The problems of large-angle attitude maneuvers of a spacecraft have gained much consideration in recent years. The configurations of the spacecraft considered are: completely rigid, a combination of rigid and flexible parts, or gyrostat-type systems. The performance indices usually include minimum torque integration, power criterion, and frequency-shaped cost functionals. The minimum time slewing problem of a rigid spacecraft was examined. Optimal control theory (Maximum Principal) was applied to the slewing motion of a general rigid spacecraft. Control torque about all three axes was computed. The equations for the system are composed of the Euler dynamical equations in the spacecraft body axes and the quaternion kinematical equation. By introducing the costates for the quaternion and the angular velocity, the Hamiltonian of the system can be formed and the optimal control obtained. Finally the methods are applied to the SCOLE slewing motion. The control variables include three control moments on the Shuttle and two control forces on the reflector. Numerical results are discussed.


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    Title :

    Minimum Time Attitude Slewing Maneuvers of a Rigid Spacecraft


    Contributors:
    F. Li (author) / P. M. Bainum (author)

    Publication date :

    1987


    Size :

    13 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





    Minimum time attitude slewing maneuvers of a rigid spacecraft

    Li, Feiyue / Bainum, Peter M. | NTRS | 1987



    Constrained Time-Optimal Slewing Maneuvers for Rigid Spacecraft (AAS 09-309)

    Melton, R.G. / American Astronautical Society / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2010