy i Let e be the time distance between satellite i and the start time of its operation. i Let be the epoch time of satellite i.
[0025] Furthermore, the latitude and longitude relationships within the 3D programming platform are established, coordinate system transformation is performed, and the 3D world space coordinates of each satellite are calculated. Specific steps include:
[0026] Based on the satellite's spatial coordinates in the J2000 coordinate system, we obtain the satellite's longitude, latitude, and altitude in the latitude-longitude coordinate system.
[0027] Based on the concept of latitude and longitude, the latitude and longitude relationship within the 3D programming platform is established, and the current spatial rectangular coordinates of the satellite are obtained through the global scaling factor;
[0028] By establishing the parent-child relationship between Earth and the satellite, eliminating the interference of Earth's rotation, completing the local coordinate system transformation, and calculating the satellite's final coordinates at this time.
[0029] Furthermore, based on the satellite's spatial coordinates in the J2000 coordinate system, the satellite's longitude, latitude, and altitude in the latitude-longitude-height coordinate system are obtained. The conversion formula is as follows:
[0030]
[0031]
[0032] Where λ is the satellite longitude, denoted as satellite latitude, h as satellite altitude, N as radius of curvature of the reference ellipsoid, e as eccentricity of the ellipsoid, and a as major radius of the ellipsoid.
[0033] Furthermore, the latitude and longitude relationships within the 3D programming platform are established, and the current spatial rectangular coordinates of the satellite are calculated using a global scaling factor. The calculation formula is as follows:
[0034]
[0035] Where R is the average radius of the Earth, with a value of 6371.393 km, h is the satellite's altitude above the Earth, and μ is the system's global scaling factor, with a value of 100.
[0036] Furthermore, based on the established parent-child relationship between Earth and the satellite, a local coordinate system transformation is performed, and the satellite's final coordinates at this point are calculated using the following formula:
[0037]
[0038] Where (x′, y′, z′) are the transformed local coordinates, (x0, y0, z0) are the spatial coordinates of the Earth as the parent object, and s x It is the scale of the parent object's x-axis, s y It is the scale of the parent object's y-axis, s z It is the scale of the parent object's z-axis.
[0039] Furthermore, based on the Earth's rotation period, the Earth's rotation is simulated and globally scaled according to a certain ratio. The formula for calculating the angle through which the Earth rotates is as follows:
[0040]
[0041] Where θ is the angle rotated, sec is the total number of seconds in a day, and t is the system time.
[0042] Technical effect
[0043] This invention provides a spatiotemporal consistency control method applicable to a low-Earth orbit mega-constellation visualization system. It defines the concepts of latitude and longitude in the three-dimensional space of the visualization 3D programming platform and realizes the mutual conversion between the J2000 coordinate system, the latitude and longitude coordinate system, and the local coordinate system of the three-dimensional space. It also considers the time alignment problem, ensuring that satellites at different times can easily achieve time and latitude alignment operations. In addition, it adds operations such as Earth rotation, perturbation interference, and automatic import, which is more in line with the online simulation scenario of low-Earth orbit mega-constellations.
[0044] The following will further explain the concept, specific structure, and technical effects of the present invention in conjunction with the accompanying drawings, so as to fully understand the purpose, features, and effects of the present invention. Attached Figure Description
[0045] Figure 1 This is a flowchart illustrating a preferred embodiment of the spatiotemporal consistency control method applicable to a low-Earth orbit mega-constellation visualization system.
[0046] Figure 2 This is a satellite visualization effect diagram of a spatiotemporal consistency control method applicable to a low-Earth orbit mega-constellation visualization system, which is a preferred embodiment of the present invention. Detailed Implementation
[0047] To make the technical problems to be solved, the technical solutions, and the beneficial effects of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present invention and are not intended to limit the present invention.
[0048] In the following description, specific details, such as particular internal procedures and techniques, are set forth for illustrative purposes and not for limitation, in order to provide a thorough understanding of the embodiments of the invention. However, those skilled in the art will appreciate that the invention may be practiced in other embodiments without these specific details. In other instances, detailed descriptions of well-known systems, apparatuses, circuits, and methods have been omitted so as not to obscure the description of the invention with unnecessary detail.
