The problem of transferring a rocket vehicle from a given circular orbit to a larger coplanar circular orbit in minimum time, using a constant low-thrust rocket engine, is considered. Parameters are chosen to correspond to a transfer from the earth's orbit in heliocentric space to the orbit of Mars. A path satisfying the first order necessary conditions of variational calculus is shown to be locally minimizing by application of a set of second order conditions. A physical explanation is offered to justify the retrothrust period occurring during the flight. A neighboring optimum feedback control law, based on estimated time-to-go, is applied to this problem. State variable and terminal constraint feedback gains are calculated while one of the second order conditions, involving the backward integration of a matrix Riccati equation, is being tested.


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    Titel :

    Perturbation guidance for minimum time flight paths of spacecraft.


    Beteiligte:
    Wood, L. J. (Autor:in)

    Kongress:

    American Institute of Aeronautics and Astronautics and American Astronautical Society, Astrodynamics Conference, Palo Alto


    Erscheinungsdatum :

    01.09.1972


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :



    Minimum time flight paths

    Schindler, G.M. | Engineering Index Backfile | 1960


    Guidance Symbology for Curved Flight Paths

    Regal, D. / Whittington, D. | British Library Conference Proceedings | 1995


    Approach guidance to circular flight paths

    KISHI, F. H. / PFEFFER, I. | AIAA | 1971