Method and apparatus for mega-constellation transit tracking, storage medium and electronic device

Abstract

The application provides a mega-constellation transit tracking method and device, a storage medium and electronic equipment, comprising: generating a transit display map of a mega-constellation; based on ground station information and basic information of the mega-constellation, marking the satellite track of the observable mega-constellation in the observation period in the transit display map; based on priority evaluation rules, generating a satellite observation list with priority; according to the priority in the satellite observation list, allocating resources for each mega-constellation in the satellite observation list to generate a satellite tracking task list corresponding to the observation period. By applying the method provided by the application, the track of the mega-constellation can be observed intuitively by generating a transit display map, and the user's decision can be determined in a man-machine interactive manner, and reasonable resource planning is performed for each mega-constellation in the observation period in combination with the user's decision and the priority evaluation rules in the system, so that optimal tracking is realized under limited resources.

Description

Technical Field

[0001] This invention relates to the field of satellite tracking technology, and in particular to a method, apparatus, storage medium, and electronic device for tracking the transit of a giant satellite constellation. Background Technology

[0002] With the dense deployment of giant low-Earth orbit satellite constellations (such as Starlink and OneWeb), a single receiving station needs to cope with the complex scenario of multiple satellites passing overhead at high frequency. How to make efficient use of limited ground receiving resources to track giant satellite constellations and formulate the optimal tracking plan based on the importance and urgency of the target is one of the key issues that need to be addressed in the tracking and receiving of giant satellite constellations.

[0003] In practical applications, there are bottlenecks such as insufficient real-time forecast processing capabilities for giant constellations and inefficient multi-station collaborative tracking. Existing forecast scheduling systems suffer from severe computational inefficiency when dealing with real-time orbit extrapolation of tens of thousands of satellites, and are unable to complete continuous forecasts for the next few hours within an acceptable timeframe. At the same time, multi-station collaborative scheduling relies on manual methods or simple rules, resulting in rigid resource allocation, low utilization, and an inability to achieve globally optimal scheduling based on the importance and urgency of the targets. Summary of the Invention

[0004] In view of this, the present invention provides a method, apparatus, storage medium, and electronic device for tracking the transit of giant satellite constellations. Through this method, the trajectory of giant satellites can be intuitively observed by generating a transit display map. The user's decision can be determined through human-computer interaction. Combining the user's decision and the priority evaluation rules within the system, reasonable resource planning can be carried out for each giant satellite during the observation period to achieve optimal tracking with limited resources.

[0005] A method for tracking the transit of a giant satellite constellation, the method comprising:

[0006] Generate a transit image of a giant satellite constellation, the transit image containing the satellite trajectory and basic information of the giant satellite, the satellite trajectory including two-dimensional trajectory and three-dimensional trajectory;

[0007] Based on ground station information and various basic information, the satellite trajectories of observable giant satellites during the observation period are marked on the transit display map;

[0008] Based on preset priority evaluation rules, a priority-based satellite observation list is generated, which includes each giant satellite with marked satellite trajectory and its corresponding priority.

[0009] Based on the priority in the satellite observation list, resources are allocated to each mega-satellite in the satellite observation list to generate a list of satellite tracking tasks corresponding to the observation period.

[0010] Optionally, the method described above includes generating a transit image of a giant satellite constellation, which includes:

[0011] Launch the satellite management interface corresponding to the pre-configured giant satellite constellation;

[0012] The system retrieves satellite ephemeris data from multiple mega-satellites online, and receives satellite ephemeris data from at least one mega-satellite input by the user through the satellite management interface. Each satellite ephemeris is stored in a pre-defined ephemeris database.

[0013] Based on the saved satellite ephemeris, a transit map of a giant satellite constellation is generated.

[0014] Optionally, the method described above includes generating a transit image of a giant satellite constellation, which includes:

[0015] Obtain TLE data for each megasatellite in a megasatellite constellation;

[0016] The SGP4 model was used to calculate the TLE data to obtain the set of positions of each giant satellite in the geocentric-geofixed coordinate system during the observation period. The set of positions is the geocentric-geofixed coordinate of the giant satellite during the observation period.

[0017] Based on the various location sets, a transit map of a giant satellite constellation is generated.

[0018] Optionally, the method described above, which involves marking the satellite trajectory of observable megasatellites during the observation period in the transit display map based on ground station information and various basic information, includes:

[0019] Obtain the minimum receiving elevation angle of the ground station, the coordinates of the ground station, and the geocentric and geofixed coordinates of each giant satellite during the observation period;

[0020] Based on the minimum receiving elevation angle, ground station coordinates, and geocentric and geofixed coordinates of the giant satellite, the set of observable satellites in the giant satellite constellation during the observation period is determined, and the set of observable satellites is the giant satellites that can be observed during the observation period.

[0021] Mark the satellite trajectories of giant satellites in the observable satellite array on the transit display map.

