Adaptive Modulation Method of Drag Coefficient Based on Precise Ephemeris

Abstract

The invention provides a resistance coefficient self-adaptive modulation method based on precise ephemeris, combined with station measurement data and high-precision dynamic model to optimize and correct the resistance modulation coefficient in TLE data, and analyzes the contour satellite under the condition of space environment change The correlation of the correction, using the correlation between the TLE data and the precise ephemeris of the contour satellite on the same day, designed the orbit prediction algorithm of the TLE+SGP4 model when the satellite is difficult to obtain enough external measurement data, and improved the orbit prediction algorithm in the case of severe changes in the space environment. TLE short-term forecast accuracy for the period. The invention can realize self-adaptive modulation of abnormal satellite resistance coefficient, has strong adaptability and improves prediction accuracy.

Description

technical field [0001] The invention belongs to the field of aerospace measurement and control, and is suitable for improving the orbit prediction accuracy of my country's low-orbit satellites in the abnormal space environment. Background technique [0002] The orbit prediction of my country's LEO satellites generally adopts two methods based on precise ephemeris and network data (TLE data). When the satellite is normal, the method based on precise ephemeris can meet the needs of satellite daily tracking. However, when the satellite is abnormal due to no available tracking measurement data, and the extrapolation time exceeds a certain time range, the method based on the precise ephemeris will be difficult to meet the tracking accuracy requirements, and the method based on TLE two-line radicals is usually used for orbit prediction . For low-orbit satellites, the atmospheric drag directly related to atmospheric density is an important source of error in orbit forecasting. Th...

AI Technical Summary

Problems solved by technology

The existing drag coefficient optimization algorithms generally use the precise ephemeris of the satellite to be solved for the drag coefficient in the calm period of the space environment to solve the atmospheric drag coefficient of multiple arcs, which is poor in adaptability to the space environment. And when the space environment changes violently and the satellite has no measurement data anomalies, resulting in no precise ephemeris, this method cannot solve the drag coefficient

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