Satellite signal cone beam drawing method and system, electronic equipment and storage medium

Abstract

The invention relates to a satellite signal cone beam drawing method and system, electronic equipment and a storage medium. The method comprises the following steps: dynamically acquiring satellite original data, and encapsulating the satellite original data into dynamic scene marking data; the satellite original data at least comprises a real-time first position coordinate of a satellite and a second position coordinate of a satellite signal coverage target; according to the first position coordinate and the second position coordinate, calculating the length and direction of a conical beam from the satellite to the coverage target, and determining the bottom surface of the conical beam according to the first position coordinate; and drawing the conical wave beam of the satellite signal from the satellite to the coverage target based on the length, direction, position and bottom surface of the conical wave beam. According to the method, the conical wave beam coverage range of the satellite signal can be calculated in real time according to the position of the satellite, the satellite signal coverage range and the signal coverage change in the satellite motion state can be presented more visually, and the visual effect and the performance experience are improved.

Description

Technical Field

[0001] This application relates to the field of satellite technology, and in particular to satellite signal conical beam mapping methods, systems, electronic devices and storage media. Background Technology

[0002] In recent years, with the rapid development of satellite technology, satellite applications have expanded widely from the military field to the civilian field, with a continuously expanding market size and increasing commercialization. Users have placed higher demands on the visualization of satellite coverage and its actual operational capabilities. Intuitively and accurately displaying satellite signal coverage is of great significance for applications such as satellite mission planning, communication link analysis, and remote sensing observation assessment. Satellite signal conical beam layout is a relatively intuitive way to represent signal coverage. It can accurately simulate the radiation range of satellite antenna signals and intuitively present the communication and observation relationship between the satellite and ground or air targets. Combined with satellite orbital dynamics models (such as transit, orbit changes, and other motion states), the spatial position and attitude of the conical beam can be dynamically updated, thereby simulating the real-time changes in the signal coverage area during satellite operation, allowing users to more intuitively grasp the dynamic coverage characteristics of the satellite.

[0003] However, existing technologies still have shortcomings in realizing the dynamic visualization of satellite signal conical beams. Therefore, it is necessary to provide a technical solution that can more intuitively present the satellite signal coverage range and the changes in signal coverage under satellite motion. Summary of the Invention

[0004] To address or partially address the problems existing in related technologies, this application provides a satellite signal conical beam plotting method, system, electronic device, and storage medium, which can more intuitively present the satellite signal coverage range and signal coverage changes under satellite motion conditions, thereby improving the visualization effect and performance experience.

[0005] The first aspect of this application provides a method for satellite signal conical beam mapping, comprising: The system dynamically acquires raw satellite data and encapsulates it into dynamic scene marker data. The raw satellite data includes at least the real-time first position coordinates of the satellite and the second position coordinates of the target covered by the satellite signal. Calculate the length, direction, and position of the conical beam from the satellite to the coverage target based on the first and second position coordinates; The bottom surface of the conical beam is determined based on the first position coordinates; The conical beam of the satellite signal from the satellite to the coverage target is drawn based on the length, direction, position, and bottom surface of the conical beam.

[0006] In some embodiments, calculating the length, direction, and position of the conical beam from the satellite to the coverage target based on the first and second location coordinates includes: The distance between the satellite and the coverage target is calculated using the first and second position coordinates, and the distance is used as the length of the conical beam. A rotation matrix is ​​generated based on the first position coordinates and the second position coordinates, and the direction of the conical beam is determined according to the rotation matrix. The midpoint between the satellite and the coverage target is calculated based on the first and second position coordinates, and the position of the conical beam is determined based on the midpoint.

[0007] In some implementations, generating a rotation matrix based on the first position coordinates and the second position coordinates, and determining the direction of the conical beam based on the rotation matrix, includes: Generate a first element, a second element, and a third element based on the first position coordinates and the second position coordinates; Construct the rotation matrix based on the first element, the second element, and the third element; The heading angle, initial pitch angle, and roll angle are extracted based on the rotation matrix. The initial pitch angle is corrected to obtain the pitch angle; The direction of the conical beam is determined based on the heading angle, the pitch angle, and the roll angle.

