Method for online identification and compensation of orbital period system error between star sensors

A system error and orbital period technology, applied in navigation calculation tools, integrated navigators, etc., can solve problems such as insufficient accuracy and insufficient autonomy, and achieve the effect of solving low accuracy and realizing online identification.

Active Publication Date: 2018-03-02
SHANGHAI AEROSPACE CONTROL TECH INST
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Problems solved by technology

[0007] The purpose of the present invention is to provide a method for online identification and compensation of orbit period system e

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  • Method for online identification and compensation of orbital period system error between star sensors
  • Method for online identification and compensation of orbital period system error between star sensors
  • Method for online identification and compensation of orbital period system error between star sensors

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Embodiment Construction

[0042] The present invention will be further elaborated below by describing a preferred specific embodiment in detail in conjunction with the accompanying drawings.

[0043] Such as Figure 1~3 As shown, an online identification and compensation method for the orbital period system error between star sensors, including:

[0044] S1, divide the track into N parts equally, and get N+1 samples;

[0045] S2, if the current position of the spacecraft is at the sample point, calculate the attitude transfer quaternion between the star sensor to be compensated and the reference star sensor at the current moment, and calculate the attitude transfer quaternion and the nominal attitude transfer quaternion deviation to obtain the systematic error between the star sensor to be compensated and the reference star sensor;

[0046] S3. Based on the N+1 sample points, use a linear interpolation algorithm to invert to obtain the systematic error between the star sensor to be compensated and th...

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Abstract

The present invention discloses a method for online identification and compensation of orbital period system error between star sensors. The method comprises: S1, equally dividing an orbit into N parts to obtain N+1 sample points; S2, if the current spacecraft is positioned at the sampling point, calculating the attitude transfer quaternion between a star sensor to be compensated and a reference star sensor at the current moment, and calculating the deviation between the attitude transfer matrix and a nominal attitude transfer quaternion to obtain the system error of the star sensor to be compensated and the reference star sensor; and S3, based on the N+1 sample points, inverting by using a linear interpolation algorithm to obtain the system error of the star sensor to be compensated and the reference star sensor at any position of the orbit, and compensating.

Description

technical field [0001] The invention relates to the field of spacecraft attitude and orbit control, in particular to an on-line identification and compensation method for orbit period system error between star sensors. Background technique [0002] As the key measurement component of the spacecraft attitude and orbit control system, the star sensor is also used as the attitude measurement reference of the satellite. Generally, the satellite is equipped with 2 to 4 star sensors. Due to the influence of factors such as the on-orbit thermal environment, the systematic error between the star-min and the star-min often manifests as an orbital period characteristic, and the magnitude of the deformation generally does not exceed 0.1°. [0003] When it is necessary to use multi-satellite sensor data fusion to improve the accuracy of satellite attitude measurement, it is necessary to eliminate systematic errors between star sensors in real time. There are two main traditional method...

Claims

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Application Information

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IPC IPC(8): G01C21/20G01C21/24
CPCG01C21/20G01C21/24
Inventor 尹海宁叶立军徐樱刘刚袁彦红王世耀邵志杰李芳华陈殿印
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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