A conical scanning method and system is provided for orienting a spacecraft with respect to a source. The system includes a spacecraft and an incidence angle sensor secured to the spacecraft to sense a signal from a source. The incidence angle sensor has a boresight that is canted with respect to the principal axis. A processor communicates with actuators on the spacecraft to adjust an attitude of the spacecraft based on information received from the incidence angle sensor and to thereby align a principal axis of the spacecraft with a direction from the spacecraft to the source. The method and system can also rely on information received from source presence sensors. The source may be the Sun, or a non-solar signal source.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Conical scanning process for spacecraft sun pointing


    Beteiligte:
    SHOER JOSEPH (Autor:in) / SINGH LEENA (Autor:in) / LIM SUNGYUNG (Autor:in) / HENDERSON TIMOTHY (Autor:in)

    Erscheinungsdatum :

    2019-05-28


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



    CONICAL SCANNING PROCESS FOR SPACECRAFT SUN POINTING

    SHOER JOSEPH / SINGH LEENA / LIM SUNGYUNG et al. | Europäisches Patentamt | 2017

    Freier Zugriff

    Conical Scanning System for Pioneer Jupiter Spacecraft

    Viskanta, V. Z. / Rose, R. E. | IEEE | 1972


    Conical scanning approach for Sun pointing on the CYGNSS microsatellite

    Shoer, Joseph / Singh, Leena / Henderson, Timothy | IEEE | 2015



    GLAS Spacecraft Pointing Study

    Born, George H. / Gold, Kenn / Ondrey, Michael et al. | NTRS | 1998