CN117831246A

CN117831246A - Low-orbit communication satellite communication method and device

Info

Publication number: CN117831246A
Application number: CN202410243882.8A
Authority: CN
Inventors: 朱亮; 沈朝阳; 戚少博; 高千峰; 张世杰; 侯海洋; 徐鸣
Original assignee: Galaxy Aerospace Beijing Network Technology Co ltd
Current assignee: Galaxy Aerospace Beijing Network Technology Co ltd
Priority date: 2024-03-04
Filing date: 2024-03-04
Publication date: 2024-04-05
Anticipated expiration: 2044-03-04
Also published as: CN117831246B

Abstract

The application provides a low-orbit communication satellite communication method and a device, wherein the low-orbit communication satellite communication method comprises the following steps: calculating a signal coverage area of a low-orbit communication satellite in the earth based on the earth attribute information of the earth and satellite attribute information of the low-orbit communication satellite; determining a spherical area corresponding to the signal coverage area in a sphere model corresponding to the earth, and positioning an effective coverage area of the low-orbit communication satellite in the spherical area according to the area parameters of the signal coverage area; calculating stepping period information of the low-orbit communication satellite according to the regional parameters, the earth attribute information and the satellite attribute information; and creating and executing a signal coverage task of the low-orbit communication satellite based on the effective coverage area and the stepping period information, wherein the signal coverage task is used for the low-orbit communication satellite to perform signal coverage on the earth.

Description

Low-orbit communication satellite communication method and device

Technical Field

The present disclosure relates to the field of information processing technologies, and in particular, to a method and an apparatus for low-orbit communication satellite communication.

Background

The constellation communication system is characterized in that network elements of the networking are movable. I.e. the communication terminal is mobile and the communication satellite is mobile. And because the movement speed of the low orbit satellite is high, the situation that better communication service can not be provided for the terminal equipment easily appears. When the communication service is provided, the principle is that the satellite staring range is determined according to the coordinate point of the low orbit satellite projected to the ground so as to provide the communication service for terminal equipment in the range. However, since the gaze range of the low-orbit satellite is limited, and all terminals in the gaze range should interact with the low-orbit satellite in the current period, if the gaze range is determined by taking the projection position of the low-orbit satellite as a fixed point, the coverage of adjacent satellites is easily overlapped, or a dead angle is easily caused. And because the satellite is in a moving state relative to the earth, the satellite cannot gaze at the same area all the time, and the satellite can shift to the next gaze cycle to gaze at other areas every interval of set time. If there is a deviation in the gaze stepping period of adjacent satellites, this may also cause a problem that coverage is overlapped, or that a certain area cannot be covered within a certain period of time. There is therefore a need for an effective solution to the above problems.

Disclosure of Invention

In view of the foregoing, embodiments of the present application provide a low-orbit communication satellite communication method to solve the technical drawbacks existing in the prior art. Embodiments of the present application also provide a low-orbit communication satellite communication apparatus, a computing device, a computer-readable storage medium and a computer program product.

According to a first aspect of an embodiment of the present application, there is provided a low-orbit communication satellite communication method, including:

calculating a signal coverage area of a low-orbit communication satellite in the earth based on the earth attribute information of the earth and satellite attribute information of the low-orbit communication satellite;

determining a spherical area corresponding to the signal coverage area in a sphere model corresponding to the earth, and positioning an effective coverage area of the low-orbit communication satellite in the spherical area according to the area parameters of the signal coverage area;

calculating stepping period information of the low-orbit communication satellite according to the regional parameters, the earth attribute information and the satellite attribute information;

and creating and executing a signal coverage task of the low-orbit communication satellite based on the effective coverage area and the stepping period information, wherein the signal coverage task is used for the low-orbit communication satellite to perform signal coverage on the earth.

Optionally, calculating a signal coverage area of the low-orbit communication satellite in the earth based on the earth attribute information of the earth and satellite attribute information of the low-orbit communication satellite includes:

acquiring the radius information and the earth surface height deviation information of the earth as the earth attribute information;

acquiring orbit height information, half-power angle information, scanning angle information and flying speed information of a low-orbit communication satellite as satellite attribute information;

calculating regional radius information according to the radius information, the ground surface height deviation information, the track height information, the half power angle information, the scanning angle information and the flying speed information;

and determining the signal coverage area of the low-orbit communication satellite in the earth according to the regional radius information.

Optionally, before the step of determining the spherical area corresponding to the signal coverage area in the spherical model corresponding to the earth is performed, the method further includes:

calculating side length information of an area composition unit according to the earth attribute information and the satellite attribute information;

and drawing a sphere model corresponding to the earth according to the side length information, wherein the sphere model is obtained by splicing a plurality of region composition units, and the region composition units are equilateral triangles.

Optionally, said locating the effective coverage area of the low-orbit communication satellite in the spherical area according to the area parameters of the signal coverage area comprises:

determining the regional parameters of the signal coverage area, and extracting regional radius information from the regional parameters;

calculating long side information and short side information of a region to be positioned in the spherical region according to the region radius information;

and dividing an effective coverage area of the low-orbit communication satellite in the spherical area according to the long-side information and the short-side information, wherein the effective coverage area is obtained by splicing a set number of area composition units.

Optionally, the calculation of the region radius information is obtained by the following formula:

；

wherein r is _max Represents the maximum value of the area radius information, H _orbit Representing the track height information, R _earth Representing the radius information, Δh representing the surface elevation deviation information,representing the half-power angle information, θ representing the scan angle information.

Optionally, the calculating step period information of the low-orbit communication satellite according to the regional parameter, the earth attribute information and the satellite attribute information includes:

Calculating the satellite moving distance of the low-orbit communication satellite according to the regional parameters;

calculating the stepping period information of the low-orbit communication satellite according to the satellite moving distance, the earth attribute information and the satellite attribute information;

the step period information is used for controlling the coverage time of the low-orbit communication satellite for signal coverage of the effective coverage area.

Optionally, the step period information is calculated by the following formula:

；

wherein P is _max Maximum value of step period information, v _sat And information representing the speed of flight of the low-orbit communication satellite.

