Method and system for evaluating on-orbit measurement precision of multi-probe star sensor

Abstract

The invention provides a method and system for evaluating the on-orbit measurement precision of a multi-probe star sensor. The method comprises the steps of acquiring on-orbit measurement data, identifying on-orbit data validity, correcting aberration, synchronizing exposure time, calculating an included angle between an optical axis and a horizontal axis, evaluating constant deviation of the star sensor, evaluating thermoelastic errors and view field space errors of the star sensor and evaluating a noise equivalent angle error. According to the invention, external factors such as errors caused by installation deformation of the star sensor and spacecraft control errors can be effectively avoided, combined attitude determination operation is not involved, the problem of satellite motion can be solved, spacecraft orbit information is not needed. The method can accurately evaluate constant deviation, thermoelastic errors, view field space errors and noise equivalent angle errors of the star sensor.

Description

technical field [0001] The invention relates to the field of optoelectronic technology, in particular to a method and system for evaluating the on-orbit measurement accuracy of a multi-head star sensor. Background technique [0002] The star sensor is a high-precision space attitude measurement device that takes the star as the reference system and the starry sky as the working object. It is the most precise attitude measurement component with the least drift so far. It often provides accurate space orientation and reference for satellites. And like the inertial gyroscope, it has the ability of autonomous navigation and has extremely important application value. With the development of star sensor technology and its basic functions, the application fields of star sensors are becoming more and more extensive. As a high-precision inertial attitude measurement instrument, the star sensor not only affects the satellite attitude control accuracy, but also directly determines the...

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Problems solved by technology

[0005] Patent document CN102735260B (application number: CN201210203660.0) discloses a method for determining the on-orbit measurement error of a star sensor, and proposes to describe the measurement error according to the star sensor body, which is divided into low-frequency error, high-frequency error, and random error, but Stellar aberration is not corrected and the exposure time between multiple star sensors is not compensated, so that the determined low-frequency error contains aberration and time asynchronous errors, which cannot truly reflect the measurement accuracy of star sensitivities

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