Method for improving attitude measurement accuracy of star sensor

A technology of star sensor and measurement accuracy, applied in the field of satellite analysis, can solve problems such as the undesired low frequency error of star sensor, and achieve the effect of improving attitude measurement accuracy and improving determination accuracy

Inactive Publication Date: 2018-07-27
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

Therefore, these methods are not advisable to deal with the low frequency error of the star sensor

Method used

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  • Method for improving attitude measurement accuracy of star sensor
  • Method for improving attitude measurement accuracy of star sensor
  • Method for improving attitude measurement accuracy of star sensor

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[0020] 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.

[0021] Such as figure 1 As shown, the method for improving star sensor attitude measurement accuracy provided by the present invention includes:

[0022] 101. Establish a satellite attitude determination system model, thereby obtaining the state estimation value of the satellite attitude;

[0023] 102. Subtracting the mean value from the gyro drift estimation value in the state estimation value to obtain a sample sequence;

[0024] 103. Perform discrete Four...

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Abstract

The invention relates to a method for improving the attitude measurement accuracy of a star sensor, belonging to the field of satellite analysis. The method comprises the following steps: establishinga satellite attitude determination system model so as to acquire the estimated state value of satellite attitude; subtracting an estimated gyroscopic drift value from the estimated state value so asto obtain a sample sequence; subjecting the sample sequence to discrete Fourier transform so as to obtain the frequency spectrum of the sample sequence and reading the frequency of the errors of the estimated gyroscopic drift value form the frequency spectrum of the sample sequence; estimating the amplitude of the periodic errors of gyroscopic drift so as to calculate the estimated amplitude valueof the low-frequency errors of the star sensor; establishing a reference model for the low-frequency error of the star sensor based on the frequency of the periodic errors of gyroscopic drift and theestimated amplitude value of the low-frequency errors of the star sensor; and updating the estimated state value of the satellite attitude according to the reference model for the low-frequency errors of the star sensor. The method provided by the invention fully takes the influence of the low-frequency errors of the star sensor on the attitude of the star sensor into consideration, so the attitude measurement accuracy of the star sensor is improved.

Description

technical field [0001] The invention relates to the field of satellite analysis, in particular to a method for improving the attitude measurement accuracy of a star sensor. Background technique [0002] High-precision pointing satellites widely use an attitude determination system composed of star sensors and gyroscopes, and use Kalman filters to process measurement data to obtain satellite attitude estimates. One of the conditions to ensure the optimality of Kalman filtering is to require the system noise and measurement noise to be Gaussian white noise. It is reasonable to approximate the measurement error of the star sensor as Gaussian white noise when the accuracy of attitude determination is not high. However, with the development of high-resolution earth observation satellites, higher and higher requirements are put forward for the accuracy of satellite attitude determination. Satisfy the accuracy index requirement of satellite attitude determination. [0003] In fa...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C25/00
CPCG01C25/00
Inventor 王炯琦陈彧赟何章鸣周海银矫媛媛周萱影侯博文孙博文
Owner NAT UNIV OF DEFENSE TECH
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