Low-orbit satellite constellation configuration keeping method

Abstract

The invention discloses a low-orbit satellite constellation configuration keeping method. The method comprises the following steps: acquiring satellite orbit parameters of an initial low-orbit satellite constellation; determining a first relative drift amount of the inter-satellite configuration caused by the initial satellite orbit parameters in the constellation life period; determining a second relative drift amount of the inter-satellite configuration caused by atmospheric drag perturbation under the initial satellite orbit parameters during the constellation lifetime; according to the first relative drift distance and the second relative drift distance, determining a third relative drift distance of the inter-satellite configuration caused by other perturbation under the initial satellite orbit parameters in the constellation life period; determining an offset amount of a satellite orbit parameter required for offsetting the third relative drift amount; and adjusting satellite orbit parameters of the initial low-orbit satellite constellation according to the offset to obtain offset satellite orbit parameters so as to maintain the configuration of the low-orbit satellite constellation. By adopting the satellite constellation configuration keeping method, the problem of long-term keeping of the low-orbit constellation configuration can be solved.

Description

technical field [0001] The invention relates to the field of low-orbit satellite constellations, in particular to a method for maintaining configurations of low-orbit satellite constellations. Background technique [0002] At present, domestic and foreign low-orbit satellite constellations are developing rapidly. After the completion of the second-generation Iridium system abroad, SpaceX’s starlink system and Oneweb’s Oneweb system are both in the process of construction; domestic low-orbit constellation systems such as Hongyan and Hongyun are also Planning and construction. [0003] In addition to the gravitational force of the center of the earth, satellites in space will also be affected by various perturbations such as the oblateness of the earth, the gravitational force of the sun and the moon, atmospheric resistance, and solar light pressure. Low-orbit satellites generally operate between 500km and 1500km. Satellites are more perturbed by atmospheric resistance, and i...

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Problems solved by technology

[0004] SpaceX's starlink system uses electric propulsion technology to maintain satellite orbits, but the electric propulsion power demand is large, so it brings a greater burden on the satellite platform; in addition, this method is not suitable for low-orbit navigation constellations, because electric propulsion It is a low-thrust long-time orbit change mechanism. During the satellite orbit change process, the navigation service of low-orbit satellites will be interrupted for a long time, which is not conducive to the business development of low-orbit navigation constellations.

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