Abstract We consider the problem of injection of a spacecraft into the heliocentric Earth's orbit ahead and/or behind the Earth by 60° and 120° in heliographic longitude. The range of solar and astrophysical problems for which these orbits are necessary is reviewed. The variants of injection into heliocentric orbits work from a low around-Earth orbit with one turn-on of the engine in this orbit and one turn-on at the end of the injection trajectory. In this case, it turns out to be more profitable to put spacecraft into orbit for three or even four revolutions of the Earth about the Sun. The velocities necessary for the start from a low around-Earth orbit, the velocities at the final point of injection, and the fuel mass (relative to the spacecraft mass) necessary for injection are estimated. The problems for which injection to similar orbits is executed, using the low-thrust engine and with a combined regime of injection, are also considered.


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    Titel :

    Spacecraft Injection into a Heliocentric Terrestrial Orbit


    Beteiligte:
    Kurt, V. G. (Autor:in) / Sukhanov, A. A. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2003




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :

    Klassifikation :

    BKL:    55.60 Raumfahrttechnik / 39.00 Astronomie: Allgemeines / 50.93 Weltraumforschung
    Lokalklassifikation TIB:    770/3520/8000



    Spacecraft Injection into a Heliocentric Terrestrial Orbit

    Kurt, V. G. / Sukhanov, A. A. | Springer Verlag | 2003



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