AbstractThe maximum terminal velocity problem of the classical propulsion is extended to a relativistic rocket assumed broken down into active mass, inert mass and gross payload. A fraction of the active mass is converted into energy shared between inert mass and active mass residual. Significant effects are considered. State and co-state equations are carried out to find the exhaust speed optimal profile.A first major result consists of a critical value of inert mass. Beyond it both true and effective jet speeds increase with time. Below it the true jet speed profile is reversed. At criticality, the best control consists of both velocities constant in time.A second meaningful result is represented by an interval of inert mass outside which no optimal control exists. Numerical results are discussed with particular emphasis to current concepts of antimatter propulsion.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Maximum terminal velocity of relativistic rocket


    Beteiligte:

    Erschienen in:

    Acta Astronautica ; 12 , 2 ; 81-90


    Erscheinungsdatum :

    1984-05-04


    Format / Umfang :

    10 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




    Relativistic Rocket Mechanics

    H. G. L. Krause | NTIS | 1960


    Relativistic rocket: Dream and reality

    Semyonov, Oleg G. | Elsevier | 2014


    Relativistic rocket and space flight

    Walter, Ulrich | Elsevier | 2006


    Relativistic rocket: Dream and reality

    Semyonov, Oleg G. | Online Contents | 2014