This paper describes a new controller for automatic attitude maneuvers of the Space Shuttle Orbiter. The controller incorporates a new solution algorithm for partially linearized, fuel-optimal maneuvers for RCS jet controlled spacecraft. These solutions provide model trajectories and jet commands that are easily tracked using a feed-forward, feedback controller structure. The result is a substantial performance improvement over the current Orbiter attitude maneuver controller. The paper discusses optimal maneuvers for this type of vehicle, giving detail of the solution algorithm. Closed-loop controller design and implementation is discussed. Detailed performance results are presented.


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    Title :

    An optimized rotation-axis model-following controller for STS orbiter attitude maneuvers


    Contributors:

    Conference:

    Guidance, Navigation and Control Conference ; 1985 ; Snowmass, CO


    Publication date :

    1985-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English