Consideration of the problem of optimal ascent from an initial circular planetary orbit to some specified final energy level by a spacecraft equipped with a low-thrust engine. Optimal is defined as minimum time. An accurate small parameter perturbation solution is presented, and the optimal trajectory is analyzed and compared with a tangential thrust trajectory.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Asymptotic solution to the problem of optimal low-thrust energy increase.


    Beteiligte:
    Jacobson, R. A. (Autor:in) / Powers, W. F. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    01.12.1972


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :



    Asymptotic Solution for the Two-Body Problem with Low-Thrust

    Sanjurjo-Rivo, M. / Bombardelli, C. / Pelaez, J. et al. | British Library Conference Proceedings | 2012


    Asymptotic Solution for the Low-Thrust Restricted Two-Body Problem

    Sanjurjo-Rivo / Bombardelli / Pelaez | AIAA | 2012



    Analytical Approximate Calculation of Optimal Low-Thrust Energy Increase Trajectories

    OTTO J. REIDELHUBER AND KLAUS-J. SCHWENZFEGER | AIAA | 1975