To drop a discarded object, such as a discarded n-th-stage rocket body or a single-staged rocket of which the engine has cut-off, to impact within a safe area while consuming as much carried fuel as possible to improve launch capability. The flight path of a two-staged rocket (1) is periodically predicted during flight, and the predicted impact point when a first-stage rocket body (11) or a fairing (15) is separated and discarded is periodically predicted from a second-stage rocket (13) at each passing scheduled point in the predicted flight path. As long as there is a passing scheduled point such that the predicted impact points of the first-stage rocket body (11) and the fairing (15) are both within the safe area, a process is periodically performed to designate the passing scheduled point furthest from the launch location of the two-staged rocket (1) as the separate-and-discard point of the first-stage rocket body (11), and when the two-staged rocket (1) reaches this separate-and-discard point, the first-stage rocket body (11) or the fairing (15) is separated and discarded.


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    Titel :

    CONTROL DEVICE FOR ROCKET


    Weitere Titelangaben:

    STEUERUNGSVORRICHTUNG FÜR RAKETE
    DISPOSITIF DE COMMANDE DE FUSÉE


    Beteiligte:

    Erscheinungsdatum :

    08.05.2019


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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