Optionally, the performing of the signal coverage task includes:

determining an area to be gazed in the earth based on the effective coverage area in the signal coverage task;

controlling the low-orbit communication satellite to perform signal coverage on the to-be-gazed area according to the stepping period information in the signal coverage task;

after the signal coverage task of the low-orbit communication satellite is created and the executing steps are executed, the method further comprises the following steps:

determining an associated gaze area adjacent to the area to be gazed upon the step period information satisfying an area switching condition;

And taking the relevant staring area as the area to be stared, and executing the step of controlling the low-orbit communication satellite to perform signal coverage on the area to be stared according to the stepping period information in the signal coverage task.

According to a second aspect of embodiments of the present application, there is provided a low-orbit communication satellite communication device, comprising:

a calculation area module configured to calculate a signal coverage area of a low-orbit communication satellite in the earth based on earth attribute information of the earth and satellite attribute information of the low-orbit communication satellite;

a positioning area module configured to determine a spherical area corresponding to the signal coverage area in a spherical model corresponding to the earth, and position an effective coverage area of the low-orbit communication satellite in the spherical area according to an area parameter of the signal coverage area;

a calculation information module configured to calculate step period information of the low-orbit communication satellite based on the region parameter, the earth attribute information, and the satellite attribute information;

and a task execution module configured to create and execute a signal coverage task of the low-orbit communication satellite based on the effective coverage area and the stepping period information, wherein the signal coverage task is used for the low-orbit communication satellite to perform signal coverage on the earth.

According to a third aspect of embodiments of the present application, there is provided a computing device comprising:

a memory and a processor;

the memory is used for storing computer executable instructions that when executed by the processor implement the steps of the low-orbit communication satellite communication method.

According to a fourth aspect of embodiments of the present application, there is provided a computer readable storage medium storing computer executable instructions which, when executed by a processor, implement the steps of the low-orbit communication satellite communication method.

According to a fifth aspect of embodiments of the present specification, there is provided a computer program product comprising a computer program or instructions which, when executed by a processor, implement the steps of the low-orbit communication satellite communication method described above.

In order to achieve signal coverage of the effective coverage area by the low-orbit communication satellite, the low-orbit communication satellite communication method provided by the embodiment is reasonable in coverage time period and coverage, ensures high satellite resource utilization rate, and can calculate the signal coverage of the low-orbit communication satellite in the earth based on the earth attribute information of the earth and the satellite attribute information of the low-orbit communication satellite. In order to avoid the problems, and improve the satellite resource utilization rate, a spherical area corresponding to the signal coverage area can be determined in a spherical model corresponding to the earth, and then an effective coverage area of the low-orbit communication satellite can be positioned in the spherical area according to the area parameters of the signal coverage area, so that the effective coverage area is connected with other adjacent coverage areas and is not overlapped and dead angles are not generated, and the coverage area of each low-orbit communication satellite is more reasonable. On the basis, because the satellite is in a motion state relative to the earth, the satellite cannot gaze at the same area all the time, the stepping period information of the low-orbit communication satellite can be calculated by combining the area parameter, the earth attribute information and the satellite attribute information, and the stepping period information and the effective coverage area create a signal coverage task related to the low-orbit communication satellite, so that when the task is executed, the satellite can be controlled to perform signal coverage on the effective coverage area according to the stepping period information, and after the period is finished, the satellite can be switched to the next area and then perform signal coverage, thereby ensuring continuous signal coverage of each area, avoiding the occurrence of the problem of overlapping or no signal coverage of the area due to the movement of the satellite, effectively improving the utilization rate of satellite resources, and solving the problem of signal coverage area distribution of the low-orbit communication satellite.

Drawings

FIG. 1 is a schematic diagram of a method for low-orbit communication satellite according to an embodiment of the present application;

FIG. 2 is a flow chart of a method for low-orbit communication satellite communication according to an embodiment of the present application;

fig. 3 is a schematic diagram of an effective coverage area in a low-orbit communication satellite communication method according to an embodiment of the present application;

FIG. 4 is a process flow diagram of a method for low-orbit communication satellite communication according to an embodiment of the present application;

fig. 5 is a schematic structural diagram of a low-orbit communication satellite communication device according to an embodiment of the present application;

FIG. 6 is a block diagram of a computing device according to one embodiment of the present application.

Detailed Description

In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present application. This application is, however, susceptible of embodiment in many other ways than those herein described and similar generalizations can be made by those skilled in the art without departing from the spirit of the application and the application is therefore not limited to the specific embodiments disclosed below.

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

It should be understood that, although the terms first, second, etc. may be used in one or more embodiments of the present application to describe various information, these information should not be limited to these terms. These terms are only used to distinguish one type of information from another. For example, a first may also be referred to as a second, and similarly, a second may also be referred to as a first, without departing from the scope of one or more embodiments of the present application.

First, terms related to one or more embodiments of the present invention will be explained.

Global navigation satellite systems (Global Navigation Satellite System, GNSS), also known as global satellite navigation systems, are space-based radio navigation positioning systems that can provide all-weather three-dimensional coordinates and velocity and time information to a user at any point on the earth's surface or near earth space. Which includes one or more satellite constellations and augmentation systems required for supporting a particular job.

Inertial navigation (inertial navigation) is a technique for obtaining instantaneous speed and instantaneous position data of an aircraft by measuring the acceleration of the aircraft and automatically performing an integration operation. The equipment forming the inertial navigation system is arranged in the carrier body, and the inertial navigation system is independent of external information and does not radiate energy to the outside when working, is not easy to interfere, and is an autonomous navigation system.

In the present application, a low-orbit communication satellite communication method is provided. The present application relates to a low-orbit communication satellite communication device, a computing apparatus, a computer-readable storage medium and a computer program product, which are described in detail in the following embodiments.