[0008] In some implementations, generating the first element, the second element, and the third element based on the first position coordinates and the second position coordinates includes: A direction vector from the satellite to the coverage target is generated based on the first position coordinates and the second position coordinates, and the direction vector is normalized to obtain a normalized vector. The first element is determined based on the normalized vector. The second initial element is determined based on the first position coordinates and the second position coordinates; The third element is determined based on the second initial element and the first element; The second element is determined based on the third element and the first element.

[0009] In some implementations, constructing the rotation matrix based on the first element, the second element, and the third element includes: Construct an initial rotation matrix based on the first element, the second element, and the third element; A model matrix is ​​constructed based on the initial rotation matrix and the first position coordinates, and the rotation matrix is ​​extracted from the model matrix.

[0010] In some embodiments, determining the bottom surface of the conical beam based on the first position coordinates includes: The first altitude of the satellite relative to the ground is determined based on the first position coordinates; The bottom surface of the conical beam is calculated based on the first altitude, the Earth's radius, and the preset beam half-apex angle radian.

[0011] In some embodiments, after drawing the conical beam from the satellite to the coverage target based on the length, direction, position, and bottom surface of the conical beam, the method further includes: In response to the user's selection of the desired rendering option for the target satellite in the interactive interface, a rendering command is generated; The conical beam is rendered for the target satellite according to the rendering instructions.

[0012] In some embodiments, the method further includes: When the user does not select the "determine rendering" setting option for the target satellite in the interactive interface, the camera's second altitude relative to the ground is obtained in real time. Determine whether the second height is less than a preset threshold. If so, render the conical beam.

[0013] A second aspect of this application provides a satellite signal conical beam mapping system, comprising: An encapsulation module is used to dynamically acquire raw satellite data and encapsulate the raw satellite data into dynamic scene marker data; the raw satellite data includes at least the real-time first position coordinates of the satellite and the second position coordinates of the target covered by the satellite signal; The calculation module is used to calculate the length, direction, and position of the conical beam from the satellite to the coverage target based on the first position coordinates and the second position coordinates; The determining module is used to determine the bottom surface of the conical beam based on the first position coordinates; A drawing module is used to draw the conical beam of the satellite signal from the satellite to the coverage target based on the length, direction, position and bottom surface of the conical beam.

[0014] A third aspect of this application provides an electronic device, comprising: Processor; and A memory that stores executable code, which, when executed by the processor, causes the processor to perform the method described above.

[0015] The technical solution provided in this application may include the following beneficial results: This application provides a method for drawing conical beams of satellite signals, comprising: dynamically acquiring raw satellite data; encapsulating the raw satellite data into dynamic scene marker data; the raw satellite data including at least a first real-time position coordinate of the satellite and a second position coordinate of the target covered by the satellite signal; calculating the length, direction, and position of the conical beam from the satellite to the target based on the first and second position coordinates; determining the bottom surface of the conical beam based on the first position coordinates; and drawing the conical beam of the satellite signal from the satellite to the target based on the length, direction, position, and bottom surface of the conical beam. This method enables real-time calculation of the conical beam coverage area of ​​the satellite signal based on the satellite's position, providing a more intuitive presentation of the satellite signal coverage area and signal coverage changes under satellite motion, thus improving visualization effects and performance experience.

[0016] It should be understood that the above general description and the following detailed description are exemplary and explanatory only, and do not limit this application. Attached Figure Description

[0017] The above and other objects, features and advantages of this application will become more apparent from the more detailed description of exemplary embodiments thereof in conjunction with the accompanying drawings, wherein the same reference numerals generally represent the same components in the exemplary embodiments thereof.

[0018] Figure 1 This is a schematic flowchart illustrating the satellite signal conical beam plotting method according to an embodiment of this application; Figure 2 This is another schematic flowchart illustrating the satellite signal conical beam plotting method shown in the embodiments of this application; Figure 3 This is a flowchart illustrating a satellite signal conical beam plotting method according to an embodiment of this application; Figure 4 This is a schematic diagram of the structure of a satellite signal conical beam mapping system shown in an embodiment of this application; Figure 5 This is a schematic diagram of the structure of an electronic device shown in an embodiment of this application. Detailed Implementation

[0019] Embodiments of this application will now be described in more detail with reference to the accompanying drawings. While embodiments of this application are shown in the drawings, it should be understood that this application may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided to make this application more thorough and complete, and to fully convey the scope of this application to those skilled in the art.

