Method for realizing beam-to-ground coverage through low-orbit satellite beam position design

A technology for low-orbit satellites and communication satellites, applied in the field of satellite communications, to achieve the effect of optimizing the number of beams and reducing the overlap rate

Active Publication Date: 2021-06-25
航天科工空间工程发展有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] So far, there are no published literature or patents dedicated to the design

Method used

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  • Method for realizing beam-to-ground coverage through low-orbit satellite beam position design
  • Method for realizing beam-to-ground coverage through low-orbit satellite beam position design
  • Method for realizing beam-to-ground coverage through low-orbit satellite beam position design

Examples

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no. 1 example

[0072] figure 1 It shows a schematic diagram of three traditional wave position arrangements, namely: tandem wave position a, overlapping wave position b and staggered wave position c.

[0073] figure 2 The schematic diagrams of the two wave position arrangement styles proposed in this embodiment are given, wherein d is a schematic diagram of the equilateral overlapping wave position arrangement style, which is composed of three spot beam positions, and the centers of the three spot beam positions form an equilateral Triangle, the side length of the equilateral triangle is the radius of the spot beam beam (the spot beam beam is the circle projected by the spot beam to the ground) times. e is a schematic diagram of the cellular overlapping wave position arrangement pattern evolved on the basis of the equilateral overlapping wave position arrangement pattern, which is composed of a central point beam position and six surrounding spot beam positions, and six surrounding point...

no. 2 example

[0150] Figure 7 A schematic structural diagram of a computer device provided by another embodiment of the present application is shown. Figure 7 The computer device 50 shown is only an example, and should not impose any limitation on the functions and scope of use of the embodiments of the present application. Such as Figure 7 As shown, computer device 50 takes the form of a general-purpose computing device. Components of computer device 50 may include, but are not limited to: one or more processors or processing units 500 , system memory 516 , bus 501 connecting various system components including system memory 516 and processing unit 500 .

[0151] Bus 501 represents one or more of several types of bus structures, including a memory bus or memory controller, a peripheral bus, an accelerated graphics port, a processor, or a local bus using any of a variety of bus structures. These architectures include, by way of example, but are not limited to Industry Standard Archite...

no. 3 example

[0159] Another embodiment of the present application provides a computer-readable storage medium, on which a computer program is stored, and when the program is executed by a processor, the method provided in the first embodiment above is implemented. In practical applications, the computer-readable storage medium may use any combination of one or more computer-readable media. The computer readable medium may be a computer readable signal medium or a computer readable storage medium.

[0160] A computer-readable storage medium may be, for example, but not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, device, or device, or any combination thereof. More specific examples (non-exhaustive list) of computer readable storage media include: electrical connections with one or more leads, portable computer disks, hard disks, random access memory (RAM), read only memory (ROM), Erasable programmable read-only memory (EPROM or flash mem...

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Abstract

The embodiment of the invention discloses a method for realizing beam-to-ground coverage through low-orbit satellite beam position design. The method comprises the following steps: S10, acquiring an orbit height, an orbit inclination angle, an equivalent half-cone angle of a ground coverage area and a spot beam half-cone angle of a low-orbit communication satellite; S12, according to the orbit height, the orbit inclination angle, the equivalent half-cone angle of the ground coverage area and the spot beam half-cone angle of the low-orbit communication satellite, obtaining the number of spot beam positions for realizing equivalent coverage of the equivalent half-cone angle area; S14, arranging the spot beam positions according to an equilateral overlapping mode or a honeycomb overlapping mode; S16, calculating an azimuth angle and a pitch angle of a center direction vector of a spot beam corresponding to each arranged spot beam position on a given reference coordinate system; S18, driving an antenna of the satellite to enable a center direction vector of a spot beam emitted by the antenna of the satellite to point to the earth according to the calculated azimuth angle and pitch angle.

Description

technical field [0001] The invention relates to the field of satellite communication, in particular to a method for realizing beam-to-earth coverage through low-orbit satellite wave position design. Background technique [0002] Satellite communication systems can be divided into GSO (Geostationary-Satellite Orbit, Geostationary Satellite Orbit) satellite communication systems and low-orbit communication satellite systems according to the altitude of the orbit. The GSO communication satellite system already has strong technical accumulation at home and abroad and has provided market services for a long time. However, the GSO communication satellite system also has obvious shortcomings, especially the time delay problem caused by long distance, which is increasingly unable to meet the increasingly high real-time requirements of communication services. Compared with the GSO communication satellite system, the main advantage of the low-orbit communication satellite system is t...

Claims

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Application Information

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IPC IPC(8): H04W16/28H04W16/18H04B7/185
CPCH04W16/28H04W16/18H04B7/18578H04B7/18597
Inventor 贺泉赵书阁向开恒杨彪
Owner 航天科工空间工程发展有限公司
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