Abstract
Micro Inertial Measurement Unit (MIMU) has given Inertial Measurement Unit (IMU) a widely application respective. In this paper, we study the application of MIMUl magnetometer integrated system on the attitude determination of micro satellite. Based on the principle of MIMU and the` measurement of magnetometer, MIMU/magnetometer system is integrated. Through designing the simulatien models of attitude determination for micro satellite, consisted of< the `SGP4 orbit model, the IGRF model and the satellite dynamic model, we do the simulation research. Simulation results with EKF show that, in 1/3 orbit time, the measurement error of attitude angular is controlled within 0.5 deg, meeting the requirement of the micro satellite attitude determination. In addition, we compare the UKF results with the EKF and find the UKF results converge faster than the EKF while the state estimate precision of the two filters are comparable.
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