[0020] The terminology used in this application is for the purpose of describing particular embodiments only and is not intended to be limiting of the application. The singular forms “a,” “the,” and “the” used in this application and the appended claims are also intended to include the plural forms unless the context clearly indicates otherwise. It should also be understood that the term “and / or” as used herein refers to and includes any or all possible combinations of one or more of the associated listed items.

[0021] It should be understood that although the terms "first," "second," "third," etc., may be used in this application to describe various information, this information should not be limited to these terms. These terms are only used to distinguish information of the same type from one another. For example, without departing from the scope of this application, first information may also be referred to as second information, and similarly, second information may also be referred to as first information. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this application, "multiple" means two or more, unless otherwise explicitly specified.

[0022] There are still shortcomings in the related technologies for realizing the dynamic visualization of satellite signal conical beams. Therefore, it is necessary to provide a technical solution that can more intuitively present the satellite signal coverage range and the changes in signal coverage under satellite motion.

[0023] To address the aforementioned issues, this application provides a method for drawing conical beams of satellite signals, which can more intuitively present the coverage area of ​​satellite signals and the changes in signal coverage under satellite motion, thereby improving the visualization effect and performance experience.

[0024] The technical solutions of the embodiments of this application are described in detail below with reference to the accompanying drawings.

[0025] Figure 1 This is a schematic flowchart illustrating the satellite signal conical beam plotting method in an embodiment of this application.

[0026] See Figure 1 The method includes: Step 110: Dynamically acquire raw satellite data and encapsulate it into dynamic scene marker data; the raw satellite data includes at least the real-time first position coordinates of the satellite and the second position coordinates of the target covered by the satellite signal.

[0027] In this embodiment, the user can dynamically configure core satellite attribute data, including satellite name, satellite ID (Identifier), satellite 3D (Three Dimensions) model parameters, orbit color, direction of travel, and spatial position. The satellite name, satellite ID, direction of travel, and spatial position can be obtained through a pre-defined interface, while the satellite 3D model parameters and orbit color can be customized by the user. The original satellite attribute data is structured. In specific implementations, the core satellite attribute data, the satellite's real-time first position coordinates, and the second position coordinates of the targets to be covered by the satellite signal can be dynamically acquired. During satellite operation, the first position coordinates P of the satellite's real-time position point A can be acquired in real time. A ,in It can also obtain the second position coordinates P of the location point B of the target covered by the satellite signal. B ,in P A and P B All coordinates are Cartesian. In this embodiment, satellites include both moving and stationary satellites, and the conical beam can be dynamically plotted and updated to follow the movement of the satellites.

[0028] Following the CZML (Cesium Markup Language) specification, raw satellite data is encapsulated into CZML format file data (dynamic scene marker data), achieving standardized integration of data and visualization rules. In practice, the generated CZML format file data is used as the data source and loaded into the Earth scene through the Cesium API (Application Programming Interface) of Cesium (an application for creating interactive 3D maps based on geospatial data). The engine automatically parses the satellite attributes and behavior rules in the file and renders the satellite's 3D model, orbit, and motion status in real time on a web page to obtain the initial scene, thus forming an intuitive interactive visualization effect.

[0029] Step 120: Calculate the length, direction, and position of the conical beam from the satellite to the coverage target based on the first and second position coordinates.

[0030] Based on the first position coordinate P A Second position coordinates P B The length len of the conical beam from the satellite to the target can be calculated, and the length len of the conical beam can be expressed by the following formula (1): (1) Based on the first position coordinate P A Second position coordinates PB The quaternion Q can be calculated, and the orientation of the conical beam can be determined based on the quaternion Q.

[0031] Based on the first position coordinate P A Second position coordinates P B It is also possible to calculate the midpoint between the satellite and the target being covered, and determine the position of the midpoint as the position of the conical beam from the satellite to the target being covered. The position can be represented by the following formula (2): (2) Step 130: Determine the bottom surface of the conical beam based on the first position coordinates.

[0032] Furthermore, it can also be based on the satellite's first position coordinates P A Calculate the coverage area of ​​the satellite signal and use it as the bottom size of the conical beam.

[0033] Step 140: Draw the conical beam of the satellite signal from the satellite to the coverage target based on the length, direction, position and bottom surface of the conical beam.

