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A Method of Improving the Accuracy of Satellite Attitude Determination

A satellite attitude and accuracy technology, applied in the field of improving the accuracy of satellite attitude determination, can solve the problems of filter performance degradation, lack of basis for filtering parameters, and difficulty in filtering parameters, etc., to improve the accuracy of satellite attitude determination, overcome residual residuals, and improve attitude determination The effect of precision

Active Publication Date: 2020-04-21
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, in theory, there is no basis for artificially adjusting the filtering parameters.
In practice, it is often difficult to manually adjust the filtering parameters, and improper selection of parameters will cause the filtering performance to decline

Method used

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  • A Method of Improving the Accuracy of Satellite Attitude Determination
  • A Method of Improving the Accuracy of Satellite Attitude Determination
  • A Method of Improving the Accuracy of Satellite Attitude Determination

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Embodiment Construction

[0016] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some of the embodiments of the present invention, not all of them. 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.

[0017] Such as figure 1 As shown, the method for improving satellite attitude determination accuracy provided by the present invention includes:

[0018] 101. According to the relative installation error of the star sensor, construct the uncertainty system model of the satellite attitude determination system;

[0019] 102. Normalize the uncertain system model into an iterative structural form of a robust filtering algorithm;

[0020] 103. Based o...

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Abstract

The invention belongs to the field of satellite analysis, and especially relates to a method used for increasing satellite attitude determination precision. The method comprises following steps: a uncertainty system model of a satellite attitude determination system is constructed based on the relative installation error of a star sensor; the uncertainty system model is subjected to standardization so as to obtain a Robust filtering algorithm iteration structure form; the weighting matrix in the Robust filtering algorithm iteration structure form is determined based on estimated error least squares optimization; a novel Robust filtering algorithm is constructed based on the Robust filtering algorithm iteration structure form and the weighting matrix; the novel Robust filtering algorithm isadopted for data processing of satellite attitude measuring data. The method is capable of inhibiting influences of star sensor relative installation error on satellite attitude determination, and increasing satellite attitude determination precision.

Description

technical field [0001] The invention relates to the field of satellite analysis, in particular to a method for improving the accuracy of satellite attitude determination. Background technique [0002] The star sensor / gyro combined attitude determination mode takes the gyro as the reference, the star sensor corrects the gyro drift, and uses the Kalman (Kalman) filter to process the measurement data to obtain the estimated value of the satellite attitude. Kalman filtering is designed based on a linear state-space model, which requires the model form and parameters to be known precisely, and the system noise is Gaussian white noise. However, in the actual application process, since satellites (especially complex satellites) are inevitably affected by various environmental and satellite orbital factors such as vibration, jitter, temperature changes, and star deformation during orbital operation, the attitude of the star sensor The characteristics of the measurement error have c...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C21/02G01C21/16G01C21/18
CPCG01C21/02G01C21/165G01C21/18
Inventor 王炯琦陈彧赟周海银矫媛媛何章鸣周萱影侯博文
Owner NAT UNIV OF DEFENSE TECH
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