Abstract The problem of optimization of a spacecraft transfer to the Apophis asteroid is investigated. The scheme of transfer under analysis includes a geocentric stage of boosting the spacecraft with high thrust, a heliocentric stage of control by a low thrust engine, and a stage of deceleration with injection to an orbit of the asteroid’s satellite. In doing this, the problem of optimal control is solved for cases of ideal and piecewise-constant low thrust, and the optimal magnitude and direction of spacecraft’s hyperbolic velocity “at infinity” during departure from the Earth are determined. The spacecraft trajectories are found based on a specially developed comprehensive method of optimization. This method combines the method of dynamic programming at the first stage of analysis and the Pontryagin maximum principle at the concluding stage, together with the parameter continuation method. The estimates are obtained for the spacecraft’s final mass and for the payload mass that can be delivered to the asteroid using the Soyuz-Fregat carrier launcher.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Optimization of transfer trajectories to the Apophis asteroid for spacecraft with high and low thrust


    Contributors:

    Published in:

    Cosmic Research ; 52 , 2 ; 106-117


    Publication date :

    2014-03-01


    Size :

    12 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English







    Rapid Solar Sail Rendezvous Missions to Asteroid 99942 Apophis

    Mengali, G. / Quarta, A.A. / European Space Agency | British Library Conference Proceedings | 2009


    Small Satellite Rendezvous and Characterization of Asteroid 99942 Apophis

    Chartres, J. / Dunham, D. / Williams, B. et al. | British Library Conference Proceedings | 2009