[0049] like Figure 1 As shown, this invention provides a spatiotemporal consistency control method applicable to low-Earth orbit mega-constellation visualization systems, comprising the following steps:
[0050] S1: On a visual 3D programming platform, establish an independent time system based on a time acceleration factor; specifically including the following steps:
[0051] S11: Based on the user interface, obtain the time acceleration coefficient δ at this time, which ranges from 1 to 500.
[0052] S12: Then, based on the time Δτ between the current frame and the previous frame, calculate the accelerated time increment for the current frame. The conversion formula is as follows:
[0053]
[0054] Where t is the system time of the current frame after acceleration, t0 is the system time before the current frame, δ is the time acceleration coefficient, and Δτ is the time between the current frame and the previous frame.
[0055] S2: Obtain the TLE ephemeris data of all satellites under a certain constellation, determine the starting operating time reference based on the time alignment function, and calculate the time distance between the satellites and the operating time reference; specific steps include:
[0056] S21: Obtain the ephemeris data of all satellites, obtain the record epoch time of each satellite, and use it as input;
[0057] S22: Based on the time alignment function, obtain the initial operating time and calculate the time distance between each satellite and the operating time; specifically, based on the epoch time recorded by each satellite obtained in step S21, obtain a unified initial operating time according to the filtering of the time alignment function, and calculate the time distance between each satellite and the initial operating time. At the beginning of system startup, each satellite fills in the time difference to ensure time consistency. The calculation formula is as follows:
[0058] e = max(e0, e1, e2, ...)
[0059] Δt i =eei
[0060] Where e is the starting time, e0, e1, and e2 are the epoch times of different satellites, and Δt i Let e be the time distance between satellite i and the start time of its operation. i Let be the epoch time of satellite i.
[0061] S3: Based on TLE ephemeris data, recorded epoch time, and satellite operating time, the SGP4 orbit prediction model is used to calculate the spatial position of each satellite in real time. In this step, based on the TLE ephemeris data of all satellites in a certain constellation, the ephemeris data, recorded epoch time, and system operating time of the satellites are obtained and used as input. The SGP4 orbit prediction model is then used to calculate the spatial coordinates (x, y, z) of each satellite in the J2000 coordinate system in real time.
[0062] S4: Establish the latitude and longitude relationships within the visual 3D programming platform, perform coordinate system transformation, and calculate the 3D world space coordinates of each satellite; specifically, based on the satellite's spatial coordinates (x, y, z) obtained in step S3 in the J2000 coordinate system, calculate the satellite's longitude, latitude, and altitude in the latitude-longitude coordinate system. The transformation formula from J2000 coordinates to latitude-longitude coordinates is as follows:
[0063]
[0064]
[0065] Where λ is the satellite longitude, denoted as satellite latitude, h as satellite altitude, N as radius of curvature of the reference ellipsoid, e as eccentricity of the ellipsoid, and a as major radius of the ellipsoid.
[0066] S42: Based on the satellite longitude λ obtained in step S41 in the latitude-longitude coordinate system, the satellite latitude... Given the satellite's altitude h above the Earth, and based on the concepts of latitude and longitude, a latitude-longitude relationship suitable for the 3D programming platform space is established. Then, through global scaling, the satellite's spatial rectangular coordinates in the current 3D world space are obtained. The calculation formula is shown below:
[0067]
[0068] Where R is the average radius of the Earth, with a value of 6371.393 km, h is the satellite's altitude above the Earth, and μ is the system's global scaling factor, with a value of 100, representing that 1 unit in the three-dimensional programming platform space is equivalent to 100 km in the real world.
[0069] S43: Based on the spatial rectangular coordinates of the satellite obtained in step S42 in the three-dimensional world space, this spatial rectangular coordinate system belongs to a static coordinate system. Considering that the satellite's latitude and longitude reference system needs to be stationary relative to the Earth due to the Earth's rotation, a parent-child relationship between the Earth and the satellite is established to eliminate the interference of the Earth's rotation and complete the transformation from the spatial coordinate system in the three-dimensional world to the local coordinate system. The calculation formula is as follows:
[0070]
[0071] Where (x′, y′, z′) are the transformed local coordinates, (x0, y0, z0) are the spatial coordinates of the Earth as the parent object, and s x It is the scale of the parent object's x-axis, s y It is the scale of the parent object's y-axis, s z It is the scale of the parent object's z-axis.
[0072] S5: Simulate the Earth's rotation based on its rotation period, and scale it globally according to a certain ratio; the formula for calculating the angle through which the Earth rotates is as follows:
[0073]
[0074] Where θ is the angle rotated, sec is the total number of seconds in a day, and t is the system time.
