An Accelerometer Calibration Method Based on Attitude Information
An accelerometer and attitude information technology, applied in the field of deep space exploration, can solve the problems of poor calibration accuracy of the accelerometer, achieve the effect of improving the calibration accuracy and ensuring the performance of autonomous navigation
Inactive Publication Date: 2018-06-19
BEIJING INSTITUTE OF TECHNOLOGYGY
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Aiming at the problem of poor accelerometer calibration accuracy in the absence of position measurement information in the prior art
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Abstract
The invention discloses an accelerometer calibration method based on attitude information, relates to an accelerometer calibration method, and belongs to the technical field of deep space detection. In order to calibrate the accelerometer in the absence of position measurement information, the present invention adopts the gyroscope-free inertial navigation method, derives the accelerometer output model, uses the attitude determination system output, and combines the nonlinear filtering method to estimate the accelerometer drift and recalculate Accelerometer drift and corresponding error variance matrix, the accelerometer drift and corresponding error variance matrix are input into the nonlinear filter, the accelerometer drift is estimated, the accelerometer calibration is completed, the calibration accuracy is improved, and the autonomous navigation performance of the atmospheric entry section is guaranteed. The technical problem to be solved by the present invention is to improve the calibration accuracy of the accelerometer in the approaching section of the planet in the absence of position measurement information, and ensure the autonomous navigation performance in the atmospheric entry section.
Description
technical field The invention relates to an accelerometer calibration method, in particular to an attitude information-based accelerometer calibration method, which belongs to the technical field of deep space detection. Background technique The inertial navigation scheme based on the inertial measurement unit is the preferred way of autonomous navigation in the entry stage of the recent planetary landing exploration mission. Inertial navigation calibration during planetary approach is therefore a necessary step to reduce drift accumulation over time. The attitude determination system of the planetary approach section can use attitude sensitive elements such as star sensors and sun sensors to accurately calibrate the gyroscope, but the calibration of the accelerometer often depends on the position measurement information, and because the position measurement information of the planetary approach section detector Information is scarce, so the problem of accelerometer calibra...
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Patent Type & Authority Patents(China)
IPC IPC(8): G01P21/00
Inventor 于正湜崔平远朱圣英高艾秦同
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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