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Internal frequency interference suppression method for a low-orbit constellation system

A low-orbit constellation and frequency interference technology, applied in the field of low-orbit satellite communications, can solve the problems of large sum of interference and affect the communication quality of earth stations, and achieve the effect of suppressing internal frequency interference

Active Publication Date: 2020-08-14
航天科工空间工程发展有限公司
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  • Abstract
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  • Application Information

AI Technical Summary

Problems solved by technology

Therefore, when the earth station communicates with a certain satellite, the sum of the interference it receives from other adjacent satellites in the constellation system is increasing, which may affect the communication quality of the earth station

Method used

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  • Internal frequency interference suppression method for a low-orbit constellation system
  • Internal frequency interference suppression method for a low-orbit constellation system
  • Internal frequency interference suppression method for a low-orbit constellation system

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no. 1 example 1

[0033] figure 1 It is a schematic flow chart of a low-orbit constellation system internal frequency interference suppression method according to the first embodiment of the present invention, as shown in figure 1 As shown, the method includes the following four steps.

[0034] Step S101: Calculate the first right ascension of the intersection point between the edge of the first satellite beam and the surface of the earth.

[0035] It should be noted that the embodiment of the present invention is applicable to the situation that the constellation system includes at least three orbital planes. Select any satellite in any one of the at least three orbital planes as the first satellite. Since the first satellite can be any satellite in the constellation, when calculating beam intersection with other satellites, you can either Calculated from the left edge of the first satellite beam, may also be calculated from the right edge of the first satellite beam. If the left edge calcu...

Embodiment 2

[0084] The embodiment of the present invention provides a low-orbit constellation system internal frequency interference suppression device, which is mainly used to implement the low-orbit constellation system internal frequency interference suppression method provided in the above-mentioned content of the embodiment of the present invention. The following is the embodiment of the present invention. The internal frequency interference suppression device of the low-orbit constellation system will be introduced in detail.

[0085] Image 6 It is a schematic structural diagram of a low-orbit constellation system internal frequency interference suppression device according to the second embodiment of the present invention. Such as Image 6 As shown, the low-orbit constellation system internal frequency interference suppression device 200 includes the following modules.

[0086] The first intersection point calculation module 201 is used to calculate the first right ascension of ...

Embodiment 3

[0091] The embodiment of the present invention also provides a computing device. Such as Figure 7 As shown, the low-orbit constellation system internal frequency interference suppression computing device 300 of this embodiment includes: a processor 301 , a memory 302 , and a program stored in the memory 302 and executable on the processor 301 . When the processor 301 executes the program, it realizes the steps in the embodiments of the above-mentioned various low-orbit constellation system internal frequency interference suppression methods, for example figure 1 Steps S101, S102, S103 and S104 are shown. Alternatively, when the processor 301 executes the program, the functions of the modules in the above-mentioned device embodiments are realized, for example Image 6 The module in the LEO constellation system realizes the internal frequency interference suppression device.

[0092]Exemplarily, the program can be divided into one or more modules, and the one or more modules...

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Abstract

The invention discloses an internal frequency interference suppression method for a low-orbit constellation system. The low-orbit constellation system comprises satellites running on at least three orbital planes, each orbital plane comprises at least one satellite, and the method comprises the steps: calculating the first right ascension of the intersection point of the beam edge of a first satellite and the earth surface, wherein the first satellite is any satellite in any one of the at least three orbital planes; calculating a second right ascension of an intersection point of a beam edge of a second satellite and the earth surface, the second satellite being a satellite spaced apart from the first satellite by a distance of two orbital planes, and the second satellite and the first satellite having the same latitude argument; and calculating the same latitude argument uc of the first right ascension and the second right ascension, and determining the satellite beam shutdown range according to the calculated latitude argument uc. Compared with the prior art, the technical scheme provided by the invention effectively suppresses the internal frequency interference of the low-orbitconstellation system on the premise of realizing the full coverage of the constellation system in the high-latitude area on the ground beams.

Description

technical field [0001] The invention relates to the field of low-orbit satellite communication, in particular to a method and device for suppressing internal frequency interference of a low-orbit constellation system. Background technique [0002] The geosynchronous orbit communication satellite system has strong technical accumulation and has established mature market services. In theory, three GSO satellites can achieve signal coverage within 70° north and south latitudes. On the other hand, the geosynchronous orbit communication satellite system also has obvious disadvantages, including long communication distance, large communication delay, low communication angle in high latitude areas, which makes communication easy to be blocked, the existence of south (north) mountain effect, and the difficulty of launching satellites into orbit. High cost and high risk. [0003] Compared with the geostationary orbit communication satellite system, the main advantages of the low-orb...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H04B7/185H04B7/155
CPCH04B7/18519H04B7/18513H04B7/15585
Inventor 赵书阁贺泉向开恒高利春周洪刚
Owner 航天科工空间工程发展有限公司
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