In-orbit identification method for relative installation error between single star sensors

Abstract

The invention provides an in-orbit identification method for relative installation error between single star sensors. The method comprises the steps of establishing a mathematical statistic model for star sensor measurement and installation error; establishing a star sensor relative installation error angle observation equation; designing an installation error angle optimal estimation algorithm and designing an installation error angle model nonlinear fitting method. The method is simple and effective, and the attitude and attitude angle speed of a spacecraft are not needed to be calculated. A star sensor relative installation error angle can be estimated under the situation that the dynamical variables are unknown. In the execution process of an actual task, the method is more practical and effective than an installation error angle estimation method which requires real-time acquisition of the attitude of the spacecraft, and compared with a conventional estimation method, the method has the advantages of being simpler and more convenient in data detection and estimation on a star due to the insensitivity for long-period data loss.

Description

technical field [0001] The invention relates to an installation error estimation technology between satellite sensors in the field of satellite high-precision attitude determination, in particular to an on-orbit identification method for relative installation error angles between single star sensors. Background technique [0002] Generally, multiple star sensors are installed on the platform body to deal with the maneuvering attitude and different orbital positions, which cause sunlight to enter the field of view of the main star sensor, and then start a stand-alone star sensor with suitable imaging conditions and lighting conditions to continuously obtain higher accuracy. High platform attitude information. In addition, the redundant use of multiple star sensors can also improve the reliability of the system. [0003] Due to the shock vibration during the launch of the spacecraft and the different illumination environments during orbital operation, there are long-period re...

AI Technical Summary

Problems solved by technology

[0005] (1) It is necessary to calculate the attitude angle or attitude angular velocity information of the spacecraft, and the requirements for information acquisition are relatively high;

[0006] (2) The noise characteristics of the star sensor itself are not used in the data estimation, and the accuracy is relatively low;

[0007] (3) It is sensitive to long-term data loss, and the robustness of the estimation method is low

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