[0075] S6: Based on the running time, update the Earth's rotation angle and the positions of all satellites in real time to display the mega-constellation network in low Earth orbit. Specifically, based on the independent time system in step S1, the satellite coordinates in three-dimensional space in step S4, and the Earth's rotation model in step S5, and driven by the system running time, update the Earth's rotation angle and the positions of all satellites in real time. Add a time acceleration slider, as well as start, pause, and reset functions, and draw the corresponding orbital path for each satellite, ultimately displaying the mega-constellation network in low Earth orbit.
[0076] The following example illustrates a spatiotemporal consistency control method applicable to a low-Earth orbit (LEO) mega-constellation visualization system provided by this invention. This embodiment describes a spatiotemporal consistency control method applicable to the mechanism layer calculation within a LEO mega-constellation visualization system. In this example, the calculation of two satellites, STARLINK-1007 and STARLINK-1008, is used. Under an independent time system, after time alignment, the spatial positions of these two satellites at 15:45:50.460 (UTCG) on February 27, 2023, are calculated, and after transformation in three-dimensional world space, the final position is confirmed.
[0077] 1. Based on the user interface, obtain the time acceleration factor δ at this moment. Assuming the system has just started, t0 = 0. Then, using Time.deltaTime to obtain the time difference Δτ between the current frame and the previous frame in the 3D programming platform, calculate the accelerated time increment for the current frame.
[0078]
[0079] Where t is the system time of the current frame after acceleration, t0 is the system time before the current frame, δ is the time acceleration coefficient, and Δτ is the time interval between the current frame and the previous frame. If δ = 50 and Δτ = 0.00452, then...
[0080] t=t0+δ*Δτ=50*0.00452=0.226
[0081]
[0082]
[0083] Note that Δτ is related to computer performance; the higher the computer performance, the smaller the value of Δτ.
[0084] 2. Obtain the TLE data of the two satellites STARLINK-1007 and STARLINK-1008, and based on the recording epoch time of each satellite, determine the starting operating time reference according to the time alignment function, and calculate the time distance between the satellite and the operating time reference;
[0085] First, obtain the TLE data for these two satellites from the website www.celestrak.org:
[0086] STARLINK-1007
[0087] 1 44713U 19074A 23058.65683403.00040542 00000+0 27217-2 0 9998 2 44713 53.0521 111.7933 0001686 84.7611 275.3570 15.06445509182212
[0089] STARLINK-1008
[0090] 1 44714U 19074B 23058.63565621.00031123 00000+0 20946-2 0 9995 2 44714 53.0538 111.8896 0001266 96.9584 263.1549 15.06479519182217
[0092] After obtaining the recording epoch times of the two satellites, STARLINK-1007 and STARLINK-1008, the time distances between STARLINK-1007 and STARLINK-1008 and the operational time reference can be obtained using the following conversion formula:
[0093] e = max(e star_1007 ,e star_1008 )
[0094] Δt i =ee i
[0095] Where e is the starting running time, e star_1007 e star_1008 Δt represents the epoch times of the two satellites, STARLINK-1007 and STARLINK-1008. i Let e be the time distance between satellite i and the start time of its operation. i Let be the epoch time of satellite i.
[0096] parameter unit Parameter value <![CDATA[STARLINK-1007 Record Epoch Time e star_1007 > UTCG February 27, 2023, 15:45:50.460 <![CDATA[STARLINK-1008 Record Epoch Time e star_1008 > UTCG February 27, 2023, 15:15:20.697 Start running time e UTCG February 27, 2023, 15:45:50.460 STARLINK-1007 time difference with reference Δt s 0 STARLINK-1008 time difference with reference Δt s 1829.763
[0097] 3. Using the SGP4 orbit prediction model, calculate the rectangular coordinates of these two satellites in the J2000 coordinate system at 15:45:50.460 (UTCG) on February 27, 2022:
[0098] J2000_x / km J2000_y / km J2000_z / km STARTLINK_1007 -2571.332 6430.975 0 STARTLINK_1008 -2410.135 -4121.246 5006.628
[0099] 4. Based on the coordinates of the two satellites in the J2000 coordinate system, calculate the satellites' latitude, longitude, and altitude in the latitude-longitude-height coordinate system using the following conversion formula.
