Low-orbit constellation phase preserving parameter estimation method

Abstract

The invention discloses a low-orbit constellation phase retention parameter estimation method, and belongs to the technical field of satellite orbit control. According to the method, the orbit semi-major axis measurement value output by satellite-borne GNSS orbit determination is not directly used, the latitude argument measurement value with high precision is used for indirectly estimating the orbit semi-major axis flat root, the orbit determination precision of an existing GNSS receiver is not improved, the high-precision requirement of satellite constellation maintenance on the orbit semi-major axis can be met, and the double-frequency GNSS receiver with a higher price is prevented from being configured on a satellite; and after the relative latitude argument measurement value is converted into the flat root, polynomial fitting is carried out, then polynomial fitting is carried out on the variation trend of the orbit semi-major axis flat root by utilizing the variation relationship between the relative latitude argument flat root and the orbit semi-major axis flat root, and the fitting coefficient is calculated, so that the orbit semi-major axis flat root at any moment is indirectly estimated, the precision of the semi-major axis flat root is superior to 1m, and constellation phase keeping can be completed based on a single-side drift ring control strategy under the condition that any semi-major axis attenuation rate is met.

Description

technical field [0001] The invention relates to a low-orbit constellation phase maintenance parameter estimation method, which belongs to the technical field of satellite orbit control. Background technique [0002] The low-orbit constellation needs to maintain a relatively stable configuration during operation to prevent changes in the coverage characteristics of the ground. Limited by the accuracy of orbit determination and orbit control, the initial orbit parameters of satellites in orbit deviate from the design parameters, resulting in changes in the relative orbit parameters between satellites, which will gradually destroy the relative configuration of the constellation; in addition, satellites in the long-term operation process It is affected by various environmental perturbations, such as the gravitational field perturbation of the earth, the gravitational perturbation of the sun and the moon, the weather resistance perturbation, and the light pressure perturbation. ...

AI Technical Summary

Problems solved by technology

Since solar activities affect the atmospheric density, the decay rate of the semi-major axis also changes accordingly. When the decay rate of the semi-major axis is small, the adjustment of the flat root of the semi-major axis of the satellite relative to the reference orbit is too large, which will cause the latitude of the satellite relative to the reference orbit. The flat root of the argument drifts out of the left boundary of the control box, resulting in poor phase keeping accuracy between co-orbiting satellites

[0006] At present, low-orbit constellation satellites generally use on-board GNSS navigation receivers to achieve autonomous orbit determination on the satellite. The root mean square error of the semi-major axis of the orbit is generally greater than 10m. The relative latitude angle exceeds the boundary of the control box, which leads to the failure of the unilateral drift loop control strategy

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