Real-time on-orbit correction method of slow varying errors among plurality of star sensors

Abstract

The invention provides a real-time on-orbit correction method of slow varying errors among a plurality of star sensors. The slow varying errors between every two head parts of the star sensors are corrected. The method comprises the following steps of S1, calculating the coordinate conversion quaternion filtering practical measuring value Q[RotOHiOHjCAL] between every two head parts of the star sensors; S2, specifying a certain head part on the star sensor as a reference head part OHref by a ground control center; S3, calculating the coordinate conversion quaternion ground precise measuring value Q[OHiOHref] from the reference head part OHref to each head part OHi of the star sensors; S4, calculating the coordinate conversion quaternion practical measuring value Q[RotOHiOHref] from each head part OHi of the star sensors to the reference head part OHref; S5, calculating each head part posture quaternion q[OHiRc] after the correction of the slow varying errors between the head parts according to the Q[OHiOHref] and the Q[RotOHiOHref] obtained in the S3 and S4. The method can realize the on-orbit real-time estimation and correction; by using a simple calculation mode, the posture determination precision of the combined fixed posture of the plurality of star sensors is improved; the slow varying errors between the non-reference head parts and the reference head parts is simply and effectively corrected; the head part posture quaternion after the correction of the slow varying errors between the head parts is obtained.

Description

technical field [0001] The invention relates to the technical field of attitude correction of satellite sensors, in particular to a method for real-time on-orbit correction of slow-varying errors among multi-satellite sensors. Background technique [0002] With the continuous development and development of aerospace science and technology and application fields, there are two trends in the development and implementation of satellites: one is represented by high-precision remote sensing satellites. Extremely high; the other direction is to develop towards small, fast, low-cost, simplified structure and configuration, to achieve a single task, or to achieve multi-task or a certain complex work by launching a large number. For the complex satellites of the former trend, the control system usually configures the star sensor as the attitude sensor component. [0003] The star sensor is currently the most accurate attitude measurement sensor used on satellites. It measures the or...

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Problems solved by technology

[0004] During the satellite’s in-orbit operation, the temperature is periodically and slowly changed by the sun’s irradiation angle. Therefore, the installation structure of the star sensor will be affected by it and deform, resulting in a dynamic deviation of the star sensor’s measurement output relative to the body’s coordinate system reference.

In addition, when the star sensor observes stars, the sky area pointed by its optical axis changes periodically with the orbital movement of the satellite, resulting in optical system errors, calibration errors, and star catalog errors changing with stars entering and leaving the field of view, which will also cause periodic These changes affect the attitude quaternion of the star sensor reference head and non-reference head, and then affect the attitude determination accuracy of the joint attitude determination of the multi-satellite sensor

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