A Correction Method for On-orbit Real-time Interaction of Binary Sensors

Abstract

The invention relates to a method for correcting in-orbit real-time interaction of double star sensors. The method comprises the steps of obtaining quaternion information of a satellite body coordinate system based on a first star sensor and a second star sensor relative to an earth core inertial coordinate system according to satellite attitude quaternion information output by the first star sensor and the second star sensor and an installation relationship between a satellite body and the first star sensor and the second star sensor, and performing synchronous calculation with current time calculated by an on-star track; calculating corrected deviations of real-time interaction between the first star sensor and the second star sensor according to the quaternion information of the satellite body coordinate system based on the two star sensors having undergone time synchronization relative to the earth core inertial coordinate system, and finally performing real-time interaction correction on the first star sensor or the second star sensor. According to the method, attitude deviations resulting from slow variation and shape change between the star sensors and a satellite reference can be reduced, and high-precision triaxial attitude determination precision of the satellite is guaranteed.

Description

technical field [0001] The invention relates to a correction method for on-orbit real-time interaction of double-star sensors, in particular to a deviation correction method for on-orbit real-time interaction when a high-precision satellite takes a double-star sensor as an attitude reference. Background technique [0002] In order to ensure the accuracy of satellite control, it is first necessary to ensure the accuracy of satellite attitude determination. It is often not enough to ensure the calculation accuracy of the satellite attitude by improving the measurement accuracy of the sensor and the attitude determination algorithm. In addition to the measurement noise error of the star sensor itself, the slow change between the optical measurement reference of the star sensor and the whole star control reference The error, the deformation deviation between the payload and the whole star reference, and the attitude deviation caused by the thermal deformation between the star se...

AI Technical Summary

Problems solved by technology

It is often not enough to ensure the calculation accuracy of the satellite attitude by improving the measurement accuracy of the sensor and the attitude determination algorithm. In addition to the measurement noise error of the star sensor itself, the slow change between the optical measurement reference of the star sensor and the whole star control reference The error, the deformation deviation between the payload and the whole star reference, and the attitude deviation caused by the thermal deformation between the star sensor and the whole star reference will ultimately affect the accuracy and quality of the imaging

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