[0022] Optionally, in the above method, generating a priority-based satellite observation list based on preset priority evaluation rules includes:

[0023] Determine whether the user performs a selection operation on any giant satellite with marked satellite tracks through the transit display map;

[0024] If the user does not select any giant satellite with marked satellite tracks through the transit display map, a priority list of satellite observations will be generated according to the priority evaluation rules.

[0025] If a user selects any giant satellite with marked satellite tracks through the transit display map, an operation list is obtained, and a priority list of satellite observations is generated based on the operation list and priority evaluation rules.

[0026] Optionally, in the above method, the allocation of resources to each megasatellite in the satellite observation list according to its priority includes:

[0027] Acquire antenna resources of the ground station, including antenna status and antenna capability parameters;

[0028] In descending order of priority, antennas matching the antenna resources of each megasatellite in the satellite observation list are searched in turn.

[0029] When any giant satellite matches the antenna resources of any antenna, the giant satellite is associated with the antenna and the antenna is locked; the locked antenna cannot be associated with other giant satellites.

[0030] Optionally, the above method may further include:

[0031] When any giant satellite is mismatched with the antenna resources of all antennas, a prompt message will be issued through the display interface showing the transit map.

[0032] A giant satellite constellation transit tracking device, the method comprising:

[0033] The image generation module is used to generate a transit image of a giant satellite constellation. The transit image includes the satellite trajectory and basic information of the giant satellite, and the satellite trajectory includes two-dimensional trajectory and three-dimensional trajectory.

[0034] The marking module is used to mark the satellite trajectory of observable megasatellites during the observation period in the transit display map based on ground station information and various basic information.

[0035] The list generation module is used to generate a priority list of satellite observations based on preset priority evaluation rules. The list of satellite observations includes each giant satellite with marked satellite trajectory and its corresponding priority.

[0036] The resource allocation module is used to allocate resources to each mega-satellite in the satellite observation list according to the priority in the satellite observation list, so as to generate a list of satellite tracking tasks corresponding to the observation period.

[0037] An electronic device, comprising:

[0038] Memory, used to store instructions;

[0039] A processor is configured to operate according to instructions to execute memory, and one or more instructions, wherein one or more instructions are stored in the memory and configured to be executed by one or more processors, as described above in the giant satellite constellation transit tracking method.

[0040] Compared with the prior art, the present invention has the following advantages:

[0041] This invention provides a method for tracking the transit of a giant satellite constellation, comprising: generating a transit map of the giant satellite constellation, the transit map including the satellite trajectories and basic information of the giant satellites, the satellite trajectories including two-dimensional and three-dimensional trajectories; marking the observable satellite trajectories of the giant satellites within the observation period on the transit map based on ground station information and various basic information; generating a priority-based satellite observation list based on preset priority evaluation rules, the satellite observation list including each giant satellite with marked satellite trajectories and its corresponding priority; and allocating resources to each giant satellite in the satellite observation list according to the priority in the satellite observation list to generate a satellite tracking task list corresponding to the observation period. By applying the method provided by this invention, the trajectories of giant satellites can be intuitively observed through the generation of the transit map, and user decisions can be determined through human-computer interaction. Combining user decisions and the system's internal priority evaluation rules, resource planning can be rationally performed for each giant satellite within the observation period, achieving optimal tracking with limited resources. Attached Figure Description

[0042] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0043] Figure 1 A flowchart illustrating a method for tracking the transit of a giant satellite constellation, as provided in an embodiment of the present invention;

[0044] Figure 2 This is a structural diagram of a giant satellite constellation transit tracking device provided in an embodiment of the present invention;

[0045] Figure 3 This is a schematic diagram of an electronic device structure provided in an embodiment of the present invention. Detailed Implementation

[0046] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0047] In this application, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. The terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0048] This invention can be used in a wide variety of general-purpose or special-purpose computing environments or configurations. For example: personal computers, server computers, handheld or portable devices, tablet devices, multiprocessor devices, distributed computing environments including any of the above devices, etc.

[0049] This invention provides a method for tracking the transit of a giant satellite constellation. The method is applied to a processor, and the flowchart of the method is shown below. Figure 1 As shown, it specifically includes:

[0050] S1: Generate a three-dimensional trajectory map of the giant satellite constellation during the observation period. The three-dimensional trajectory map contains the three-dimensional satellite trajectories of multiple giant satellites and the observation information of each three-dimensional satellite trajectory.

[0051] S2: Based on the observation information and satellite information of each mega-satellite, select the key observation satellites from the mega-satellite constellation during the observation period;

[0052] S3: Obtain equipment information of available equipment at the ground station within the target time period;

[0053] S4: Based on the information from each device and the observation information from each key observation satellite, set the tracking task for each key observation satellite within the target time period.

[0054] Based on the above steps S1-S4, the following specific explanations are provided:

[0055] S1: A transit view of the generated giant satellite constellation.

