This research considers the descent path of a space vehicle, from periselenium of its operational orbit to the lunar surface. The trajectory is split in two arcs: (a) approach, up to a specified altitude, and (b) terminal descent and soft touchdown. For phase (a), a new locally flat near-optimal guidance is used, which is based on iterative projection of the spacecraft position and velocity, and availability of closed-form expressions for the related costate variables. Attitude control is aimed at pursuing the desired spacecraft orientation, and uses an adaptive tracking scheme that compensates for the inertia uncertainties. Arc (b) is aimed at gaining the correct vertical alignment and low velocity at touchdown. For phase (b) a predictive bang-off-bang guidance algorithm is proposed that is capable of guaranteeing the desired final conditions, while providing the proper allocation of side jet ignitions. Actuation of side jets is implemented using pulse width modulation, in both phases. Monte Carlo simulations prove that the guidance and control architecture at hand drives the spacecraft toward safe touchdown, in the presence of non-nominal flight conditions.


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    Title :

    Explicit Near-Optimal Guidance and Pulse-Modulated Control for Lunar Descent and Touchdown


    Additional title:

    Aerotec. Missili Spaz.


    Contributors:
    Pontani, M. (author) / Celani, F. (author) / Carletta, S. (author)

    Published in:

    Aerotecnica Missili & Spazio ; 101 , 4 ; 361-370


    Publication date :

    2022-12-01


    Size :

    10 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





    Explicit near-optimal guidance and pulse-modulated control for lunar descent and touchdown

    Pontani, M. / Celani, F. / Carletta, S. | BASE | 2022

    Free access



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