Method for forecasting and correcting star-sensitive slow-varying errors for geostationary orbit satellite

Abstract

The invention discloses a method for forecasting and correcting star-sensitive slow-varying errors for a geostationary orbit satellite. The method mainly comprises the following steps: 1, determining an error according to a load calibrated attitude, and calculating an attitude measurement error of a star sensor; 2, calculating a measurement error in a star sensor measuring system according to an installation matrix of the star sensor; 3, fitting a slow-varying error of the star sensor by the measurement error data by virtue of a segmented multi-order Fourier function; 4, calculating fixed star time differences at a forecast date and a calibration date according to a transformational relation between local time and sidereal hour angle; 5, forecasting the attitude measurement error of the star sensor by utilizing the fitted slow-varying error of the star sensor; and 6, calculating the corrected attitude determination angle according to a measurement model of the star sensor. According to the method disclosed by the invention, high-precision attitude reference can be provided for image navigation and registration, and the image registering precision of an optic remote sensing satellite can be effectively improved.

Description

technical field [0001] The invention relates to the field of forecasting and correcting slow-varying errors of star sensors, in particular to a method for forecasting and correcting slow-varying errors of satellites in geostationary orbits. Background technique [0002] With the continuous development of earth observation satellites, people have put forward higher requirements for the attitude control accuracy and stability of satellites, especially for high-precision optical remote sensing satellites, which also require satellite platforms to have high attitude determination accuracy, which is the basis for image navigation and registration. Provide high-precision attitude reference. Due to the change of the space environment temperature and the solar thermal effect, the optical system and imaging spot of the star sensor will be slowly changed, thus affecting the measurement accuracy of the star sensor. The commonly used method on the star is to use high-precision gyro com...

AI Technical Summary

Problems solved by technology

Due to the change of the space environment temperature and the solar thermal effect, it will have a slowly changing influence on the optical system and imaging spot of the star sensor, thus affecting the measurement accuracy of the star sensor

The commonly used method on the star is to use high-precision gyro combination and high-precision star sensor combined with Kalman filter to determine the attitude to achieve high-precision attitude, but it cannot correct the slowness caused by the influence of space environment temperature and solar thermal effect on the star sensor. variable error

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