A design and implementation method of sub-arc-second high-precision attitude determination for remote sensing satellites

Abstract

The invention relates to a sub-arc-second level remote sensing satellite high-precision attitude determination design and implementation method. Install a high-precision star camera, star sensor, and vibratory gyro measurement equipment on the high-resolution optical load backplane with a common reference, and install a three-axis fiber optic gyro on the satellite platform. Together with the high-resolution optical payload, the above-mentioned equipment adopts a unified high-precision time reference. Firstly, the star sensor and the three-axis fiber optic gyroscope are used for on-orbit real-time combined attitude determination, and the attitude determination accuracy reaches the order of arc seconds in real time. Accuracy is combined with attitude determination, and the attitude determination accuracy finally reaches the sub-arc second level. The invention can improve the accuracy and stability of attitude determination by an order of magnitude at the same time, and can achieve sub-arcsecond attitude determination accuracy for each imaging pixel point when the optical load is scanned and imaged in each line, which is very suitable for wireless remote sensing of optical remote sensing satellites. High-precision geometric positioning requirements for control points.

Description

technical field [0001] The invention belongs to the technical field of attitude control of remote sensing satellites, in particular to a sub-arc-second-level high-precision attitude determination design and implementation method of remote sensing satellites. Background technique [0002] High-precision attitude determination of high-resolution optical remote sensing satellites is a key problem that restricts high-precision geometric processing and applications. At present, in the high-precision three-axis stable satellites operating in orbit at home and abroad, a high-precision attitude measurement system composed of gyroscopes and star sensors is generally used. The state equation is established through the kinematic laws of the satellite, and the output of the gyroscope and star sensors is passed through A certain information fusion algorithm is used to obtain the attitude information of the satellite. The star sensor works in the real-time dynamic measurement mode, and i...

AI Technical Summary

Problems solved by technology

However, in order to achieve sub-arc-second attitude determination, that is, less than 1 arc-second attitude determination, the traditional star sensor can no longer meet its measurement accuracy requirements

At present, the sub-arc-second very high-precision star sensor technology is immature, and it is expensive, heavy, bulky, and power-consuming. The huge cost of the above costs is not suitable for the application of small satellites

Moreover, the data update rate of the star sensor is only about 10Hz at most, and it cannot measure the rapid changes of the camera pointing in real time. New measures need to be adopted to further improve the measurement accuracy

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