A method for on-orbit real-time compensation of low-frequency errors of star sensors

A star sensor, low-frequency error technology, applied in the field of spacecraft attitude determination, can solve problems affecting satellite pointing accuracy, remote sensing image positioning accuracy, inability to accurately quantitatively evaluate payload performance, etc., so as to reduce the impact and overcome low-frequency Influence of errors and the effect of improving the accuracy of attitude determination

Active Publication Date: 2017-07-28
BEIJING INST OF CONTROL ENG
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Problems solved by technology

This simplified model cannot accurately reflect the attitude determination accuracy of the satellite, and cannot accurately and quantitatively evaluate the impact of attitude determination accuracy on the payload performance
[0007] 2. Affect satellite pointing accuracy
[0009] 3. Affect the positioning accuracy of remote sensing images
[0010] In ground image processing, due to the existence of low-frequency errors, the positioning accuracy of remote sensing images is affected

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  • A method for on-orbit real-time compensation of low-frequency errors of star sensors
  • A method for on-orbit real-time compensation of low-frequency errors of star sensors
  • A method for on-orbit real-time compensation of low-frequency errors of star sensors

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Embodiment

[0067] The star sensor measurement error is modeled as the sum of random noise and low frequency error. The random error of the optical axis pointing of star sensor 1 is 3" (3σ). The low-frequency error of the star sensor is considered to be five times the frequency of the fundamental frequency. The values ​​of the low-frequency error parameters of the three axes of the star sensor are shown in Table 1. There is a low-frequency error in the sensor, and the 7-day satellite three-axis attitude error curve is as follows figure 2 shown.

[0068] Table 1 Star sensor low frequency error parameters

[0069]

[0070] (1) Error Quaternion Calculated as follows

[0071] δq x =φθ LFEx ;

[0072] δq y =φθ LFEy ;

[0073] δq z =φθ LFEz ;

[0074]

[0075] Among them, φ=[1 cos(τ) sin(τ) cos(2τ) sin(2τ) cos(3τ) sin(3τ)], τ=ω LFE t Abs ; LFE =7.2722×10 -5 , t Abs is the absolute star time; the amplitude θ of the cosine and sine signals in the Fourier series LFEx=[0 0...

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Abstract

The invention discloses an on-orbit real-time compensating method for low-frequency errors of a star sensor. The low-frequency errors produced by temperature distortion and the like of the star sensor are compensated in real time in an on-orbit mode by taking imaging effective load as attitude reference, observing to obtain posture change of the star sensor relative to the effective load and fitting with Fourier series. After the low-frequency errors are compensated in real time, the satellite attitude determining precision can be improved, the interferences of low-frequency errors are eliminated, and the satellite high-precision imaging and image positioning are facilitated.

Description

technical field [0001] The invention belongs to the field of attitude determination of spacecraft, and relates to a high-precision attitude determination of a satellite platform. Background technique [0002] High-precision pointing satellites widely use star sensors to measure satellite attitude. For satellite attitude determination systems, in the past few decades, people usually approximate the measurement errors of star sensors as Gaussian white noise. This approximation is reasonable when the accuracy of attitude determination is not high. In recent years, the development of high-resolution earth observation satellites has put forward higher and higher requirements for the accuracy of satellite attitude determination. In this case, the method of approximating the measurement error of the star sensor as Gaussian white noise cannot meet the accuracy requirements of satellite attitude determination. [0003] In fact, the measurement error of star sensor can be divided i...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C25/00G01C21/02
CPCG01C21/025G01C25/00
Inventor 汤亮陈守磊熊凯刘一武王楷胡少春郭廷荣
Owner BEIJING INST OF CONTROL ENG
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