In this paper the authors assume that they have measurements of a first difference of a typical satellite navigation carrier phase differential, which is a homogeneous quadratic function of the components of the attitude quaternion. They illustrate the determination of large or sustained attitudes using a dedicated unscented Kalman filter. The unscented Kalman filter structure was chosen for the dedicated filter because of its derivative free nature and other advantages. When a Gaussian distributed vector random variable is transformed to an equivalent quaternion it does not continue to be Gaussian distributed. For this reason, a new predictor-corrector form of the unscented Kalman filter is proposed to maintain the normalization of the unscented mean quaternion estimate in the presence of additive disturbances. The results from their realistic simulations indicate that the large attitude of a spacecraft can be estimated to within 0-1 % accuracy over large time frames. The filter is particularly useful for autonomous operations of spacecraft as well as in other applications where the process model is bilinear or second order in the states.


    Access

    Access via TIB

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Spacecraft large attitude estimation using a navigation sensor


    Additional title:

    Raumschiff-Orientierungsbestimmung mit Hilfe eines Navigationssensors


    Contributors:

    Published in:

    The Journal of Navigation ; 63 , 1 ; 89-104


    Publication date :

    2010


    Size :

    16 Seiten, 6 Bilder, 29 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English