Referring to fig. 1, in order to achieve signal coverage of an effective coverage area by a low-orbit communication satellite, and ensure that the coverage time period and coverage are reasonable, the low-orbit communication satellite communication method provided by the embodiment can calculate the signal coverage of the low-orbit communication satellite in the earth based on the earth attribute information of the earth and the satellite attribute information of the low-orbit communication satellite. In order to avoid the problems, and improve the satellite resource utilization rate, a spherical area corresponding to the signal coverage area can be determined in a spherical model corresponding to the earth, and then an effective coverage area of the low-orbit communication satellite can be positioned in the spherical area according to the area parameters of the signal coverage area, so that the effective coverage area is connected with other adjacent coverage areas and is not overlapped and dead angles are not generated, and the coverage area of each low-orbit communication satellite is more reasonable. On the basis, because the satellite is in a motion state relative to the earth, the satellite cannot gaze at the same area all the time, the stepping period information of the low-orbit communication satellite can be calculated by combining the area parameter, the earth attribute information and the satellite attribute information, and the stepping period information and the effective coverage area create a signal coverage task related to the low-orbit communication satellite, so that when the task is executed, the satellite can be controlled to perform signal coverage on the effective coverage area according to the stepping period information, and after the period is finished, the satellite can be switched to the next area and then perform signal coverage, thereby ensuring continuous signal coverage of each area, avoiding the occurrence of the problem of overlapping or no signal coverage of the area due to the movement of the satellite, effectively improving the utilization rate of satellite resources, and solving the problem of signal coverage area distribution of the low-orbit communication satellite.

Fig. 2 shows a flowchart of a low-orbit communication satellite communication method according to an embodiment of the present application, which specifically includes the following steps:

step S202, calculating the signal coverage area of the low-orbit communication satellite in the earth based on the earth attribute information of the earth and the satellite attribute information of the low-orbit communication satellite.

The low-orbit communication satellite communication method provided by the embodiment is applied to a scene of creating a signal coverage task for the low-orbit communication satellite, and is used for realizing that the low-orbit communication satellite can cover signals according to set time for a designated area when in signal coverage, and the adjacent satellite can achieve the purpose of seamless switching, so that more stable and high-quality communication service is provided for the terminal.

The earth attribute information specifically refers to attribute description information corresponding to the earth, including but not limited to earth radius information, earth surface altitude difference information, earth rotation information, earth revolution information, and the like. Correspondingly, the satellite attribute information specifically refers to attribute description information of a corresponding low-orbit communication satellite, including but not limited to orbit height information of the satellite, an antenna normal half-power angle of the satellite, an average flying speed of the satellite, a time interval of beam control of the satellite antenna, a batch of the satellite, a model of the satellite and the like. Correspondingly, the signal coverage area specifically refers to an area which can be covered by the low-orbit communication satellite on the earth surface, and the area can provide signal coverage by the low-orbit communication satellite, but because the area is larger, and an overlapping area possibly exists between adjacent satellites, the satellite resource waste can be caused, and the area can be adjusted subsequently to obtain an effective coverage area corresponding to the satellite, so that the utilization rate of the satellite resource is improved.

Based on the above, in order to perform more reasonable signal coverage on the earth through the low-orbit communication satellite, and achieve seamless switching between adjacent satellites, the earth attribute information of the earth and the satellite attribute information of the low-orbit communication satellite can be acquired first, and based on the information, the calculation of the signal coverage area of the low-orbit communication satellite relative to the earth can be performed, so that the effective coverage area corresponding to the positioning satellite in the sphere model for the area can be conveniently performed, and the utilization rate of satellite resources can be improved.

Further, when calculating the signal coverage area based on the earth attribute information and the satellite attribute information, considering that the signal coverage area is an actual coverage area of the satellite in the earth, the effective coverage area needs to be determined on the basis of the signal coverage area, so that the accuracy of the effective coverage area can be ensured on the premise that the calculation accuracy of the area needs to be ensured, and the calculation can be performed by combining information of multiple dimensions. In this embodiment, the specific implementation manner is as follows:

acquiring the radius information and the earth surface height deviation information of the earth as the earth attribute information; acquiring orbit height information, half-power angle information, scanning angle information and flying speed information of a low-orbit communication satellite as satellite attribute information; calculating regional radius information according to the radius information, the ground surface height deviation information, the track height information, the half power angle information, the scanning angle information and the flying speed information; and determining the signal coverage area of the low-orbit communication satellite in the earth according to the regional radius information.

Specifically, the half power angle information specifically refers to a normal half power angle of the satellite antenna, and the scan angle information specifically refers to a maximum scan angle of the satellite beam. The corresponding area radius information specifically refers to the area radius size information of the signal coverage area.

Based on this, in order to ensure the calculation accuracy of the signal coverage area, the radius information and the surface height deviation information of the earth may be acquired first as the earth attribute information; simultaneously acquiring orbit height information, half power angle information, scanning angle information and flying speed information of a low-orbit communication satellite as satellite attribute information; on the basis, the radius information, the ground surface height deviation information, the track height information, the half power angle information, the scanning angle information and the flying speed information can be combined to calculate the regional radius information; and then determining the signal coverage area of the low-orbit communication satellite in the earth according to the regional radius information. And the effective coverage area is conveniently calculated based on the signal coverage area.

Further, the calculation of the region radius information can be obtained by the following formula (1):

（1）；

In the implementation, considering the effective coverage area of the low-orbit communication satellite with the phased array antenna, the effective coverage area is mainly related to the maximum half power angle of the beam and the scanning angle of the antenna, and the coverage area range may be affected by other factors, so that the maximum value of the area radius information can be calculated by combining the parameters, and the signal coverage area of the corresponding low-orbit communication satellite can be drawn based on the radius. In practical application, after the maximum value of the area radius information is obtained through calculation, a target value smaller than the maximum value can be selected as the area radius information according to practical requirements, so that the drawn signal coverage area is ensured to be more in line with a real scene.

For example, the earth radius R1 is acquired, and the earth-surface altitude deviation h1 of the low-orbit communication satellite 1 in the signal coverage area covered by the earth surface is acquired; simultaneously acquiring satellite orbit height H1 of low-orbit communication satellite 1 and normal half-power angle of satellite antenna1, maximum scan angle θ1 of satellite beam and average satellite flying speed v1, on the basis, calculating by combining the formula (1) to obtain the radius r which can be covered by the low-orbit communication satellite 1 at the maximum scanning angle of the corresponding wave beam of the earth _max . With r is as _max The signal coverage of the low-orbit communication satellite 1 on the earth can be determined based on the radius, and the effective coverage can be conveniently determined based on the signal coverage subsequently.

