Abstract
This paper addresses the design and verification of an
attitude control system for an agile satellite using
experimental data. Typical agile satellites are equipped
with control momentum gyros, which allow for the generation
of high internal reaction torques and hence attitude
maneuvers with high angular rates. The architecture of the
attitude control system with design implications is
presented and discussed. In order to mitigate the risks
associated with design and verification of the highly
demanding agile attitude control, experimental results
involving a hardware in-the-loop demonstrator are
presented. The overall design process and closed loop
performance evaluation allows an increasing technology
readiness level for target missions.
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