[0100]
[0101]
[0102] Where λ is the satellite longitude, denoted as satellite latitude, h as satellite altitude, N as radius of curvature of the reference ellipsoid, e as eccentricity of the ellipsoid, and a as major radius of the ellipsoid.
[0103] latitude / deg Longitude / deg ground clearance / km STARTLINK_1007 0.000 78.112 547.842 STARTLINK_1008 46.538 -154.000 551.160
[0104] Based on the latitude, longitude, and altitude coordinates of the STARLINK-1007 satellite, the corresponding latitude and longitude relationship is established within the 3D programming platform. Then, through global scaling, the satellite's spatial rectangular coordinates in the current 3D space are obtained, as shown in the following formula:
[0105]
[0106] Where R is the average radius of the Earth, with a value of 6371.393 km, h is the satellite's altitude above the Earth, and μ is the system's global scaling factor, with a value of 100, representing that 1 unit in three-dimensional space is equivalent to 100 km in the real world. Substituting these values into the above formula, we can obtain:
[0107]
[0108] Based on the spatial rectangular coordinates (x, y, z) of the STARLINK-1007 satellite in the current three-dimensional space, the parent-child relationship between the Earth and the satellite is established. To eliminate the interference of Earth's rotation, the transformation from the three-dimensional spatial coordinate system to the local coordinate system needs to be completed. The calculation formula is as follows:
[0109]
[0110] Where (x) ′ y ′ , z ′ (x0, y0, z0) are the transformed local coordinates, and (x0, y0, z0) are the spatial coordinates of the Earth, the parent object. Since the Earth is located at the center of three-dimensional space, its coordinates are (0, 0, 0). x It is the scale of the parent object's x-axis, s y It is the scale of the parent object's y-axis, s z It is the scale of the parent object's z-axis, s x s y s z Their values are all 127.43. Substituting them into the above formula, we get:
[0111]
[0112] The process of solving the local coordinate system in three-dimensional space for the STARLINK-1008 satellite is the same as the process described above, and will not be repeated here.
[0113] 5. Based on the Earth's rotation period, simulate the Earth's rotation and perform global scaling in three-dimensional space according to a certain ratio. The formula for the Earth's angular velocity is as follows:
[0114]
[0115] Where sec is the total number of seconds in a day, and then based on the system time t, the angle through which the Earth rotates can be obtained as θ = ωt.
[0116] 6. Based on the independent time system in step 1, the starting time reference in step 2, the local coordinates of the satellites in three-dimensional space in step 4, and the Earth rotation model in step 5, the Earth rotation angle and the positions of all satellites are updated in real time, driven by the system running time. A time acceleration slider is added, as well as start, pause, and reset functions. The corresponding orbital path is drawn for each satellite, and finally, a low-Earth orbit mega-constellation network is displayed.
[0117] By repeating the above steps, the position of any satellite in three-dimensional space can be calculated in real time, and eventually a large low-Earth orbit constellation network can be obtained.
[0118] This invention provides a spatiotemporal consistency control method applicable to low-Earth orbit (LEO) mega-constellation visualization systems. It addresses issues such as the lack of common coordinate system transformations in the physical world and the lack of object alignment operations at different times in visualization 3D programming platforms. Compared to traditional visualization simulation techniques, this method offers significant improvements in satellite constellation scale, model construction time, and visualization mechanism layer computation, providing reliable computational and model construction data support for satellite network visualization simulation. The mathematical model used in this invention has a computational speed dependent on host configuration, is not limited or affected by software, and can be modified according to business scenarios, even allowing for the addition of more consideration formulas, thus offering high flexibility. This spatiotemporal consistency control method for LEO mega-constellation visualization systems achieves higher accuracy in motion calculations at the mechanism layer, resulting in better visualization effects and consistency with real-world objects.
[0119] The preferred embodiments of the present invention have been described in detail above. It should be understood that those skilled in the art can make numerous modifications and variations based on the concept of the present invention without creative effort. Therefore, all technical solutions that can be obtained by those skilled in the art based on the concept of the present invention through logical analysis, reasoning, or limited experimentation on the basis of existing technology should be within the scope of protection defined by the claims.