[0056] The transit map includes basic information, a two-dimensional trajectory map, and a three-dimensional trajectory animation for each giant satellite in the giant satellite constellation. The two-dimensional transit map displays a ground projection of the giant satellite's transit trajectory, and the three-dimensional transit map displays the giant satellite's three-dimensional motion trajectory. The transit map is displayed on a pre-set display screen, allowing users to observe the current position of each giant satellite in real time.

[0057] The basic information of a megasatellite includes satellite ephemeris, TLE (Two-Line Element Set) data, satellite application type, etc. TLE data includes information such as satellite row identifier, satellite number, orbital inclination, orbit type, and orbital revolution number.

[0058] In one optional implementation, the transit image can be generated by calculating coordinates using the ephemeris data of multiple megasatellites from a database. This involves: activating a pre-configured satellite management interface corresponding to the megasatellite constellation; retrieving the ephemeris data of multiple megasatellites online; and receiving the ephemeris data of at least one megasatellite input by the user through the satellite management interface. All satellite ephemeris data are stored in a pre-configured database. Based on the stored ephemeris data, a transit image of the megasatellite constellation is generated. The ephemeris data of each satellite in the database can be obtained from publicly available online sources or manually input by the user through the satellite management interface. Therefore, when generating the transit image, the satellite management interface is activated first, and simultaneously, a web crawler is launched. The web crawler retrieves the ephemeris data of the megasatellites online, while the user inputs the ephemeris data through the satellite management interface. When the satellite ephemeris obtained by the web crawler and the satellite ephemeris input by the user belong to the same megasatellite, the ephemeris obtained by the web crawler is discarded. When both obtained ephemeris belong to the same megasatellite and there are differences between them, the user is prompted about the differences through the satellite management interface, and the correct ephemeris for the megasatellite is retained based on the user's selection or correction. After saving the satellite ephemeris to the ephemeris database, a transit map of the megasatellite constellation is generated according to the user's generation instructions.

[0059] In one optional implementation, the process of generating a transit image of a giant satellite constellation may be as follows: acquiring the TLE (Two-Line Element Set) data of each giant satellite in the giant satellite constellation; acquiring the TLE data of each giant satellite in the giant satellite constellation; applying the SGP4 model to calculate the TLE data to obtain the position set of each giant satellite in the geocentric-geofixed coordinate system during the observation period, wherein the position set is the geocentric-geofixed coordinate of the giant satellite during the observation period; and generating a transit image of the giant satellite constellation based on each position set.

[0060] Based on the SGP4 model, the process of calculating position and velocity in the ECI coordinate system (Earth-Centered Inertial) and performing coordinate system transformation is as follows: The target satellite constellation is traversed, and ephemeris extrapolation is performed based on TLE data to obtain the ECI parameters of all target satellites within a specified time period (e.g., 12:00:00~12:30:00). These parameters mainly include the satellites' positions (x, y, z) and velocities (Vx, Vy, Vz). For the specific process of obtaining the ECI parameters, refer to steps 1) to 6 below.

[0061] 1) Average orbital feature update: Update the average motion based on the time difference ∆t.

[0062]

[0063] in, The average initial motion is located at positions 53-56 in the second row of the two-row root numbers; The first derivative of the mean motion is located in the second row of the two-row roots, positions 34-43. The time difference with the ephemeris time, in seconds; the first line of the two rows of roots, 19-32, represents the ephemeris time in UTC, for example: 24358.50950042, corresponding to the 358th day of 2024, i.e., (2024-12-23 12:13:40 UTC). Assuming the current time is 2024-12-23 12:40:00 UTC, we can calculate... =1579.

[0064] 2) Solving Kepler's equations, and finding the deviated anterior angle E using the mean anterior angle M:

[0065]

[0066] It is a near-point angle, located in the second row of the two-row root numbers, positions 41-50; The average motion parameters at the current moment are calculated from step 1) above;

[0067] Iterative solution: After convergence, we obtain E, where, The eccentricity of the orbit is located in the second row of the two-row root numbers, positions 27-33.

[0068] 3) Calculation of true nearest angle:

[0069]

[0070]

[0071] in, The angle is the near-point angle, which is obtained by solving step 2) above.

[0072] 4) Calculation of orbital position (elliptical orbit):

[0073] First, solve for the semi-major axis ( ):

[0074]

[0075]

[0076] is the Earth's gravitational constant.

[0077] Secondly, solve for the distance between the Earth's centers ( ):

[0078]

[0079] Relative position of the orbital ellipse:

[0080]

[0081] 5) Velocity component calculation

[0082] Radial velocity:

[0083]

[0084] Lateral velocity:

[0085]

[0086] in, Specific angular momentum; The gravitational constant of Earth; The orbital eccentricity is located in the second row of two roots, positions 27-33. True near point angle

[0087] 6) Coordinate system transformation (ECI to ECEF): The geocentric inertial coordinate system (ECI) is transformed into the geocentric geofixed coordinate system (ECEF) using a rotation matrix.