In summary, by combining the parameters of multiple dimensions to calculate the area radius information and determining the signal coverage area based on the calculated area radius information, the accuracy of the calculation of the signal coverage area can be ensured, and the actual signal coverage area corresponding to the low-orbit communication satellite can be ensured to be subsequently divided based on the calculated accuracy, so that more stable and better communication service is provided.

And step S204, determining a spherical area corresponding to the signal coverage area in the spherical model corresponding to the earth, and positioning the effective coverage area of the low-orbit communication satellite in the spherical area according to the area parameters of the signal coverage area.

Specifically, after the signal coverage area corresponding to the low-orbit communication satellite is determined, further, considering that the signal coverage area is calculated based on the area radius information, the signal coverage area is circular, and if the subsequent signal coverage is performed according to the circular coverage area, the problem that adjacent satellite signal coverage overlaps or coverage dead angles may occur. Therefore, when the effective coverage area is positioned, the signal coverage area can be mapped to the sphere model corresponding to the earth to be completed, meanwhile, the sphere model is obtained by splicing a large number of polygons, so that the shape of the effective coverage area can be positioned according to the shape of an area component unit of the sphere model, for example, the sphere model is obtained by splicing a large number of equilateral triangles, when the effective coverage area is positioned, a hexagon can be selected as the shape of the effective coverage area, and then the effective coverage area corresponding to the signal coverage area is positioned in the sphere model, and the area is a hexagon. And the effective coverage areas corresponding to other adjacent satellites can be connected without overlapping or dead angles. When the satellite focuses on the area, the corresponding beam scanning area can be found in the earth according to the hexagon to cover signals, so that the aim of higher satellite resource utilization rate is fulfilled.

Based on the above, when the effective coverage area is positioned, the effective coverage areas of the adjacent satellites are considered to meet, and no dead angle and no overlap exist, so that a sphere model which is obtained by splicing a plurality of area composition units and has a similar shape to the earth and a position mapping relation can be determined, and then a spherical area corresponding to the signal coverage area can be determined on the sphere model. After the spherical area is determined on the spherical model, the area parameters of the signal coverage area, such as the radius information of the area, and the like, can be determined, and the signal coverage area with smaller positioning range in the spherical area can be used as the effective coverage area corresponding to the low-orbit communication satellite on the basis of the area parameters, so that the signal coverage task associated with the low-orbit communication satellite can be conveniently established on the basis of the effective coverage area, and more stable and continuous communication service can be provided for the corresponding area when the signal coverage task is executed.

In addition, considering that the sphere model is the basis for locating the effective coverage area, it is necessary to ensure the closeness of the sphere model to the shape of the earth, so that the effective coverage area corresponding to the signal coverage area can be correctly fed back. In this embodiment, the specific implementation manner is as follows:

Calculating side length information of an area composition unit according to the earth attribute information and the satellite attribute information; and drawing a sphere model corresponding to the earth according to the side length information, wherein the sphere model is obtained by splicing a plurality of region composition units, and the region composition units are equilateral triangles.

Specifically, the region composition unit specifically refers to an equilateral triangle drawn according to the side length information. Based on this, in order to be able to ensure the degree of similarity of the sphere model and the earth shape, the side length information of the region composition unit may be calculated from the earth attribute information and the satellite attribute information; and drawing a sphere model corresponding to the earth according to the side length information, wherein the drawn sphere model is obtained by splicing a plurality of area composition units.

In practical application, considering that the earth is not a particularly regular sphere shape, if polygons of other shapes are adopted to draw the sphere model, it may not be ensured that the constructed sphere model is closer to the real shape of the earth, so in order to make the drawn sphere model more approximate to the shape of the earth with smaller errors, an equilateral triangle can be selected as a region composing unit, and because the equilateral triangle is a minimum polygon structure, and the model structure formed after splicing has larger variability, the model structure is more similar to the shape of the earth, and therefore, the equilateral triangle is used as the region composing unit based on the model structure, and the errors can be reduced by subsequent use. In addition, other polygons may be selected as region constituent units in the case of tolerance to errors. Correspondingly, the side length information specifically refers to calculating the side length information of any side of the region composition unit after determining the shape of the region composition unit, and is used for splicing the sphere model by using the region composition unit corresponding to the side length information.

The sphere model is drawn based on the equilateral triangle, so that a schematic diagram shown in fig. 3 (a) can be obtained, and when the subsequent effective coverage area positioning is performed based on the schematic diagram, the effective coverage area can be formed by selecting a set number of equilateral triangles according to the area parameter frame of the signal coverage area, thereby being convenient to use in the application stage.

In conclusion, by drawing the sphere model by combining the earth attribute information and the satellite attribute information, the similarity degree of the sphere model and the shape of the earth can be ensured, so that the positioning of the effective coverage area can be performed based on the sphere model in the application stage, and the positioning accuracy is ensured.

Further, when the effective coverage area of the low-orbit communication satellite is positioned according to the area parameters of the signal coverage area, in order to ensure positioning accuracy, the long side and the short side of the area can be calculated by combining the area radius information, so that the effective coverage area is divided in the spherical area. In this embodiment, the specific implementation manner is as follows:

determining the regional parameters of the signal coverage area, and extracting regional radius information from the regional parameters; calculating long side information and short side information of a region to be positioned in the spherical region according to the region radius information; and dividing an effective coverage area of the low-orbit communication satellite in the spherical area according to the long-side information and the short-side information, wherein the effective coverage area is obtained by splicing a set number of area composition units.

Specifically, the area radius information specifically refers to an area radius size corresponding to the signal coverage area. Correspondingly, the area to be positioned specifically refers to an effective coverage area to be divided, the long side information of the effective coverage area is the long side size of the area, the short side information of the effective coverage area is the short side size of the area, and the effective coverage area is also surrounded by polygonal shapes, such as a hexagon, an octagon or a quadrilateral, due to the fact that the sphere model is composed of a plurality of polygons.

Based on this, when locating the effective coverage area according to the area parameters of the signal coverage area, in order to ensure the availability of the effective coverage area, the area parameters of the signal coverage area may be determined first, and the area radius information may be extracted from the area parameters; according to the radius information of the area, the long side information and the short side information of the area to be positioned are calculated in the spherical area, after the long side information and the short side information of the area to be positioned are obtained, the size information of the area to be divided is indicated to be already in the spherical area, then the effective coverage area of the low-orbit communication satellite can be divided in the spherical area according to the long side information and the short side information, and the effective coverage area is spliced by a set number of area composition units.

