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Predictive Unscented Kalman Filter for Gyroless Satellite Attitude Determination


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Predictive Unscented Kalman Filter for Gyroless Satellite Attitude Determination
LIAO He1WANG Ben-li1CAO Zheng-li2
1. Research Center of Satellite Technology,Harbin Institute of Technology,Harbin 150080,China; 2. Shenyang Aircraft Research and Design Institute,Shenyang 110035,China
model uncertainty initial attitude-error gyroless satellite attitude determination predictive unscented Kalman filter quaternion normalization
V448. 22
In order to reduce the reliance of gyroless satellite attitude determination on satellite attitude dynamic model and initial attitude information,a predictive unscented Kalman filter( UKF) is presented. The Taylor series expansion approach in predictive filter is used to estimate the model uncertainty of the unknown satellite attitude dynamics. It is propagated into UKF to estimate satellite attitude. Instead of the quaternion, the generalized three-dimensional attitude representation is used as the dynamic state to maintain the quaternion normalization in the filter. The simulation results indicate that the presented filter can estimate the satellite attitude accurately even when the big model uncertainty of satellite attitude dynamics and initial attitude-error exist in the meantime.


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Last Update: 2012-10-24