[0088]

[0089] The geocentric coordinate system obtained by the above coordinate system transformation can be a rotation matrix around the Z-axis.

[0090] It should be noted that the two lines of root data consist of two lines of ASCII text, containing the key roots of the satellite orbit, epoch time, and orbital perturbation-related correction parameters. These can be directly input into the orbit prediction model to calculate the satellite's position and velocity at any given time.

[0091] In this invention, according to the process of steps 1) to 6) above, the geocentric coordinate system of the giant satellite in each time period is calculated, the geocentric coordinate system of each time period is input into a pre-set three-dimensional engine (e.g., CesiumJS geographic visualization engine), the three-dimensional trajectory animation is generated by the three-dimensional engine, and the three-dimensional trajectory in the three-dimensional trajectory animation is projected onto two-dimensional coordinates to generate a two-dimensional trajectory map.

[0092] After obtaining the three-dimensional trajectory animation and the two-dimensional trajectory, the three-dimensional trajectory animation and the two-dimensional trajectory are displayed in the corresponding partition according to the pre-set display partition. The partition contains the coordinates (i.e., two-dimensional coordinates and three-dimensional coordinates) of each giant satellite and the basic information of the satellite.

[0093] Optionally, in the trajectory display diagram of the present invention, the basic information of each giant satellite is displayed in the form of a pop-up window. When the user triggers any trajectory in the two-dimensional trajectory diagram or any dynamic trajectory in the three-dimensional trajectory dynamic diagram through a control device (e.g., mouse) or touch, the basic information of the giant satellite to which the trajectory belongs is displayed in the form of a pop-up window next to the triggered trajectory.

[0094] S2: Based on ground station information and various basic information, mark the satellite trajectory of observable giant satellites during the observation period in the transit display map.

[0095] Ground station information includes ground station coordinates and minimum receiving elevation angle. Based on the ground station information and basic information about each megasatellite, the satellite trajectories of megasatellites that can be observed during the observation period are marked on the overflight display map, allowing users to visually identify the megasatellites that can be observed during the observation period. Marked satellite trajectories can be displayed using highlighted lines, while unmarked satellite trajectories are displayed using grayscale lines. Observable satellites refer to those whose signals can be received by the ground station antenna.

[0096] In this invention, the process of marking the satellite trajectories of observable mega-satellites during the observation period is as follows: obtaining the minimum receiving elevation angle of the ground station, the ground station coordinates, and the geocentric and geofixed coordinates of each mega-satellite during the observation period; based on the minimum receiving elevation angle, the ground station coordinates, and the geocentric and geofixed coordinates of the mega-satellites, determining the set of observable satellites in the mega-satellite constellation during the observation period, wherein the set of observable satellites is the mega-satellite observable during the observation period; and marking the satellite trajectories of the mega-satellites in the observable satellite set in the transit display diagram.

[0097] Specifically, the ground station coordinates are latitude and longitude coordinates. Since they need to be converted to the Earth-centered Earth-fixed (ECEF) coordinate system to obtain the ECEF coordinates of the ground station, the formula for converting latitude and longitude coordinates to ECEF is as follows:

[0098]

[0099] in, The radius of curvature of the Earth; This is the Earth's semi-major axis; The square of the first eccentricity of the Earth; This refers to the altitude of the ground station. Longitude of the ground station; This refers to the latitude of the ground station.

[0100] After converting the latitude and longitude coordinates of the ground station into ECEF coordinates, it is necessary to select satellites that can be observed from the giant satellite constellation based on the ground station coordinates, the minimum elevation angle of the ground station, and the ECEF coordinates of the giant satellite.

[0101] For a satellite to be able to be observed, its azimuth and elevation angles must be greater than the minimum elevation angle of the ground station. Only under these conditions can the ground station receive the satellite's signal.

[0102] The formula for calculating the azimuth of a giant satellite is as follows:

[0103] The azimuth angle is the angle rotated clockwise from true north to the target direction:

[0104]

[0105] in, Local horizontal coordinate system The middle finger points to the component pointing due east. Local horizontal coordinate system The component pointing north; It is obtained from the following formula:

[0106]

[0107]

[0108] The ECEF coordinates of the satellite; For the ECEF coordinates of the ground station, It is a rotation matrix.

[0109] The formula for calculating the elevation angle of a giant satellite is as follows:

[0110]

[0111] in, Local horizontal coordinate system The middle finger points to the component in the vertical direction.

[0112] After calculating the azimuth and elevation angles of the giant satellite, the azimuth and elevation angles are compared with the minimum receiving elevation angle of the ground station. If the azimuth and elevation angles are greater than the minimum receiving elevation angle of the ground station, the giant satellite is an observable satellite, and its trajectory is marked on the transit display map.

[0113] In this invention, by marking observable mega-satellites, users can intuitively identify the mega-satellites whose signals can be received by ground stations during the observation period. Based on the marked satellite trajectories, users can select key satellites to be observed, avoiding the omission of key satellites due to limited ground station resources.