In practical applications, although the largest area that can be covered by the satellite signal of the low-orbit communication satellite is a spherical circular area with an area radius information, it is impossible to always cover such a large area because the satellite is in an operational state. Considering that the whole satellite signal coverage mode of the low-orbit communication satellite is staring, the effective coverage area corresponding to the effective single satellite is smaller than the area of a hemispherical circle, and the single low-orbit communication satellite can be ensured to have a fixed coverage area in a certain staring period based on the effective coverage area. Therefore, consider that the sphere model is made by a large scaleAnd (5) splicing the equilateral triangles. Thus, the effective coverage area of a single low-orbit communication satellite can be designed to be hexagonal in shape and determined to be the effective coverage area of a hexagon within the spherical area, and the short side of the hexagon can be one-half r _max The long side is r _max 。

In the above example, the radius of the signal coverage area corresponding to the low-orbit communication satellite 1 is determined to be r _max Then, considering that the sphere model is obtained by splicing equilateral triangles and combines the motion mode of the low-orbit communication satellite, half of the range in the signal coverage area can be selected as an effective coverage area, and the effective coverage area can be hexagonal in shape, so that the sphere model can be filled with the equilateral triangles contained in the sphere model. Thus, as shown in FIG. 3 (b), the signal coverage area radius r may be varied _max Short side 1/2*r of calculated effective coverage area _max And long side r _max And on the spherical surface area corresponding to the signal coverage area in the sphere model, the effective coverage area corresponding to the low-orbit communication satellite 1 is separated according to the long-side size and the short-side size, so that the low-orbit communication satellite 1 can cover the area in a staring period under a moving state, and the signal coverage is completed. It should be noted that, three hexagonal areas shown in fig. 3 (b) are the same effective coverage area corresponding to the signal coverage area, and the purpose of displaying the three hexagonal areas is to represent that the signal coverage areas corresponding to the low-orbit communication satellite 1 are all the same effective coverage area under the conditions that the low-orbit communication satellite 1 is at different moments and all the three moments belong to the staring period. That is, the vertical dimension in the figure corresponds to the time variation dimension, and characterizes that the effective coverage area of the low-orbit communication satellite is unchanged in the staring period.

In summary, by combining the regional parameters of the signal coverage region to calculate the effective coverage region on the spherical region, it can be ensured that the satellite has a fixed coverage region in the movement state and the staring period, so as to ensure that the signal coverage region of each staring period can always obtain signal coverage, thereby providing high-quality and stable communication service for the terminal.

Step S206, calculating step period information of the low-orbit communication satellite according to the regional parameter, the earth attribute information and the satellite attribute information.

Specifically, after the effective coverage area corresponding to the low-orbit communication satellite is determined, further, considering that the satellite is in a motion state relative to the earth, the same satellite cannot be ensured to gaze at an area all the time, so that the satellite moves out of a range corresponding to the area after the satellite is gazed at the effective coverage area for a set time, and communication service cannot be provided for the area. In order to avoid signal interruption, and after the satellite moves out of the range, the effective coverage area corresponding to each satellite can be seamlessly switched to the next satellite to continue signal coverage of the area, and the stepping period information of the low-orbit communication satellite can be calculated by combining the area parameter, the earth attribute information and the satellite attribute information, so that the low-orbit communication satellite can continue to stare the next effective coverage area after the period is finished, and the last effective coverage area can be continuously covered by the adjacent satellite, thereby forming a seamless switching coverage area, and any one effective coverage area can be covered by the satellite corresponding to the current moment of the area.

The step period information specifically refers to time information of staring an effective coverage area of the low-orbit communication satellite, and is used for controlling the satellite to perform signal coverage on the effective coverage area within the time period, and after the satellite moves out of the area, the satellite continues to perform signal coverage according to the period information for the next area, so that the effect of no sense of satellite signal switching is achieved.

Furthermore, when the step period information is calculated, the gaze time is considered to be influenced by various factors, so that the signal coverage time is accurate, the adjacent satellites can be connected in a seamless manner, and the method can be realized by combining multidimensional parameters such as satellite moving distance and the like. In this embodiment, the specific implementation manner is as follows:

calculating the satellite moving distance of the low-orbit communication satellite according to the regional parameters; calculating the stepping period information of the low-orbit communication satellite according to the satellite moving distance, the earth attribute information and the satellite attribute information; the step period information is used for controlling the coverage time of the low-orbit communication satellite for signal coverage of the effective coverage area.

In particular, the satellite movement distance refers to the distance that the low-orbit communication satellite needs to move relative to the signal coverage area, and the signal coverage is performed on the area within the movement distance. Based on this, considering that the signal coverage area of the low-orbit communication satellite needs to be covered by the satellite which is moved without interruption, in order to ensure the coverage time continuity, the satellite movement distance of the low-orbit communication satellite can be calculated according to the area parameter; calculating the stepping period information of the low-orbit communication satellite according to the satellite moving distance, the earth attribute information and the satellite attribute information; and the step period information may be used to control the coverage time of the low-orbit communication satellite for signal coverage for the effective coverage area.

Further, the calculation of the step period information can be obtained by the following formula (2):

（2）；

wherein P is _max Represents the maximum value of the step period information, r _max Represents the maximum value of the area radius information, H _orbit Representing the track height information, R _earth Represents the radius information, Δh represents the surface height deviation information, v _sat And information representing the speed of flight of the low-orbit communication satellite.

That is, assuming that the low-orbit communication satellite flies from the lower direction, the effective coverage area moves from the upper side to the lower side of the spherical area from the satellite viewpoint, and thus the longest distance moved is approximated as. Therefore, the stepping period information of the coverage effective coverage area of the low-orbit communication satellite can be calculated by combining the formula (2), thereby realizing the control of the single communication satellite in the low-orbit constellation, and the stepping period is carried out every other timeThe coverage needs to be adjusted. In addition, because the communication satellites in the low orbit constellation are the same batch of satellites of the same type, the stepping period and the effective coverage range of adjacent satellites are the same, and when the satellites are switched in any area, the non-inductive switching can be achieved.

