Method for correcting in-orbit real-time interaction of double star sensors

A technology of double star sensor and star sensor, which can be used in instruments, measuring devices, navigation calculation tools, etc., can solve the problems of measurement noise error, slow variation error, affecting imaging accuracy and quality, etc.

Active Publication Date: 2017-01-18
SHANGHAI AEROSPACE CONTROL TECH INST
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Problems solved by technology

It is often not enough to ensure the calculation accuracy of the satellite attitude by improving the measurement accuracy of the sensor and the attitude determination algorithm. In addition to the measurement noise error of the star sensor itself, the slow change between the optical measurement reference of the

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  • Method for correcting in-orbit real-time interaction of double star sensors
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  • Method for correcting in-orbit real-time interaction of double star sensors

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Embodiment Construction

[0070] The following combination figure 1 , a preferred embodiment of the present invention is described in detail.

[0071] Such as figure 1 As shown, the correction method for the real-time interaction of the double star sensor provided by the present invention uses the attitude information output by one of the star sensors to compensate the deviation of the attitude information output by the other sensor in real time, including the following steps:

[0072] S1, according to the satellite attitude quaternion information output by the first star sensor ST1, and the installation relationship between the first star sensor ST1 and the satellite body, obtain the quaternion information of the satellite body coordinate system relative to the earth-centered inertial coordinate system;

[0073] S2. According to the satellite attitude quaternion information output by the second star sensor ST2, and the installation relationship between the second star sensor ST2 and the satellite bod...

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Abstract

The invention relates to a method for correcting in-orbit real-time interaction of double star sensors. The method comprises the steps of obtaining quaternion information of a satellite body coordinate system based on a first star sensor and a second star sensor relative to an earth core inertial coordinate system according to satellite attitude quaternion information output by the first star sensor and the second star sensor and an installation relationship between a satellite body and the first star sensor and the second star sensor, and performing synchronous calculation with current time calculated by an on-star track; calculating corrected deviations of real-time interaction between the first star sensor and the second star sensor according to the quaternion information of the satellite body coordinate system based on the two star sensors having undergone time synchronization relative to the earth core inertial coordinate system, and finally performing real-time interaction correction on the first star sensor or the second star sensor. According to the method, attitude deviations resulting from slow variation and shape change between the star sensors and a satellite reference can be reduced, and high-precision triaxial attitude determination precision of the satellite is guaranteed.

Description

technical field [0001] The invention relates to a correction method for on-orbit real-time interaction of double-star sensors, in particular to a deviation correction method for on-orbit real-time interaction when a high-precision satellite takes a double-star sensor as an attitude reference. Background technique [0002] In order to ensure the accuracy of satellite control, it is first necessary to ensure the accuracy of satellite attitude determination. It is often not enough to ensure the calculation accuracy of the satellite attitude by improving the measurement accuracy of the sensor and the attitude determination algorithm. In addition to the measurement noise error of the star sensor itself, the slow change between the optical measurement reference of the star sensor and the whole star control reference The error, the deformation deviation between the payload and the whole star reference, and the attitude deviation caused by the thermal deformation between the star se...

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Application Information

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IPC IPC(8): G01C25/00G01C21/20
CPCG01C21/20G01C25/00
Inventor 郭思岩王文妍钟金凤张艳召石晓涵张云霞李小斌
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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