[0114] S3: Generate a priority list of satellite observations based on preset priority evaluation rules.

[0115] The satellite observation list includes each giant satellite with its track marked and its corresponding priority.

[0116] It should be noted that after marking satellite tracks, users can choose to highlight mega-satellites requiring focused observation or remain silent. Before the observation period begins, the transit map is updated in real-time to determine whether the user has selected any mega-satellite with marked tracks. If so, the mega-satellite with the selected track is designated as the one requiring focused observation, and its priority is updated to increase its priority. Each mega-satellite can have its initial priority set according to a preset priority evaluation rule. This rule is based on satellite type or application, for example, prioritizing satellites by application, with priority from highest to lowest as follows: military reconnaissance satellites, disaster monitoring satellites, scientific research satellites, and general communication satellites.

[0117] In this invention, a priority-based satellite observation list is generated based on a preset priority evaluation rule, including: determining whether the user performs a selection operation on any giant satellite with marked satellite trajectories through the transit view; if the user does not perform a selection operation on any giant satellite with marked satellite trajectories through the transit view, a priority-based satellite observation list is generated according to the priority evaluation rule; if the user performs a selection operation on any giant satellite with marked satellite trajectories through the transit view, an operation list is obtained, and a priority-based satellite observation list is generated based on the operation list and the priority evaluation rule.

[0118] In this embodiment of the invention, existing mega-satellites can be applied in multiple fields. To avoid the failure of observation of satellites that need to be observed during the observation period due to limited ground station resources, it is necessary to prioritize each mega-satellite. The priority ranking method according to the priority evaluation rules can be set to the default priority. If a mega-satellite with a lower priority needs to be observed during the observation period, the user can select the satellite trajectory of the mega-satellite through the transit display map to trigger the corresponding selection operation, thereby updating the priority of each mega-satellite and generating a priority satellite observation list to avoid missing key satellites that need to be observed due to ground station resource limitations.

[0119] S4: Allocate resources to each mega-satellite in the satellite observation list according to the priority in the satellite observation list, so as to generate a list of satellite tracking tasks corresponding to the observation period.

[0120] Specifically, according to the priority in the satellite observation list, resources are allocated to each mega-satellite in the list, including: acquiring antenna resources of ground stations, which include antenna status and antenna capability parameters; searching for antennas with matching antenna resources for each mega-satellite in the list in descending order of priority; when any mega-satellite matches the antenna resources of any antenna, the mega-satellite is associated with that antenna and the antenna is locked; the locked antenna cannot be associated with other mega-satellites; when any mega-satellite does not match the antenna resources of any antenna, a prompt message is issued through the display interface of the transit map.

[0121] In this invention, the sorted list of satellite observations is traversed in priority order, and the following sub-steps are performed for mega-satellites:

[0122] a. Resource search: Search for antennas that meet all of the following conditions in the set of all antenna resources of the ground station: 1) The antenna capability matches the coverage requirements such as frequency band and polarization; 2) The antenna is not locked during the observation period.

[0123] b. Decision and Recording: If found: Associate the megasatellite with the antenna, lock the antenna during the observation period, and mark it as occupied. This association is recorded in the final satellite tracking task list. If not found (i.e., all available antennas are occupied by higher priority tasks during the required time period): Trigger the "Conflict Resolution" process. After the output loop ends, output all successfully assigned megasatellites and their corresponding antennas and observation periods, forming a conflict-free satellite tracking task list.

[0124] The "conflict adjudication" process is as follows:

[0125] a. Conflict identification and assessment: Traverse all antennas, identify those that were occupied before or during the observation period, and find other mega-satellites that occupy those antennas and have a lower priority than the current mega-satellite.

[0126] b. Forcibly unbind the low-priority mega-satellite from its original antenna, releasing the time slot it occupies. Then, allocate the antenna to the current mega-satellite and lock the resources.

[0127] c. This strategy involves rescheduling previously forcibly deactivated, low-priority mega-satellites. The system re-executes the resource search process for these low-priority mega-satellites:

[0128] The first approach is to allocate a new antenna to the low-priority megasatellite if available resources on other antennas can be found that meet the observation time slots and capacity requirements of the megasatellite.

[0129] The second method: If, after searching again using the first method, no available resources can be found for the low-priority mega-satellite, the system will mark it as canceled due to resource conflict and remove it from the current plan. The reason for cancellation can be recorded in the log for analysis.

[0130] The method provided in this invention can dynamically adjust satellite resource allocation and fault tolerance. It simulates the decision-making process of a human scheduler—"ensuring priority while considering general tasks"—but executes automatically at millisecond speeds. It significantly improves the success rate of high-value missions and the overall utilization efficiency of system resources, representing a key algorithmic innovation in solving the core problem of "achieving optimal tracking with limited resources."

