A novel conversion algorithm is presented that combines the fidelity of indirect optimization methods with the generality of direct methods to more easily solve time-optimal, finite-burn pseudo-rendezvous problems. An algorithm is described that converts a set of multiple-impulses, representing the entirety or a portion of a high- or low-thrust maneuver, to an exact time optimal finite-burn trajectory for a thrust limited, constant exhaust velocity spacecraft. A pseudo-rendezvous problem is one that yields a solution whose final time, position and velocity state is equal to that of the original post-impulsive trajectory. An iterative adjoint-control transformation is used to initialize the optimal control two-point boundary value problem. Examples are shown for both high and low-thrust non-coplanar Earth orbit transfers, as well as a low-thrust Hohmann-type Earth-Mars transfer.


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    Title :

    Multi-Impulse to Time Optimal Finite Burn Trajectory Conversion


    Contributors:
    Fogel, J. (author) / Williams, J. (author) / Widner, M. (author) / Batcha, A. (author)

    Conference:

    AIAA/AAS Space Flight Mechanics Meeting ; 2020 ; Orlando, FL, United States


    Publication date :

    2020-01-06


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


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