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Star sensor and gyro combined attitude determining method for processing multiplicative noise

A star sensor and multiplicative noise technology, applied in the field of satellite analysis, can solve problems not involved in the application level

Inactive Publication Date: 2019-03-15
FOSHAN UNIVERSITY
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Problems solved by technology

[0009] However, no one has done relevant research on non-dynamic linear systems with random multiplicative noise, and the current research does not involve specific application levels, especially the satellite attitude determination system composed of star sensor / gyroscope

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  • Star sensor and gyro combined attitude determining method for processing multiplicative noise
  • Star sensor and gyro combined attitude determining method for processing multiplicative noise
  • Star sensor and gyro combined attitude determining method for processing multiplicative noise

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Embodiment Construction

[0048] The concept, specific structure and technical effects of the present invention will be clearly and completely described below in conjunction with the embodiments and accompanying drawings, so as to fully understand the purpose, features and effects of the present invention. Apparently, the described embodiments are only some of the embodiments of the present invention, rather than all of them. Based on the embodiments of the present invention, other embodiments obtained by those skilled in the art without creative efforts belong to The protection scope of the present invention.

[0049] refer to figure 1 , the application of the present invention discloses a star sensor gyro combination attitude determination method for processing multiplicative noise, comprising the following steps:

[0050] Step 1, determine the expression and statistical characteristics of the multiplicative installation error;

[0051] Step 2, according to the state equation of the satellite attit...

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Abstract

The invention discloses a star sensor and gyro combined attitude determining method for processing multiplicative noise. The star sensor and gyro combined attitude determining method comprises the following steps: determining an expression of multiplicative installation errors and counting characteristics; establishing a satellite attitude determination system model with star sensor multiplicativeinstallation errors; discretizing and linearizing the satellite attitude determination system model to obtain a linear discrete system model; carrying out time updating on the system state of the linear discrete system model to obtain state filter parameters; transferring an error quaternion in the state filter parameters into an attitude Euler angle. According to the star sensor and gyro combined attitude determining method disclosed by the invention, the satellite attitude determination system model with the multiplicative installation errors of a star sensor and gyro combination is established on the basis of the error quaternion; an optimal attitude filtering algorithm based on linear minimum variance is designed by utilizing a linear minimum variance estimation and projection theorem; by use of an algorithm, suppression of multiplicative measurement noise of the star sensor and estimation of the satellite triaxial motion posture are realized, and the influence of the multiplicative measurement noise on posture determination precision is effectively reduced.

Description

technical field [0001] The invention relates to the technical field of satellite analysis, in particular to a method for determining the attitude of a star sensor / gyroscope combination used for processing multiplicative noise. Background technique [0002] The main task of satellite attitude determination is to estimate the attitude parameters of the satellite relative to a certain reference coordinate system based on the measurement value of the attitude sensor with noise. The attitude determination system is mainly composed of an attitude sensor and the corresponding information processing algorithm, namely the attitude determination algorithm. The attitude determination accuracy depends on the measurement accuracy of the attitude sensor and the accuracy of the attitude determination algorithm. [0003] The satellite attitude determination system is an important part of the satellite attitude control system. High-precision attitude determination is an important foundation ...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C25/00
CPCG01C25/00
Inventor 陈彧赟王炯琦何敏藩苗晴邢立宁王锐伍国华
Owner FOSHAN UNIVERSITY
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