[0034] The conical beam representing the satellite signal from the satellite to the coverage target is drawn based on the beam's length (len), orientation, position, and bottom size. During the drawing process, the color, transparency, and other data of the conical beam can also be set.

[0035] This application provides a method for drawing conical beams of satellite signals, comprising: dynamically acquiring raw satellite data and encapsulating the raw satellite data into dynamic scene marker data; the raw satellite data includes at least the real-time first position coordinates of the satellite and the second position coordinates of the target covered by the satellite signal; calculating the length, direction, and position of the conical beam from the satellite to the target based on the first and second position coordinates; determining the bottom surface of the conical beam based on the first position coordinates; and drawing the conical beam of the satellite signal from the satellite to the target based on the length, direction, position, and bottom surface of the conical beam. This method enables real-time calculation of the conical beam coverage area of ​​the satellite signal based on the satellite's position, providing a more intuitive presentation of the satellite signal coverage area and signal coverage changes under satellite motion, thus improving visualization effects and performance experience.

[0036] Figure 2 This is another schematic flowchart illustrating the satellite signal conical beam plotting method in the embodiments of this application.

[0037] See Figure 2 The method includes: Step 210: Dynamically acquire raw satellite data and encapsulate it into dynamic scene marker data; the raw satellite data includes at least the real-time first position coordinates of the satellite and the second position coordinates of the target covered by the satellite signal.

[0038] In this embodiment, the user can dynamically configure core satellite attribute data, including satellite name, satellite ID, satellite 3D model parameters, orbit color, direction of travel, and spatial position. The satellite name, satellite ID, direction of travel, and spatial position can be obtained through a pre-set interface, while the satellite 3D model parameters and orbit color can be customized by the user. The original satellite attribute data is structured. In specific implementations, the core satellite attribute data, the satellite's real-time first position coordinates, and the second position coordinates of the targets to be covered by the satellite signal can be dynamically acquired. During satellite operation, the first position coordinates P of the satellite's real-time position point A can be acquired in real time. A ,in It can also obtain the second position coordinates P of the location point B of the target covered by the satellite signal. B ,in P A and P B All coordinates are Cartesian. In this embodiment, satellites include both moving and stationary satellites, and the conical beam can be dynamically plotted and updated to follow the movement of the satellites.

[0039] Following the CZML (Cesium Markup Language) specification, raw satellite data is encapsulated into CZML format files (dynamic scene markup data), achieving standardized integration of data and visualization rules. In practice, the generated CZML format files are used as the data source and loaded into the Earth scene via the Cesium API. The engine automatically parses the satellite attributes and behavior rules in the files, rendering the satellite's 3D model, orbit, and motion status in real time on the web page to obtain the initial scene, thus creating an intuitive and interactive visualization effect.

[0040] Step 220: Calculate the distance between the satellite and the coverage target using the first and second position coordinates, and use the distance as the length of the conical beam.

[0041] Based on the first position coordinate P A Second position coordinates P B The distance from the satellite to the target being covered can be calculated, and the distance from the satellite to the target being covered can be used as the length len of the conical beam. The calculation method is based on Equation (1).

[0042] Step 230: Generate a rotation matrix based on the first position coordinates and the second position coordinates, and determine the direction of the conical beam according to the rotation matrix.

[0043] Based on the first position coordinate P A Second position coordinates P B A rotation matrix can be generated, the rotation matrix can be transformed to obtain a quaternion Q, and the orientation of the conical beam can be determined based on the quaternion Q.

[0044] In an optional embodiment of this application, step 230 includes: Sub-step 231: Generate the first element, the second element, and the third element based on the first position coordinates and the second position coordinates.

[0045] Based on the first position coordinate P A Second position coordinates P B It can generate the first, second, and third elements of a rotation matrix.

[0046] Sub-step 232: Construct a rotation matrix based on the first element, the second element, and the third element.

[0047] A rotation matrix can be constructed using the first, second, and third elements. .

[0048] Sub-step 233: Extract the heading angle, initial pitch angle, and roll angle based on the rotation matrix.

[0049] According to the rotation matrix The heading angle h, initial pitch angle p, and roll angle r can be extracted, referencing equation (3): (3) The HPR (Halpern-Peaceman-Rachford) method is a first-order accelerated optimization algorithm designed for large-scale linear programming (LP) problems. Its core idea combines Halpern iteration with the neighbor-based Peaceman-Rachford splitting operator, using matrix-vector multiplication as the core operation and employing relaxation techniques to achieve large-step updates, thereby improving solution efficiency. In one example, the HPR method is used to rotate the matrix... Extract the heading angle h, initial pitch angle p, and roll angle r.