In the above example, the flight direction of the low-orbit communication satellite 1 is from bottom to top, so that it can be determined that the effective coverage area is moved from the upper side to the lower side of the circular area with respect to the satellite, and further that the longest movement distance of the low-orbit communication satellite 1 is Combine area radius information->The earth radius R1, the earth surface altitude deviation H1, the satellite orbit altitude H1 and the satellite average flying speed v1 can calculate the stepping period P of the low-orbit communication satellite 1, and then the low-orbit communication satellite 1 can be controlled to cover the effective coverage area according to the stepping period P, and after reaching the coverage time, the next signal coverage area is switched.

In conclusion, by combining the multidimensional parameters to calculate the stepping period of the satellite, the calculation precision of the stepping period can be ensured, so that seamless connection between adjacent satellites can be realized when the coverage area of the satellite is adjusted, and more stable and high-quality communication service is provided for the terminal.

And step S208, creating and executing a signal coverage task of the low-orbit communication satellite based on the effective coverage area and the stepping period information, wherein the signal coverage task is used for the low-orbit communication satellite to perform signal coverage on the earth.

Specifically, after the effective coverage area and the step period information corresponding to the low-orbit communication satellite are obtained, further, in order to enable the low-orbit communication satellite to perform signal coverage on the effective coverage area according to the step period information, a signal coverage task of the low-orbit communication satellite can be created and executed by combining the effective coverage area and the step period information, so that the low-orbit communication satellite performs signal coverage on an actual area corresponding to the effective coverage area in the earth according to the step period information. And after the period is over, switching to the next effective coverage area to continue signal coverage.

Further, when the signal coverage task is executed, in order to determine the area to be gazed at according to the effective coverage area, signal coverage is performed according to the stepping period information. In this embodiment, the specific implementation manner is as follows:

determining an area to be gazed in the earth based on the effective coverage area in the signal coverage task; and controlling the low-orbit communication satellite to perform signal coverage on the to-be-gazed area according to the stepping period information in the signal coverage task.

Specifically, the area to be gazed specifically refers to the corresponding actual signal coverage area of the effective coverage area in the earth. Based on this, when signal coverage is performed, the area to be gazed in the earth can be determined according to the effective coverage area in the signal coverage task; and then controlling the low-orbit communication satellite to cover the signal of the area to be stared according to the stepped period information in the signal coverage task.

On the basis, after the coverage time of the low-orbit communication satellite for the effective coverage area is finished, in order to achieve seamless switching between adjacent satellites, the coverage area corresponding to the adjacent satellites can be determined, and signal coverage is continued, and in the embodiment, the specific implementation mode is as follows:

Determining an associated gaze area adjacent to the area to be gazed upon the step period information satisfying an area switching condition; and taking the relevant staring area as the area to be stared, and executing the step of controlling the low-orbit communication satellite to perform signal coverage on the area to be stared according to the stepping period information in the signal coverage task.

Specifically, the area switching condition specifically refers to a condition that the step period information reaches the end time node. Correspondingly, the relevant gazing area specifically refers to an area adjacent to the area to be gazed, and the area and the coverage area of the area to be gazed are the same. Based on the above, in the case that the stepping period information satisfies the area switching condition, which indicates that the satellite needs to adjust the coverage area at this time, an associated gaze area adjacent to the area to be gazed can be determined; and taking the combined staring area as an area to be stared, and executing the step of controlling the low-orbit communication satellite to perform signal coverage on the area to be stared according to the step period information in the signal coverage task. That is, after each period is finished, it indicates that the satellite moves to the position corresponding to the next area, and then the satellite can be controlled to continue to perform signal coverage on the next area.

For example, after determining the stepping period and the effective coverage area corresponding to the communication satellite in the low-orbit constellation, the communication satellite may be controlled to perform signal coverage on the effective coverage area according to the stepping period, and when reaching the stepping period end node, the area 2 adjacent to the current gazing area 1 may be determined, then the control satellite may continue to perform signal coverage on the area 2, and the area 1 may be further subjected to signal coverage by other communication satellites moving upstream, so as to form a complete signal coverage network.

The application of the low-orbit communication satellite communication method provided in the present application to a low-orbit communication network is taken as an example in conjunction with fig. 4, and the low-orbit communication satellite communication method will be further described below. Fig. 4 shows a process flow chart of a low-orbit communication satellite communication method according to an embodiment of the present application, which specifically includes the following steps:

step S402, radius information and surface altitude deviation information of the earth are obtained as earth attribute information.

In step S404, orbit height information, half power angle information, scan angle information, and flight speed information of the low-orbit communication satellite are acquired as satellite attribute information.

Step S406, calculating regional radius information according to the radius information, the ground surface height deviation information, the track height information, the half power angle information, the scanning angle information and the flying speed information.

In step S408, a signal coverage area of the low-orbit communication satellite in the earth is determined according to the area radius information.

Step S410, determining a spherical area corresponding to the signal coverage area in a spherical model corresponding to the earth, determining an area parameter of the signal coverage area, and extracting area radius information from the area parameter.

Step S412, calculating long side information and short side information of the area to be positioned in the spherical area according to the area radius information.

And step S414, dividing an effective coverage area of the low-orbit communication satellite in the spherical area according to the long-side information and the short-side information, wherein the effective coverage area is obtained by splicing a set number of area composition units.

In step S416, a satellite moving distance of the low-orbit communication satellite is calculated according to the regional parameter.

In step S418, step period information of the low-orbit communication satellite is calculated according to the satellite moving distance, the earth attribute information and the satellite attribute information.

The step period information is used for controlling the coverage time of the low-orbit communication satellite for signal coverage aiming at the effective coverage area.

Step S420, creating a signal coverage task of the low-orbit communication satellite based on the effective coverage area and the step period information.

Step S422, determining a region to be gazed in the earth based on the effective coverage area in the signal coverage task.

Step S424, the low-orbit communication satellite is controlled to perform signal coverage on the area to be gazed according to the step period information in the signal coverage task.

