This paper describes the methodology used to develop the spacecraft pointing stability constraints and instrument disturbance limits for the Geostationary Operational Environmental Satellite (GOES) R series of spacecraft launching on or after 2012. Instrument line of sight stability and control requirements drive the spacecraft pointing stability constraints. In turn, the spacecraft constraints are used to define the instrument disturbance limits. The resulting limits on the spacecraft and instruments are defined in terms of spacecraft pointing error displacement, velocity and acceleration.


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    Titel :

    Spacecraft pointing stability constraints and instrument disturbance limits for optical remote sensing satellites


    Beteiligte:

    Kongress:

    Sensors, Systems, and Next-Generation Satellites VII ; 2003 ; Barcelona,Spain


    Erschienen in:

    Erscheinungsdatum :

    02.02.2004





    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



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