Spacecraft Attitude and Pointing Error Identification Method Based on Landmark Information

Abstract

The invention provides a spacecraft attitude pointing error identification method based on road sign information. The method comprises the steps that 1, a mathematical statistic model for sensor vector measurement and installation error angles is built; 2, an installation error angle observation equation between a full attitude sensor and a single vector sensor is constructed; 3, an optimal estimation method is designed to estimate an installation error angle between the full attitude sensor and the single vector sensor within some interval; 4, data fitting is performed on error angle data within different intervals to obtain a basic time varying installation error angle equation. The pointing error identification method is simple and accurate, the attitude angle and the angular speed of a spacecraft do not need to be calculated, attitude data of the spacecraft do not need to be acquired in real time, insensitivity on long-term data loss is achieved, and the practicability is high.

Description

technical field [0001] The invention relates to a space vehicle on-orbit attitude pointing error determination technology, in particular to a space vehicle on-orbit attitude error estimation method based on landmark information. Background technique [0002] The on-orbit pointing accuracy index of remote sensing satellites is directly related to the accuracy level of target geographic location determination. The size of the spacecraft pointing error can comprehensively measure the spacecraft’s on-orbit attitude determination and attitude control. With the continuous improvement of space mission requirements, it is urgent to accurately give the spacecraft pointing error and make effective corrections. [0003] At present, the relevant domestic research work mainly focuses on the attitude determination of the spacecraft body, and there are few studies on the determination of the spacecraft pointing. The spacecraft experienced a strong impact during launch, and was affected by...

AI Technical Summary

Problems solved by technology

Therefore, the relevant results of determining the attitude of the spacecraft body cannot solve the problem of determining the orientation of the spacecraft

In addition, a small number of research results on the determination of spacecraft pointing errors need to use the attitude information of the spacecraft itself, and it needs to be identified through the data of several orbital cycles, and the requirements for data acquisition are relatively high.

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