In summary, in order to realize that the low-orbit communication satellite performs signal coverage on the effective coverage area, and the coverage time period and coverage area are reasonable, the high utilization rate of satellite resources is ensured, and the signal coverage area of the low-orbit communication satellite in the earth can be calculated based on the earth attribute information of the earth and the satellite attribute information of the low-orbit communication satellite. In order to avoid the problems, and improve the satellite resource utilization rate, a spherical area corresponding to the signal coverage area can be determined in a spherical model corresponding to the earth, and then an effective coverage area of the low-orbit communication satellite can be positioned in the spherical area according to the area parameters of the signal coverage area, so that the effective coverage area is connected with other adjacent coverage areas and is not overlapped and dead angles are not generated, and the coverage area of each low-orbit communication satellite is more reasonable. On the basis, because the satellite is in a motion state relative to the earth, the satellite cannot gaze at the same area all the time, the stepping period information of the low-orbit communication satellite can be calculated by combining the area parameter, the earth attribute information and the satellite attribute information, and the stepping period information and the effective coverage area create a signal coverage task related to the low-orbit communication satellite, so that when the task is executed, the satellite can be controlled to perform signal coverage on the effective coverage area according to the stepping period information, and after the period is finished, the satellite can be switched to the next area and then perform signal coverage, thereby ensuring continuous signal coverage of each area, avoiding the occurrence of the problem of overlapping or no signal coverage of the area due to the movement of the satellite, effectively improving the utilization rate of satellite resources, and solving the problem of signal coverage area distribution of the low-orbit communication satellite.

Corresponding to the above method embodiment, the present application further provides an embodiment of a low-orbit communication satellite communication device, and fig. 5 shows a schematic structural diagram of a low-orbit communication satellite communication device according to an embodiment of the present application. As shown in fig. 5, the apparatus includes:

a calculation region module 502 configured to calculate a signal coverage region of a low-orbit communication satellite in the earth based on earth attribute information of the earth and satellite attribute information of the low-orbit communication satellite;

a positioning area module 504 configured to determine a spherical area corresponding to the signal coverage area in the spherical model corresponding to the earth, and position an effective coverage area of the low-orbit communication satellite in the spherical area according to an area parameter of the signal coverage area;

a calculation information module 506 configured to calculate step period information of the low-orbit communication satellite based on the region parameter, the earth attribute information, and the satellite attribute information;

a task execution module 508 configured to create and execute a signal coverage task for the low-orbit communication satellite for signal coverage of the earth based on the effective coverage area and the step period information.

In an alternative embodiment, the computing area module 502 is further configured to:

In an alternative embodiment, the apparatus further comprises:

a drawing module configured to calculate side length information of an area composing unit from the earth attribute information and the satellite attribute information; and drawing a sphere model corresponding to the earth according to the side length information, wherein the sphere model is obtained by splicing a plurality of region composition units, and the region composition units are equilateral triangles.

In an alternative embodiment, the location area module 504 is further configured to:

In an alternative embodiment, the calculation of the region radius information is obtained by the following formula:

；

In an alternative embodiment, the calculation information module 506 is further configured to:

In an alternative embodiment, the step period information is calculated by the following formula:

；

In an alternative embodiment, the performing of the signal overlay task includes:

determining an area to be gazed in the earth based on the effective coverage area in the signal coverage task; controlling the low-orbit communication satellite to perform signal coverage on the to-be-gazed area according to the stepping period information in the signal coverage task;

after the signal coverage task of the low-orbit communication satellite is created and the executing steps are executed, the method further comprises the following steps: determining an associated gaze area adjacent to the area to be gazed upon the step period information satisfying an area switching condition; and taking the relevant staring area as the area to be stared, and executing the step of controlling the low-orbit communication satellite to perform signal coverage on the area to be stared according to the stepping period information in the signal coverage task.

In order to achieve signal coverage of the effective coverage area by the low-orbit communication satellite, the low-orbit communication satellite communication device provided by the embodiment has reasonable coverage time period and coverage, ensures high satellite resource utilization rate, and can calculate the signal coverage of the low-orbit communication satellite in the earth based on the earth attribute information of the earth and the satellite attribute information of the low-orbit communication satellite. In order to avoid the problems, and improve the satellite resource utilization rate, a spherical area corresponding to the signal coverage area can be determined in a spherical model corresponding to the earth, and then an effective coverage area of the low-orbit communication satellite can be positioned in the spherical area according to the area parameters of the signal coverage area, so that the effective coverage area is connected with other adjacent coverage areas and is not overlapped and dead angles are not generated, and the coverage area of each low-orbit communication satellite is more reasonable. On the basis, because the satellite is in a motion state relative to the earth, the satellite cannot gaze at the same area all the time, the stepping period information of the low-orbit communication satellite can be calculated by combining the area parameter, the earth attribute information and the satellite attribute information, and the stepping period information and the effective coverage area create a signal coverage task related to the low-orbit communication satellite, so that when the task is executed, the satellite can be controlled to perform signal coverage on the effective coverage area according to the stepping period information, and after the period is finished, the satellite can be switched to the next area and then perform signal coverage, thereby ensuring continuous signal coverage of each area, avoiding the occurrence of the problem of overlapping or no signal coverage of the area due to the movement of the satellite, effectively improving the utilization rate of satellite resources, and solving the problem of signal coverage area distribution of the low-orbit communication satellite.

The above is an exemplary scheme of a low-orbit communication satellite communication device of the present embodiment. It should be noted that, the technical solution of the low-orbit communication satellite communication device and the technical solution of the low-orbit communication satellite communication method belong to the same concept, and details of the technical solution of the low-orbit communication satellite communication device, which are not described in detail, can be referred to the description of the technical solution of the low-orbit communication satellite communication method. Furthermore, the components in the apparatus embodiments should be understood as functional blocks that must be established to implement the steps of the program flow or the steps of the method, and the functional blocks are not actually functional partitions or separate limitations. The device claims defined by such a set of functional modules should be understood as a functional module architecture for implementing the solution primarily by means of the computer program described in the specification, and not as a physical device for implementing the solution primarily by means of hardware.

Fig. 6 illustrates a block diagram of a computing device 600 provided in accordance with an embodiment of the present application. The components of computing device 600 include, but are not limited to, memory 610 and processor 620. The processor 620 is coupled to the memory 610 via a bus 630 and a database 650 is used to hold data.

