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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    Title :

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


    Contributors:

    Conference:

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


    Published in:

    Publication date :

    2004-02-02





    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English



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