[0050] Sub-step 234: Correct the initial pitch angle to obtain the pitch angle.

[0051] Correcting the initial pitch angle p by compensating with 1.5π radians (270°) yields the final pitch angle. Reference formula (4): (4) Sub-step 235: Determine the direction of the conical beam based on the heading angle, pitch angle, and roll angle.

[0052] Based on the first position coordinate P A and heading angle h, pitch angle The roll angle r generates a quaternion Q, which is then used to determine the orientation of the conical beam. The quaternion Q can be expressed by equation (5): (5) in, is a function representing quaternions.

[0053] Sub-step 231 includes: A direction vector from the satellite to the coverage target is generated based on the first and second position coordinates, and the direction vector is normalized to obtain a normalized vector. The first element is determined based on the normalized vector. The second initial element is determined based on the first and second position coordinates; The third element is determined based on the second initial element and the first element; The second element is determined based on the third element and the first element.

[0054] Based on the first position coordinate P A Second position coordinates P B The direction vector d from the satellite to the target can be calculated using equation (6): (6) Normalizing the direction vector d yields the normalized vector. Reference formula (7): (7) Normalized vector The first element z is determined to be the direction of motion of the local Z-axis pointing direction vector d.

[0055] Based on the first position coordinate P A Second position coordinates P B The second initial element y can be determined, referring to equation (8): (8) The second initial element's y-direction points in the opposite direction to the Earth's center, which is upward.

[0056] The third element x can be determined based on the second initial element y and the first element z, as shown in equation (9): (9) The third element x, the second initial element y, and the first element z form a right-handed coordinate system.

[0057] Re-orthogonalize the second initial element y to generate the second element. Reference formula (10): (10) Sub-step 232 includes: Construct an initial rotation matrix based on the first, second, and third elements; Construct a model matrix based on the initial rotation matrix and the first position coordinates, and extract the rotation matrix from the model matrix.

[0058] Based on the first element z, the second element Construct the initial rotation matrix R with the third element x, as shown in equation (11): (11) The initial rotation matrix R is a rotation matrix relative to the Cartesian coordinate system.

[0059] Based on the first position coordinate P A The model matrix M can be constructed from the initial rotation matrix R, as shown in equation (12): (12) The rotation matrix can be extracted from the model matrix M. The rotation matrix at this time is the rotation matrix relative to the northeast-northeast coordinate system.

[0060] Step 240: Calculate the midpoint between the satellite and the coverage target based on the first and second position coordinates, and determine the position of the conical beam based on the midpoint.

[0061] Based on the first position coordinate P A Second position coordinates P B The midpoint between the satellite and the target it covers can be calculated, and the midpoint can be determined as the position of the conical beam from the satellite to the target it covers, as shown in equation (13): (13).

[0062] Step 250: Determine the bottom surface of the conical beam based on the first position coordinates.

[0063] Based on the satellite's first position coordinates P A In The bottom size of the conical beam can be determined.

[0064] In an optional embodiment of this application, step 250 includes: Determine the satellite's first altitude relative to the ground based on the first position coordinates; The bottom surface of the conical beam is calculated based on the first altitude, the Earth's radius, and the preset beam half-apex angle radian.

[0065] Based on the satellite's first position coordinates P A In The satellite's first altitude relative to the ground, the Earth's radius, and the preset beam half-apex angle can be used to calculate the coverage area of ​​the satellite signal. The coverage area of ​​the satellite signal is determined as the bottom size of the conical beam, as shown in equation (14). (14).

[0066] Step 260: Draw the conical beam of the satellite signal from the satellite to the coverage target based on the length, direction, position and bottom surface of the conical beam.

[0067] The conical beam of the satellite signal from the satellite to the coverage target is drawn based on the length (len), orientation, position, and bottom size of the conical beam.

[0068] In an optional embodiment of this application, after step 260, the method further includes: In response to the user's selection of the desired rendering option for the target satellite in the interactive interface, a rendering command is generated; Render a conical beam for the target satellite according to the rendering instructions.