Computing device 600 also includes access device 640, access device 640 enabling computing device 600 to communicate via one or more networks 660. Examples of such networks include public switched telephone networks (PSTN, public Switched Telephone Network), local area networks (LAN, local Area Network), wide area networks (WAN, wide Area Network), personal area networks (PAN, personal Area Network), or combinations of communication networks such as the internet. The access device 640 may include one or more of any type of network interface, wired or wireless, such as a network interface card (NIC, network interface controller), such as an IEEE802.11 wireless local area network (WLAN, wireless Local Area Network) wireless interface, a worldwide interoperability for microwave access (Wi-MAX, worldwide Interoperability for Microwave Access) interface, an ethernet interface, a universal serial bus (USB, universal Serial Bus) interface, a cellular network interface, a bluetooth interface, a near field communication (NFC, near Field Communication) interface, and so forth.

In one embodiment of the present application, the above-described components of computing device 600, as well as other components not shown in FIG. 6, may also be connected to each other, such as by a bus. It should be understood that the block diagram of the computing device illustrated in FIG. 6 is for exemplary purposes only and is not intended to limit the scope of the present application. Those skilled in the art may add or replace other components as desired.

Computing device 600 may be any type of stationary or mobile computing device, including a mobile computer or mobile computing device (e.g., tablet, personal digital assistant, laptop, notebook, netbook, etc.), mobile phone (e.g., smart phone), wearable computing device (e.g., smart watch, smart glasses, etc.), or other type of mobile device, or a stationary computing device such as a desktop computer or personal computer (PC, personal Computer). Computing device 600 may also be a mobile or stationary server.

Wherein the processor 620 is configured to execute computer-executable instructions of the low-orbit communication satellite communication method.

The foregoing is a schematic illustration of a computing device of this embodiment. It should be noted that, the technical solution of the computing device and the technical solution of the low-orbit communication satellite communication method belong to the same concept, and details of the technical solution of the computing device, which are not described in detail, can be referred to the description of the technical solution of the low-orbit communication satellite communication method.

An embodiment of the present application also provides a computer-readable storage medium storing computer instructions that, when executed by a processor, are for use in a low-orbit communication satellite communication method.

The above is an exemplary version of a computer-readable storage medium of the present embodiment. It should be noted that, the technical solution of the storage medium and the technical solution of the low-orbit communication satellite communication method belong to the same concept, and details of the technical solution of the storage medium which are not described in detail can be referred to the description of the technical solution of the low-orbit communication satellite communication method.

An embodiment of the present disclosure also provides a computer program product comprising a computer program or instructions which, when executed by a processor, implement the steps of the low-orbit communication satellite communication method described above.

The foregoing is a schematic version of a computer program product of this embodiment. It should be noted that, the technical solution of the computer program product and the technical solution of the low-orbit communication satellite communication method belong to the same concept, and details of the technical solution of the computer program product, which are not described in detail, can be referred to the description of the technical solution of the low-orbit communication satellite communication method.

The computer instructions include computer program code that may be in source code form, object code form, executable file or some intermediate form, etc. The computer readable medium may include: any entity or device capable of carrying the computer program code, a recording medium, a U disk, a removable hard disk, a magnetic disk, an optical disk, a computer Memory, a Read-Only Memory (ROM), a random access Memory (RAM, random Access Memory), an electrical carrier signal, a telecommunications signal, a software distribution medium, and so forth. It should be noted that the content of the computer readable medium can be increased or decreased appropriately according to the requirements of the patent practice, for example, in some areas, according to the patent practice, the computer readable medium does not include an electric carrier signal and a telecommunication signal.

It should be noted that, for the sake of simplicity of description, the foregoing method embodiments are all expressed as a series of combinations of actions, but it should be understood by those skilled in the art that the present application is not limited by the order of actions described, as some steps may be performed in other order or simultaneously in accordance with the present application. Further, those skilled in the art will also appreciate that the embodiments described in the specification are all preferred embodiments, and that the acts and modules referred to are not necessarily all necessary for the present application.

In the foregoing embodiments, the descriptions of the embodiments are emphasized, and for parts of one embodiment that are not described in detail, reference may be made to the related descriptions of other embodiments.

The above-disclosed preferred embodiments of the present application are provided only as an aid to the elucidation of the present application. Alternative embodiments are not intended to be exhaustive or to limit the invention to the precise form disclosed. Obviously, many modifications and variations are possible in light of the teaching of this application. The embodiments were chosen and described in order to best explain the principles of the invention and the practical application, to thereby enable others skilled in the art to best understand and utilize the invention. This application is to be limited only by the claims and the full scope and equivalents thereof.

Claims

1. A method of low-orbit communication satellite communication, comprising:

2. The method according to claim 1, wherein calculating a signal coverage area of the low-orbit communication satellite in the earth based on the earth attribute information of the earth and the satellite attribute information of the low-orbit communication satellite comprises:

3. The method of claim 1, wherein prior to the step of determining a spherical region corresponding to the signal coverage region in the spherical model corresponding to the earth, further comprising:

4. The method of claim 1, wherein locating the effective coverage area of the low-orbit communication satellite in the spherical region according to the regional parameters of the signal coverage area comprises:

5. The low-orbit communication satellite communication method according to claim 2, wherein the calculation of the region radius information is obtained by the following formula:

；

6. The method according to claim 1, wherein calculating the step period information of the low-orbit communication satellite based on the regional parameter, the earth attribute information, and the satellite attribute information, comprises:

7. The method of claim 5, wherein the step period information is calculated by the following formula:

；

8. The method of any of claims 1-7, wherein the performing of the signal coverage task comprises:

9. A low-orbit communication satellite communication device, comprising:

10. A computing device, comprising:

a memory and a processor;

the memory is configured to store computer executable instructions and the processor is configured to execute the computer executable instructions to implement the steps of the method of any one of claims 1 to 8.

11. A computer readable storage medium storing computer instructions which, when executed by a processor, implement the steps of the method of any one of claims 1 to 8.

12. A computer program product comprising a computer program or instructions which, when executed by a processor, carries out the steps of the method of any one of claims 1 to 8.