[0131] Based on the method provided in the embodiments of steps S1-S4 of the present invention, the present invention has the following specific implementation methods for resource allocation and tracking of satellites passing over at different times:

[0132] 1) Based on a visual management interface, the latest ephemeris information of mega-constellations is imported in real time to form a mega-constellation ephemeris database. Specifically, a visual satellite management interface is provided, which can realize the import, online update, and editing of ephemeris data for mega-constellations (StarLink, OneWeb, etc.); a local database is provided to realize the storage, update, and query functions of ephemeris files.

[0133] 2) Based on the SGP4 model, calculate the position and velocity in the ECI coordinate system, perform coordinate system transformation, and obtain the approximate position and velocity of the target satellite group over a specified time period. This step mainly calculates the satellite positions (…). ) and speed ( , This is used to calculate the antenna's direction and further determine which satellites can be tracked.

[0134] 3) Calculate the observation parameters of the target satellite group at the specified receiving location. The system provides a ground station location setting function, mainly including parameters such as longitude, latitude, and altitude; based on the beam coverage characteristics of different satellite constellations, set the minimum receiving elevation angle of the receiving station, which is one of the important conditions for determining satellite visibility; based on the ground station location and the configured minimum receiving elevation angle, calculate the list of visible satellites in the future fixed time window (observation period), and generate visible satellite information and store it in the database.

[0135] 4) Generate transit alerts for key targets based on the list of key monitored satellites. Provide a visual management interface to configure and manage key satellite targets and priority parameters; perform important target matching and filtering based on transit time windows to generate tracking priority plans and alert information for receiving satellites.

[0136] 5) Generate satellite tracking requirements based on available receiving resources and target importance. First, screen available receiving resources of designated ground stations and determine their operational status, working status, etc.; then access the priority information of important targets and match them with available antenna resources according to the current antenna mission status and antenna receiving capabilities (mainly including receiving frequency band and feed polarization) to generate resource matching information.

[0137] 6) Generate an automatic tracking prediction strategy for each receiving antenna resource type. Based on priority, generate a tracking strategy for each receiving antenna, mainly including parameters such as antenna start tracking time, end time, and tracking point.

[0138] Based on the method provided by this invention, the ability to continuously forecast the transit of giant satellite constellations is realized. This solves the problem of optimizing the tracking strategy for high-frequency transit satellites of giant constellations under limited resources at ground stations, thereby maximizing the continuous tracking and reception capability of giant constellation satellites.

[0139] and Figure 1 Corresponding to the method described above, embodiments of the present invention also provide a giant satellite constellation transit tracking device for tracking... Figure 1 In the specific implementation of the method, the giant satellite constellation transit tracking device provided in this embodiment of the invention is applied to the processor, and its structural schematic diagram is shown below. Figure 2 As shown, it specifically includes:

[0140] The image generation module 201 is used to generate a transit image of a giant satellite constellation. The transit image includes the satellite trajectory and basic information of the giant satellites. The satellite trajectory includes a two-dimensional trajectory and a three-dimensional trajectory.

[0141] The marking module 202 is used to mark the satellite trajectory of observable giant satellites during the observation period in the transit display map based on ground station information and various basic information.

[0142] The list generation module 203 is used to generate a priority-based satellite observation list based on a preset priority evaluation rule. The satellite observation list includes each giant satellite with marked satellite trajectory and its corresponding priority.

[0143] The resource allocation module 204 is used to allocate resources to each mega-satellite in the satellite observation list according to the priority in the satellite observation list, so as to generate a satellite tracking task list corresponding to the observation period.

[0144] In the apparatus provided in this embodiment of the invention, the image generation module 201 generates a transit image of a giant satellite constellation specifically for:

[0145] Launch the satellite management interface corresponding to the pre-set mega-satellite constellation; retrieve the satellite ephemeris of multiple mega-satellites online, and receive the satellite ephemeris of at least one mega-satellite input by the user through the satellite management interface. Each satellite ephemeris is saved in the pre-set ephemeris database; generate a transit display map of the mega-satellite constellation based on the saved satellite ephemeris.

[0146] In the apparatus provided in this embodiment of the invention, the image generation module 201 generates a transit image of a giant satellite constellation, specifically used for:

[0147] Obtain TLE data for each giant satellite in the giant satellite constellation; apply the SGP4 model to calculate the TLE data to obtain the set of positions of each giant satellite in the geocentric-geofixed coordinate system during the observation period, wherein the set of positions is the geocentric-geofixed coordinate of the giant satellite during the observation period; based on each set of positions, generate a transit map of the giant satellite constellation.

[0148] In the apparatus provided in this embodiment of the invention, the marking module 202, based on ground station information and various basic information, marks the satellite trajectory of observable megasatellites during the observation period in the transit display map, specifically for:

[0149] Obtain the minimum receiving elevation angle of the ground station, the coordinates of the ground station, and the geocentric and geofixed coordinates of each giant satellite during the observation period; based on the minimum receiving elevation angle, the coordinates of the ground station, and the geocentric and geofixed coordinates of the giant satellites, determine the set of observable satellites in the giant satellite constellation during the observation period, wherein the set of observable satellites is the giant satellites observable during the observation period; mark the satellite trajectories of the giant satellites in the observable satellite set in the transit display map.

