It was shown earlier that 1 x 10 to the -14th Doppler data and 3 cm accuracy range measurements to a small Mercury Relativity Satellite in a polar orbit with four-hour period can give high-accuracy tests of gravitational theory. A particular conceptual design has been developed for such a satellite, which would take less than 10 percent of the approach mass for a possible future Mercury Orbiter Mission. The spacecraft is similar to the Pioneer Venus Orbiter, but scaled down by about a factor four in linear dimensions. A despun antenna 30 cm in diameter is used for tracking. The transmitted power is roughly 0.2 watts at K-band and 0.5 watts at X-band. The orbit parameters for individual eight-hour arcs and the gravity field of Mercury through degree and order 10 are determined mainly from the Doppler data. A 50 MHz K-band sidetone system provides the basic ranging accuracy. The spacecraft mass is 50 kg or less.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Conceptual design for a Mercury relativity satellite


    Beteiligte:
    Bender, P. L. (Autor:in) / Ashby, N. (Autor:in) / Wahr, J. M. (Autor:in) / Vincent, M. A. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    01.01.1989



    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Conceptual design for a mercury relativity satellite

    Bender, P.L. / Ashby, N. / Vincent, M.A. et al. | Elsevier | 1989


    Conceptual design of satellite SAR

    Raney, R.K. | Tema Archiv | 1984


    Orbit Design for General Relativity Experiments: Heliocentric and Mercury-centric Cases

    Park, Ryan / Scheeres, Daniel / Giampieri, Giacomo et al. | AIAA | 2004



    Autometric gyro for satellite relativity experiments.

    Frisch, D. H. / Kasper, J. F., Jr. | NTRS | 1969