Abstract In order to carry out tasks of the RadioAstron mission, a high-apogee orbit was designed. On average, the period of its satellite’s orbit around the Earth is 8.5 days with evolution due to gravitational perturbations produced by the Moon and the Sun. The perigee and apogee of this orbit vary within the limits 7500–70000 km and 270000–333000 km, respectively. The basic evolution of the orbit represents a rotation of its plane around the line of apsides. Over 3 years, the plane normal to the orbit draws on the celestial sphere an oval with a semi-major axis of about 150° and semi-minor axis of about 45°.


    Access

    Access via TIB

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Orbit design for the Spektr-R spacecraft of the ground-space interferometer


    Contributors:

    Published in:

    Cosmic Research ; 52 , 5 ; 332-341


    Publication date :

    2014




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English



    Classification :

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



    Orbit design for the Spektr-R spacecraft of the ground-space interferometer

    Kardashev, N. S. / Kreisman, B. B. / Pogodin, A. V. et al. | Springer Verlag | 2014


    Trajectory correction of the Spektr-R spacecraft motion

    Zaslavskiy, G. S. / Stepan’yants, V. A. / Tuchin, A. G. et al. | Springer Verlag | 2014


    Trajectory correction of the Spektr-R spacecraft motion

    Zaslavskiy, G. S. / Stepan’yants, V. A. / Tuchin, A. G. et al. | Online Contents | 2014


    On the protection constructions for the Spektr

    Meshcheryakov, S.A. | AIAA | 2006


    Ground strike spacecraft space-atmosphere inner orbit whole-section control method

    WU BAOLIN / DONG YUYANG / DING XUELIANG et al. | European Patent Office | 2023

    Free access