Sub-arc-second remote sensing satellite high-precision attitude determination design and implementation method

Abstract

The invention relates to a sub-arc-second remote sensing satellite high-precision attitude determination design and implementation method. A high-precision star camera, a star sensor and vibration measuring gyroscope measuring equipment are fixedly connected and mounted on a high-resolution optical load back plate in a co-reference manner, and a three-axis fiber-optic gyroscope is mounted on a satellite platform. The devices and a high-resolution optical load all adopt a unified high-precision time reference. Firstly, the star sensor and the three-axis fiber-optic gyroscope are used for carrying out on-orbit real-time combined attitude determination, the attitude determination precision reaches an arc second level in on-orbit real-time, then the high-precision star camera, vibration measurement gyroscope measurement data and the star sensor are used for carrying out high-precision combined attitude determination on the ground, and the attitude determination precision finally reaches a sub arc second level. The precision and the stability of attitude determination can be improved by one order of magnitude at the same time, sub-arc-second attitude determination precision can be realized by each imaging pixel point when each line of scanning imaging of the optical load is refined, and the method is quite suitable for the control-point-free high-precision geometric positioning requirement of the optical remote sensing satellite.

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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