This paper presents the results of a design study involving the application of a combined LQR/dynamic inversion//spl mu/-synthesis control strategy to the descent phase of a reusable launch vehicle (RLV). A nominal desired plant response is formed by deriving a set of linear quadratic regulator gains for a plant model representing an intermediate point along the descent trajectory. A dynamic inversion controller, based on the linearized plant dynamics, is employed to drive the plant response at off-nominal conditions towards the regulated dynamics at the nominal point. The equalization provided by the inner-loop controller makes it possible to use a fixed outer-loop controller, derived using /spl mu/-synthesis, to provide robust performance throughout the descent trajectory. The use of body-axis rotational accelerations as generalized controls within the inner-loop provides a means for blending the reaction control system (RCS) with the aerodynamic control effectors during the low dynamic pressure portion of the descent trajectory. Results of a six-degree-of-freedom, nonlinear simulation demonstrate the effectiveness of the control strategy.


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    Title :

    Descent-phase control of a reusable launch vehicle


    Contributors:
    Caplin, J. (author)


    Publication date :

    2002-01-01


    Size :

    686607 byte




    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English



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