Claims
1. A spatiotemporal consistency control method applicable to low-Earth orbit mega-constellation visualization systems, characterized in that, Includes the following steps: On a visual 3D programming platform, an independent time system is established based on a time acceleration factor; Specifically, the following steps are included: The time acceleration factor is obtained based on the user interface. Its value ranges from 1 to 500; Then, based on the time between the current frame and the previous frame... Calculate the accelerated time increment for the current frame using the following conversion formula: ， Where t is the system time of the current frame after acceleration. The system time prior to the current frame. This is the time acceleration factor. The time between the current frame and the previous frame; Obtain the TLE ephemeris data of all satellites under a certain constellation, determine the starting operating time reference based on the time alignment function, and calculate the time distance between the satellite and the operating time reference; Based on TLE ephemeris data, record epoch time, and satellite orbit time, the SGP4 orbit prediction model is used to calculate the spatial position of each satellite in real time. Establish the latitude and longitude relationships within the visual 3D programming platform, perform coordinate system transformation, and calculate the 3D world space coordinates of each satellite; specific steps include: Based on the satellite's spatial coordinates in the J2000 coordinate system, we obtain the satellite's longitude, latitude, and altitude in the latitude-longitude coordinate system. Based on the concept of latitude and longitude, the latitude and longitude relationship within the 3D programming platform is established, and the current spatial rectangular coordinates of the satellite are obtained through the global scaling factor; By establishing the parent-child relationship between Earth and the satellite, eliminating the interference of Earth's rotation, completing the local coordinate system transformation, and calculating the satellite's final coordinates at this time; Based on the Earth's rotation period, the Earth's rotation is simulated and globally scaled according to a certain ratio; Based on the operating time, the Earth's rotation angle and the positions of all satellites are updated in real time to showcase the massive low-Earth orbit constellation network.
2. The spatiotemporal consistency control method applicable to a low-Earth orbit mega-constellation visualization system as described in claim 1, characterized in that, To obtain the TLE ephemeris data of all satellites in a given constellation, and determine the starting operating time reference based on the time alignment function, the specific steps include: Obtain the ephemeris data of all satellites to get the record epoch time for each satellite; Based on the time alignment function, the starting time of operation is obtained, and the time distance between each satellite and the starting time is calculated.
3. The spatiotemporal consistency control method applicable to a low-Earth orbit mega-constellation visualization system as described in claim 2, characterized in that, Based on the time alignment function, the starting operation time is obtained, and the time distance between each satellite and the operation time is calculated. The calculation formula is as follows: ， ， in The start time of operation. , , For the epoch times of different satellites, The time distance between satellite i and the start time of operation. Let be the epoch time of satellite i.
4. The spatiotemporal consistency control method applicable to a low-Earth orbit mega-constellation visualization system as described in claim 1, characterized in that, Based on the satellite's spatial coordinates in the J2000 coordinate system, the satellite's longitude, latitude, and altitude in the latitude-longitude-height coordinate system are obtained. The conversion formula is as follows: ， ， in, For satellite longitude, For satellite latitude, Where N is the satellite altitude and N is the radius of curvature of the reference ellipsoid. Let be the eccentricity of the ellipsoid, and a be the major radius of the ellipsoid.
5. The spatiotemporal consistency control method applicable to a low-Earth orbit mega-constellation visualization system as described in claim 4, characterized in that, Establish the latitude and longitude relationships within the 3D programming platform, and calculate the current spatial rectangular coordinates of the satellite using a global scaling factor. The calculation formula is as follows: ， Where R is the Earth's average radius, which is 6371.393 km. The satellite's altitude above the ground. This is the system-wide scaling factor, with a value of 100.
6. The spatiotemporal consistency control method applicable to a low-Earth orbit mega-constellation visualization system as described in claim 5, characterized in that, Based on the established parent-child relationship between Earth and the satellite, a local coordinate system transformation is performed, and the satellite's final coordinates at this point are calculated using the following formula: ， in( ) are the transformed local coordinates, ( , , () are the spatial coordinates of the Earth, which serves as the parent object. It is the scale of the parent object's x-axis. It is the scale of the parent object's y-axis. It is the scale of the parent object's z-axis.
7. The spatiotemporal consistency control method applicable to a low-Earth orbit mega-constellation visualization system as described in claim 1, characterized in that, Based on the Earth's rotation period, the Earth's rotation is simulated and globally scaled according to a certain ratio. The formula for calculating the angle through which the Earth rotates is as follows: ， in, For the angle of rotation, The total number of seconds in a day. System time.