[0069] Furthermore, it can determine whether to render a conical beam based on the user's settings. If the user selects the "confirm rendering" setting option in the interactive interface, a rendering command can be generated, and a conical beam can be rendered for the target satellite according to the rendering command.

[0070] In an optional embodiment of this application, the method further includes: When the user does not select the "determine rendering" setting option for the target satellite in the interactive interface, the camera's second altitude relative to the ground is obtained in real time. Determine if the second height is less than a preset threshold; if so, render the conical beam.

[0071] In practical implementation, if the user does not select the "confirm rendering" setting option for the target satellite in the interactive interface, the camera's second altitude relative to the ground can be obtained in real time. If the second altitude is less than a preset threshold, the conical beam is rendered; otherwise, rendering is not performed, reducing system resource consumption and optimizing performance. In one example, the preset threshold can be set to 500,000m. During implementation, to facilitate analysis of the target satellite's beam pattern, user settings are prioritized. If the user selects the "confirm rendering" setting option in the interactive interface, the conical beam will still be rendered even if the camera's second altitude exceeds the preset threshold.

[0072] In actual use, users can drag the unit Earth model to "fly freely" to any location, and can intuitively observe the projection path and coverage of the conical beam simulated satellite signal from different angles, providing users with an immersive experience; it can be used in scenarios such as satellite mission planning (such as ground station site selection), emergency communication plan simulation, and satellite communication (such as signal interference analysis and multi-satellite collaborative coverage).

[0073] Reference Figure 3 The flowchart for the method of drawing conical beams for satellite signals includes: dynamically acquiring raw satellite data, encapsulating the raw satellite data into CZML data and loading the CZML data, calculating the length of the conical beam, determining the direction of the conical beam, determining the position of the conical beam, determining the bottom surface of the conical beam, drawing the conical beam, and determining whether the camera height is not greater than a preset threshold (e.g., 500,000m). If so, the conical beam is rendered; otherwise, the conical beam is not rendered.

[0074] This application provides a method for drawing conical beams of satellite signals, which can calculate the coverage area of ​​satellite signals in real time based on the satellite's position, presenting the coverage area of ​​satellite signals and the changes in signal coverage under satellite motion more intuitively, and improving the visualization effect and performance experience.

[0075] Corresponding to the aforementioned application function implementation method embodiments, this application also provides a satellite signal conical beam mapping system, electronic device, and corresponding embodiments.

[0076] Figure 4 This is a schematic diagram of the structure of a satellite signal conical beam mapping system shown in an embodiment of this application.

[0077] See Figure 4 The system includes: The encapsulation module 610 is used to dynamically acquire raw satellite data and encapsulate the raw satellite data into dynamic scene marker data; the raw satellite data includes at least the real-time first position coordinates of the satellite and the second position coordinates of the target covered by the satellite signal; Calculation module 620 is used to calculate the length, direction, and position of the conical beam from the satellite to the coverage target based on the first position coordinates and the second position coordinates; The determining module 630 is used to determine the bottom surface of the conical beam based on the first position coordinates; The drawing module 640 is used to draw the conical beam of the satellite signal from the satellite to the coverage target based on the length, direction, position and bottom surface of the conical beam.

[0078] In an optional embodiment of this application, the computing module 620 includes: The first calculation submodule is used to calculate the distance between the satellite and the coverage target using the first and second position coordinates, and to use the distance as the length of the conical beam. The second calculation submodule is used to generate a rotation matrix based on the first and second position coordinates, and to determine the direction of the conical beam based on the rotation matrix. The third calculation submodule is used to calculate the midpoint between the satellite and the coverage target based on the first and second position coordinates, and to determine the position of the conical beam based on the midpoint.

[0079] The second calculation submodule is also used for: Generate the first element, the second element, and the third element based on the first and second position coordinates; Construct a rotation matrix based on the first, second, and third elements; Extracting heading angle, initial pitch angle, and roll angle based on rotation matrix; The pitch angle is obtained by correcting the initial pitch angle; The direction of the conical beam is determined by the heading angle, pitch angle, and roll angle.

[0080] The second calculation submodule is also used for: A direction vector from the satellite to the coverage target is generated based on the first and second position coordinates, and the direction vector is normalized to obtain a normalized vector. The first element is determined based on the normalized vector. The second initial element is determined based on the first and second position coordinates; The third element is determined based on the second initial element and the first element; The second element is determined based on the third element and the first element.