[0150] In the apparatus provided in this embodiment of the invention, the list generation module 203 generates a priority-based satellite observation list based on a preset priority evaluation rule, specifically used for:

[0151] Determine whether the user performed a selection operation on any giant satellite with marked satellite tracks through the transit view; if the user did not perform a selection operation on any giant satellite with marked satellite tracks through the transit view, generate a priority list of satellite observations according to the priority evaluation rules; if the user performed a selection operation on any giant satellite with marked satellite tracks through the transit view, obtain an operation list, and generate a priority list of satellite observations based on the operation list and the priority evaluation rules.

[0152] In the apparatus provided in this embodiment of the invention, the resource allocation module 204 allocates resources to each megasatellite in the satellite observation list according to the priority in the satellite observation list, specifically for:

[0153] The antenna resources of the ground station are acquired, including antenna status and antenna capability parameters. Antennas matching the antenna resources of each megasatellite in the satellite observation list are searched in descending order of priority. When any megasatellite matches the antenna resources of any antenna, the megasatellite is associated with the antenna and the antenna is locked. The locked antenna cannot be associated with other megasatellites.

[0154] In the apparatus provided in this embodiment of the invention, the resource allocation module 204 is further configured to:

[0155] When any giant satellite is mismatched with the antenna resources of all antennas, a prompt message will be issued through the display interface showing the transit map.

[0156] The specific working process of each module in the giant satellite constellation transit tracking device disclosed in the above embodiments of the present invention can be found in the corresponding content of the giant satellite constellation transit tracking method disclosed in the above embodiments of the present invention, and will not be repeated here.

[0157] This invention also provides a storage medium that includes stored instructions, wherein the execution of the instructions controls the device containing the storage medium to perform the aforementioned giant satellite constellation transit tracking method.

[0158] This invention also provides an electronic device, the structural schematic of which is shown below. Figure 3 As shown, it specifically includes: a memory 301 for storing instructions 302; and a processor 303 for performing the following operations according to the instructions:

[0159] Generate a transit image of a giant satellite constellation, the transit image containing the satellite trajectory and basic information of the giant satellite, the satellite trajectory including two-dimensional trajectory and three-dimensional trajectory;

[0160] Based on ground station information and various basic information, the satellite trajectories of observable giant satellites during the observation period are marked on the transit display map;

[0161] Based on preset priority evaluation rules, a priority-based satellite observation list is generated, which includes each giant satellite with marked satellite trajectory and its corresponding priority.

[0162] Based on the priority in the satellite observation list, resources are allocated to each mega-satellite in the satellite observation list to generate a list of satellite tracking tasks corresponding to the observation period.

[0163] The various embodiments in this specification are described in a progressive manner. Similar or identical parts between embodiments can be referred to mutually. Each embodiment focuses on describing the differences from other embodiments. In particular, for system or system embodiments, since they are basically similar to method embodiments, the description is relatively simple, and relevant parts can be referred to the descriptions in the method embodiments. The systems and system embodiments described above are merely illustrative. The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the modules can be selected to achieve the purpose of this embodiment according to actual needs. Those skilled in the art can understand and implement this without creative effort.

[0164] Those skilled in the art will further recognize that the units and algorithm steps of the various examples described in connection with the embodiments disclosed herein can be implemented in electronic hardware, computer software, or a combination of both.

[0165] To clearly illustrate the interchangeability of hardware and software, the components and steps of each example have been generally described in terms of functionality above. Whether these functions are implemented in hardware or software depends on the specific application and design constraints of the technical solution. Those skilled in the art can use different methods to implement the described functions for each specific application, but such implementations should not be considered beyond the scope of this invention.

[0166] The above description of the disclosed embodiments enables those skilled in the art to make or use the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention. Therefore, the invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A method for tracking the transit of a giant satellite constellation, characterized in that, The method includes: Generate a transit image of a giant satellite constellation, the transit image containing the satellite trajectory and basic information of the giant satellite, the satellite trajectory including two-dimensional trajectory and three-dimensional trajectory; Based on ground station information and various basic information, the satellite trajectories of observable giant satellites during the observation period are marked on the transit display map; Based on preset priority evaluation rules, a priority-based satellite observation list is generated, which includes each giant satellite with marked satellite trajectory and its corresponding priority. Based on the priority in the satellite observation list, resources are allocated to each mega-satellite in the satellite observation list to generate a list of satellite tracking tasks corresponding to the observation period; The step of generating a priority-based satellite observation list based on a preset priority evaluation rule includes: determining whether the user performs a selection operation on any giant satellite with marked satellite trajectories through the transit view; if the user does not perform a selection operation on any giant satellite with marked satellite trajectories through the transit view, a priority-based satellite observation list is generated according to the priority evaluation rule; if the user performs a selection operation on any giant satellite with marked satellite trajectories through the transit view, an operation list is obtained, and a priority-based satellite observation list is generated based on the operation list and the priority evaluation rule, wherein the priority evaluation rule sets priorities according to satellite type or satellite application nature. The process of allocating resources to each megasatellite in the satellite observation list according to its priority includes: acquiring antenna resources from ground stations, including antenna status and antenna capability parameters; searching for idle antennas that match the antenna resources of each megasatellite in the satellite observation list in descending order of priority; when an idle antenna resource matches a megasatellite, associating the megasatellite with that antenna and locking the antenna; when no idle antenna resource matches a megasatellite, triggering a conflict resolution process, releasing the antenna resources already allocated to lower-priority megasatellites and reallocating them, wherein locked antennas cannot be associated with other megasatellites.

