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

A geostationary orbit, slowly changing error technology, applied in the direction of measuring devices, instruments, etc., can solve the problem of inability to correct the slow changing error of the star sensor, affecting the measurement accuracy of the star sensor, the optical system of the star sensor and the slow change of the imaging spot, etc. question

Active Publication Date: 2017-11-28
SHANGHAI AEROSPACE CONTROL TECH INST
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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-pr

Method used

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

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[0076] The present invention provides a method for predicting and correcting the star-sensitivity slow-variation error of a geostationary orbit satellite. In order to make the present invention more obvious and understandable, the present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

[0077] Such as figure 1 Shown, a kind of geostationary orbit satellite star-sensitivity slow-variation error forecast correction method of the present invention, its steps are as follows:

[0078] Step S1: Calculate the attitude measurement error of the star sensor according to the attitude determination error calibrated by the payload;

[0079] Let the attitude of the load calibration be The fixed attitude angle of the star sensor is but:

[0080]

[0081]

[0082] Then the attitude measurement error matrix C of the star sensor bbr for:

[0083]

[0084] in:

[0085] is the roll angle of the load,

[0086] θ...

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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...

Claims

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Application Information

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IPC IPC(8): G01C25/00
CPCG01C25/00
Inventor 周连文马雪阳何益康余维李苗
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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