[0081] The second calculation submodule is also used for: Construct an initial rotation matrix based on the first, second, and third elements; Construct a model matrix based on the initial rotation matrix and the first position coordinates, and extract the rotation matrix from the model matrix.

[0082] In an optional embodiment of this application, the determining module 630 includes: The first altitude submodule is used to determine the first altitude of the satellite relative to the ground based on the first position coordinates; The bottom surface submodule is used to calculate the bottom surface of the conical beam based on the first height, the Earth's radius, and the preset beam half-apex angle radian.

[0083] In an optional embodiment of this application, the system further includes: The rendering instruction module is used to generate rendering instructions in response to the user's selection of the desired rendering setting for the target satellite in the interactive interface. The first rendering module is used to render a conical beam for the target satellite according to rendering instructions.

[0084] In an optional embodiment of this application, the system further includes: The second altitude module is used to obtain the camera's second altitude relative to the ground in real time when the user does not select the "determine rendering" setting option for the target satellite in the interactive interface. The second rendering module is used to determine whether the second height is less than a preset threshold. If so, the conical beam is rendered.

[0085] This application provides a satellite signal conical beam mapping system, which can calculate the conical beam coverage of satellite signals in real time based on the satellite's position, presenting the satellite signal coverage and signal coverage changes under satellite motion more intuitively, and improving the visualization effect and performance experience.

[0086] Regarding the system in the above embodiments, the specific ways in which each module performs operations have been described in detail in the embodiments related to the method, and will not be elaborated further here.

[0087] Figure 5 This is a schematic diagram of the structure of an electronic device shown in an embodiment of this application.

[0088] See Figure 5 The electronic device 700 includes a memory 710 and a processor 720.

[0089] The processor 720 can be a Central Processing Unit (CPU), or other general-purpose processors, digital signal processors (DSPs), application-specific integrated circuits (ASICs), field-programmable gate arrays (FPGAs), or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. The general-purpose processor can be a microprocessor or any conventional processor.

[0090] Memory 710 may include various types of storage units, such as system memory, read-only memory (ROM), and permanent storage devices. ROM may store static data or instructions required by the processor 720 or other modules of the computer. Permanent storage devices may be read-write storage devices. Permanent storage devices may be non-volatile storage devices that retain stored instructions and data even when the computer is powered off. In some embodiments, permanent storage devices use mass storage devices (e.g., magnetic or optical disks, flash memory) as permanent storage devices. In other embodiments, permanent storage devices may be removable storage devices (e.g., floppy disks, optical drives). System memory may be a read-write storage device or a volatile read-write storage device, such as dynamic random access memory. System memory may store some or all of the instructions and data required by the processor during operation. Furthermore, memory 710 may include any combination of computer-readable storage media, including various types of semiconductor memory chips (e.g., DRAM, SRAM, SDRAM, flash memory, programmable read-only memory), and disks and / or optical disks may also be used. In some embodiments, memory 710 may include a removable storage device that is readable and / or writable, such as a laser disc (CD), a read-only digital versatile optical disc (e.g., DVD-ROM, dual-layer DVD-ROM), a read-only Blu-ray disc, an ultra-high density optical disc, a flash memory card (e.g., SD card, mini SD card, Micro-SD card, etc.), a magnetic floppy disk, etc. Computer-readable storage media do not contain carrier waves or transient electronic signals transmitted wirelessly or via wired connections.

[0091] The memory 710 stores executable code, which, when processed by the processor 720, can cause the processor 720 to execute part or all of the methods described above.

[0092] Furthermore, the method according to this application can also be implemented as a computer program or computer program product, which includes computer program code instructions for performing some or all of the steps in the method described above.

[0093] Alternatively, this application may be implemented as a computer-readable storage medium (or a non-transitory machine-readable storage medium or a machine-readable storage medium) storing executable code (or computer program or computer instruction code) that, when executed by a processor of an electronic device (or server, etc.), causes the processor to perform part or all of the steps of the methods described above according to this application.

[0094] This application also provides a computer program product, which includes computer instructions that, when executed by a processor, implement the method described above.

[0095] The various embodiments of this application have been described above. These descriptions are exemplary and not exhaustive, nor are they limited to the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments. The terminology used herein is chosen to best explain the principles, practical application, or improvement of the technology in the market, or to enable others skilled in the art to understand the embodiments disclosed herein.

