A new method for orbit and attitude determination of satellite simultaneously based on Three-Axis-Magnetometer (TAM) and gyro data is presented, which is a breakthrough in traditional pattern of treating orbit and attitude of satellite separately. Considering of the nonlinear system, a modified Unscented Kalman Filter is developed. The magnetic field components are used to update as measurement and the gyro data are used to propagate the state vector. Because of the constraint of the quaternion, an error vector update approach is proposed. Numerical simulations are given at last, and the algorithm is confirmed to be feasible and effective.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Modified UKF for integrated orbit and attitude determination based on gyro and magnetometer


    Contributors:
    Yanjun Xing, (author) / Xibin Cao, (author) / Shijie Zhang, (author)


    Publication date :

    2008-12-01


    Size :

    565815 byte




    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English



    Magnetometer-Only Attitude and Rate Determination for a Gyro-less Spacecraft

    Natanson, G. A. / Challa, M. S. / Deutschmann, J. et al. | British Library Conference Proceedings | 1994




    GYRO STELLAR ATTITUDE DETERMINATION

    Ghezal, M. / Polle, B. / Rabejac, C. et al. | British Library Conference Proceedings | 2006


    Attitude and orbit determination for small satellite using magnetometer measurement

    Jianqi, Wang / Xibin, Cao / Zhaowei, Sun | Emerald Group Publishing | 2003