2 February 2004 Spacecraft pointing stability constraints and instrument disturbance limits for optical remote sensing satellites
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Abstract
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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Derrick A. Early, Derrick A. Early, Alan D. Reth, Alan D. Reth, Otilia I. Rodriguez-Alvarez, Otilia I. Rodriguez-Alvarez, } "Spacecraft pointing stability constraints and instrument disturbance limits for optical remote sensing satellites", Proc. SPIE 5234, Sensors, Systems, and Next-Generation Satellites VII, (2 February 2004); doi: 10.1117/12.511166; https://doi.org/10.1117/12.511166
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