Claims

1. A method for plotting conical beams of satellite signals, characterized in that, The method includes: The system dynamically acquires raw satellite data and encapsulates it into dynamic scene marker data. The raw satellite data includes at least the real-time first position coordinates of the satellite and the second position coordinates of the target covered by the satellite signal. Calculate the length, direction, and position of the conical beam from the satellite to the coverage target based on the first and second position coordinates; The bottom surface of the conical beam is determined based on the first position coordinates; The conical beam of the satellite signal from the satellite to the coverage target is drawn based on the length, direction, position, and bottom surface of the conical beam.

2. The method according to claim 1, characterized in that, The calculation of the length, direction, and position of the conical beam from the satellite to the coverage target based on the first and second position coordinates includes: The distance between the satellite and the coverage target is calculated using the first and second position coordinates, and the distance is used as the length of the conical beam. A rotation matrix is ​​generated based on the first position coordinates and the second position coordinates, and the direction of the conical beam is determined according to the rotation matrix. The midpoint between the satellite and the coverage target is calculated based on the first and second position coordinates, and the position of the conical beam is determined based on the midpoint.

3. The method according to claim 2, characterized in that, The step of generating a rotation matrix based on the first position coordinates and the second position coordinates, and determining the direction of the conical beam based on the rotation matrix, includes: Generate a first element, a second element, and a third element based on the first position coordinates and the second position coordinates; Construct the rotation matrix based on the first element, the second element, and the third element; The heading angle, initial pitch angle, and roll angle are extracted based on the rotation matrix. The initial pitch angle is corrected to obtain the pitch angle; The direction of the conical beam is determined based on the heading angle, the pitch angle, and the roll angle.

4. The method according to claim 3, characterized in that, The step of generating the first element, the second element, and the third element based on the first position coordinates and the second position coordinates includes: A direction vector from the satellite to the coverage target is generated based on the first position coordinates and the second position coordinates, and the direction vector is normalized to obtain a normalized vector. The first element is determined based on the normalized vector. The second initial element is determined based on the first position coordinates and the second position coordinates; The third element is determined based on the second initial element and the first element; The second element is determined based on the third element and the first element.

5. The method according to claim 3, characterized in that, Constructing the rotation matrix based on the first element, the second element, and the third element includes: Construct an initial rotation matrix based on the first element, the second element, and the third element; A model matrix is ​​constructed based on the initial rotation matrix and the first position coordinates, and the rotation matrix is ​​extracted from the model matrix.

6. The method according to claim 1, characterized in that, Determining the bottom surface of the conical beam based on the first position coordinates includes: The first altitude of the satellite relative to the ground is determined based on the first position coordinates; The bottom surface of the conical beam is calculated based on the first altitude, the Earth's radius, and the preset beam half-apex angle radian.

7. The method according to claim 1, characterized in that, After drawing the conical beam from the satellite to the coverage target based on the length, direction, position, and bottom surface of the conical beam, the method further includes: In response to the user's selection of the desired rendering option for the target satellite in the interactive interface, a rendering command is generated; The conical beam is rendered for the target satellite according to the rendering instructions.

8. The method according to claim 7, characterized in that, The method further includes: When the user does not select the "determine rendering" setting option for the target satellite in the interactive interface, the camera's second altitude relative to the ground is obtained in real time. Determine whether the second height is less than a preset threshold. If so, render the conical beam.

9. A satellite signal conical beam mapping system, characterized in that, The system includes: An encapsulation module is used to dynamically acquire raw satellite data and encapsulate the raw satellite data into dynamic scene marker data; the raw satellite data includes at least the real-time first position coordinates of the satellite and the second position coordinates of the target covered by the satellite signal; The calculation module is used to calculate the length, direction, and position of the conical beam from the satellite to the coverage target based on the first position coordinates and the second position coordinates; The determining module is used to determine the bottom surface of the conical beam based on the first position coordinates; A drawing module is used to draw the conical beam of the satellite signal from the satellite to the coverage target based on the length, direction, position and bottom surface of the conical beam.

10. An electronic device, characterized in that, include: processor; as well as A memory having executable code stored thereon, which, when executed by the processor, causes the processor to perform the method as described in any one of claims 1-8.

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