Phase maintaining method based on reference satellite

A satellite and phase technology, applied in the field of satellite control, can solve the problems of complex implementation process and too many phase maintenance strategies, and achieve the effects of improving continuity, avoiding calculation ambiguity and short phase maintenance time.

Inactive Publication Date: 2020-02-28
INNOVATION ACAD FOR MICROSATELLITES OF CAS +1
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  • Abstract
  • Description
  • Claims
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Problems solved by technology

[0006] The technical problem to be solved by the present invention is: the existing phase

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  • Phase maintaining method based on reference satellite
  • Phase maintaining method based on reference satellite
  • Phase maintaining method based on reference satellite

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Embodiment Construction

[0032] Specific implementations of the present invention will be described below. It should be noted that in the process of specific descriptions of these implementations, for the sake of concise description, it is impossible for this specification to describe all the features of the actual implementations in detail. This description uses specific examples to describe the present application, and can help anyone familiar with the process or system of the present invention to perform experimental operations, but is not intended to limit the protection scope thereof.

[0033] For satellite constellations, when the attenuation of the satellite orbit height is small, it will not affect the performance of the constellation, so the maintenance of the constellation configuration comes down to the maintenance of the phase between satellites. The present invention proposes a phase maintenance strategy based on a reference satellite, selects a reference satellite, and minimizes the cumul...

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Abstract

The invention provides a phase maintaining method based on a reference satellite. The phase maintaining method comprises the following steps: (1) calculating a boundary value of satellite phase drift;(2) after constellation networking, calculating the phase of each satellite in the constellation; (3) respectively taking each satellite in the constellation as a target satellite, and calculating the phase angle drift amount of other satellites in the constellation relative to the target satellite; (4) calculating an accumulated value of the phase angle drift amount; (5) selecting a satellite with the minimum phase difference design nominal value and the minimum phase angle drift critical threshold relative to the target satellite as a reference satellite, judging the satellite needing phasemaintenance, and predicting the phase maintenance time; and (6) when the phase difference of the satellite needing phase maintenance relative to the reference satellite is close to a threshold value,orbit control is carried out on the satellite needing phase maintenance according to the phase angle drifting direction, and adjustment and maintenance of the relative phase are achieved. According to the method, the defect of multiple times of absolute site maintenance is overcome, and the complexity of constellation configuration maintenance is reduced.

Description

technical field [0001] The invention relates to a constellation configuration maintenance method, in particular to a reference satellite-based Walker constellation phase maintenance method, which belongs to the technical field of satellite control. Background technique [0002] Global high coverage, ultra-short revisit interval and other usage requirements have led to new satellite projects ranging from dozens to hundreds of satellite constellations. The Walker constellation is known for its global latitude coverage and uniform revisit properties are widely used. The orbital altitude, inclination and eccentricity of each satellite in the Walker constellation are the same, and theoretically the configuration of the constellation will also remain unchanged. However, in addition to being affected by the gravitational force of the earth, satellites in orbit are also affected by perturbing forces including the oblateness of the earth, the gravitational perturbation of the sun an...

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Application Information

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IPC IPC(8): H04B7/185
CPCH04B7/18571H04B7/18573
Inventor 陈雨赵灵峰刘会杰张璇张晓杰边小龙
Owner INNOVATION ACAD FOR MICROSATELLITES OF CAS
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