2. The method according to claim 1, characterized in that, The generated transit image of the giant satellite constellation includes: Launch the satellite management interface corresponding to the pre-configured giant satellite constellation; The system retrieves satellite ephemeris data from multiple mega-satellites online, and receives satellite ephemeris data from at least one mega-satellite input by the user through the satellite management interface. Each satellite ephemeris is stored in a pre-defined ephemeris database. Based on the saved satellite ephemeris, a transit map of a giant satellite constellation is generated.

3. The method according to claim 1, characterized in that, The generated transit image of the giant satellite constellation includes: Obtain TLE data for each megasatellite in a megasatellite constellation; The SGP4 model was used to calculate the TLE data to obtain the set of positions of each giant satellite in the geocentric-geofixed coordinate system during the observation period. The set of positions is the geocentric-geofixed coordinate of the giant satellite during the observation period. Based on the various location sets, a transit map of a giant satellite constellation is generated.

4. The method according to claim 3, characterized in that, The method of marking the observable megasatellite trajectory during the observation period in the transit display map based on ground station information and various basic information includes: Obtain the minimum receiving elevation angle of the ground station, the coordinates of the ground station, and the geocentric and geofixed coordinates of each giant satellite during the observation period; Based on the minimum receiving elevation angle, ground station coordinates, and geocentric and geofixed coordinates of the giant satellite, the set of observable satellites in the giant satellite constellation during the observation period is determined, and the set of observable satellites is the giant satellites that can be observed during the observation period. Mark the satellite trajectories of giant satellites in the observable satellite array on the transit display map.

5. The method according to claim 1, characterized in that, The method further includes: When any giant satellite is mismatched with the antenna resources of all antennas, a prompt message will be issued through the display interface showing the transit map.

6. A giant satellite constellation transit tracking device, characterized in that, The device includes: The image generation module is used to generate a transit image of a giant satellite constellation. The transit image includes the satellite trajectory and basic information of the giant satellite, and the satellite trajectory includes two-dimensional trajectory and three-dimensional trajectory. The marking module is used to mark the satellite trajectory of observable megasatellites during the observation period in the transit display map based on ground station information and various basic information. The list generation module is used to generate a priority-based list of satellite observations based on preset priority evaluation rules. The list of satellite observations includes each giant satellite with marked satellite trajectory and its corresponding priority. The resource allocation module is used to allocate resources to each mega-satellite in the satellite observation list according to the priority in the satellite observation list, so as to generate a list of satellite tracking tasks corresponding to the observation period. The inventory generation module generates a priority-based satellite observation inventory based on preset priority evaluation rules, specifically including: Determine whether the user performed a selection operation on any giant satellite with marked satellite tracks through the transit view; if the user did not perform a selection operation on any giant satellite with marked satellite tracks through the transit view, generate a priority list of satellite observations according to the priority evaluation rules; if the user performed a selection operation on any giant satellite with marked satellite tracks through the transit view, obtain an operation list, and generate a priority list of satellite observations based on the operation list and the priority evaluation rules, wherein the priority evaluation rules are set according to satellite type or satellite application nature. The process of allocating resources to each megasatellite in the satellite observation list according to its priority includes: acquiring antenna resources from ground stations, including antenna status and antenna capability parameters; searching for idle antennas that match the antenna resources of each megasatellite in the satellite observation list in descending order of priority; when an idle antenna resource matches a megasatellite, associating the megasatellite with that antenna and locking the antenna; when no idle antenna resource matches a megasatellite, triggering a conflict resolution process, releasing the antenna resources already allocated to lower-priority megasatellites and reallocating them, wherein locked antennas cannot be associated with other megasatellites.

7. A storage medium, characterized in that, The storage medium includes stored instructions, wherein, when the instructions are executed, the device in which the storage medium resides controls the execution of the method as described in any one of claims 1-5.

8. An electronic device, characterized in that, include: Memory, used to store instructions; A processor configured to operate according to instructions to perform the method as described in any one of claims 1-5.

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