Method for estimating output deviations of triaxial magnetometer

A three-axis magnetic and magnetometer technology, applied in the field of spacecraft control, can solve problems affecting the effect of spacecraft attitude control, magnetometer output deviation, attitude determination error, etc.

Inactive Publication Date: 2017-10-20
RESEARCH INSTITUTE OF TSINGHUA UNIVERSITY IN SHENZHEN
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Problems solved by technology

When the spacecraft is in orbit, due to the influence of space environmental factors, the output of the magnetometer may have a certain deviation
The d...

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  • Method for estimating output deviations of triaxial magnetometer
  • Method for estimating output deviations of triaxial magnetometer
  • Method for estimating output deviations of triaxial magnetometer

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[0043] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention. In the case of no conflict, the following embodiments and features in the embodiments can be combined with each other.

[0044] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the technical field of the invention. The terms used herein in the description of the present invention are for the purpose of describing specific embodiments only, and are not intended to lim...

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Abstract

The invention provides a method for estimating the output deviations of a triaxial magnetometer. The method is applied to spacecrafts. The output deviations of the triaxial magnetometer comprise a deviation vector and a deviation matrix. The method comprises the following steps: determining an attitude matrix from star coordinate system to track coordinate system by using a double-vector method; acquiring the measured value of the magnetometer; establishing a deviation model of the magnetometer which is used for defining the relationship among the measured value of the magnetometer, the deviation vector, the deviation matrix and the attitude matrix; and subjecting the deviation model to iterative operation in virtue of Kalman filtering so as to estimate the deviation vector and the deviation matrix in real time. The method provided by the invention is fast in calculation convergence, high in precision and applicable to spacecrafts with stable attitudes and has reference significance to error analysis, in-orbit correction and subsequent designing of the triaxial magnetometer and other triaxial vector sensors with similar measuring principles.

Description

technical field [0001] The invention belongs to the field of spacecraft control, in particular to an output deviation estimation method of a three-axis magnetometer. Background technique [0002] This section is intended to provide a background or context to a detailed description of the invention that is recited in the claims. The descriptions herein are not admitted to be prior art by inclusion in this section. [0003] In the aerospace field, a magnetometer is a common attitude sensor, which is mainly used for spacecraft attitude measurement. Because the magnetometer has low power consumption, light weight, and is less restricted by the environment, it can be used in conjunction with other attitude sensors to determine the attitude of the spacecraft. It is often used for attitude control of low-orbit-orbit spacecraft. When the spacecraft is in orbit, due to the influence of space environmental factors, the output of the magnetometer may have a certain deviation. The de...

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Application Information

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IPC IPC(8): G01C25/00
CPCG01C25/00
Inventor 靳瑾向蕾陈曦匡麟玲
Owner RESEARCH INSTITUTE OF TSINGHUA UNIVERSITY IN SHENZHEN
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