Navigation aspects of a rendezvous mission to Deimos (the outer satellite of Mars) were examined using a modified Viking Monte Carlo error analysis program. Rendezvous is initiated by two-impulse transfer from an observation orbit cotangent with the orbit of Deimos. Television sightings of the satellite against a star background will allow a 20 km closest approach radius (R99) 99% of the time. This is well within the 100 km range of the terminal rendezvous radar. An additional delta-V capability of about 100 m/sec (above the nominal) must be allocated to account for the statistical nature of the mission. This delta-V requirement was found to be very sensitive to the level of satellite ephemeris error and maneuver execution error. The R99 on the other hand, is sensitive to the in-orbit DSN error and the maneuver execution error.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Navigation requirements for rendezvous with the satellites of Mars.


    Beteiligte:
    Satin, A. L. (Autor:in)

    Kongress:

    The growth and maturity of navigation in space; National Space Meeting ; 1972 ; Orlando, FL


    Erscheinungsdatum :

    1972-01-01


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :



    Mars Rendezvous Relative Navigation Implementation for SINPLEX

    Sagliano, Marco / Steffes, Stephen R. / Theil, Stephan | AIAA | 2014


    Mars Rendezvous Relative Navigation Implementation for SINPLEX (AIAA 2014-4104)

    Sagliano, M. / Steffes, S.R. / Theil, S. et al. | British Library Conference Proceedings | 2014


    Relative Navigation Requirements for Automatic Rendezvous and Capture Systems

    P. M. Kachmar / R. J. Polutchko / W. Chu et al. | NTIS | 1991


    Relative navigation requirements for automatic rendezvous and capture systems

    Kachmar, Peter M. / Polutchko, Robert J. / Chu, William et al. | NTRS | 1991