Spacecraft attitude control is described by a nonlinear dynamic mathematical model. When Euler parameters are used to define the orientation of a spacecraft with respect to an inertial frame, the model takes a certain form where the components of one factor are quadratic or higher order functions of the state vehicles. Large-angle maneuvers have traditionally been accomplished as a succession of small-angle rotations from a sequence of defined operating points about which the model is linearized. Alternatively, a sequence off single axis rotations are performed. These processes are computationally burdensome and are unable to produce fast multi-axial rotational maneuvers.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Nonlinear Methods for Spacecraft Attitude Maneuvers


    Beteiligte:
    A. L. Batten (Autor:in)

    Erscheinungsdatum :

    1985


    Format / Umfang :

    160 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Optimal Nonlinear Tracking of Spacecraft Attitude Maneuvers

    Tewari, Ashish / Sharma, Rajnish | AIAA | 2004


    Optimal nonlinear feedback control for spacecraft attitude maneuvers

    CARRINGTON, C. K. / JUNKINS, J. L. | AIAA | 1986


    Optimal Spacecraft Attitude Maneuvers via Adjoint Method

    Guo, Jian ;Yao, Yu ;He, Feng Hua | Trans Tech Publications | 2013


    Fuel Optimal Maneuvers with Spacecraft Attitude Constraints

    Zanon, Darren / Campbell, Mark | AIAA | 2006


    Variable-structure control of spacecraft attitude maneuvers

    DWYER, THOMAS A. W. / SIRA-RAMIREZ, HEBERTT | AIAA | 1988