Abstract
This paper describes the reliability and performance evaluation of fault detection and isolation (FDI) for the attitude control of a typical satellite, the Mars Express (MEX) orbiter. The study uses a detailed non-linear simulation of the MEX, and the FDI performance for thruster misalignments is evaluated subject to disturbance signals and model uncertainty. Carefully selected performance criteria indices are used together with Monte Carlo robustness tuning and performance evaluation to yield an FDI design methodology. This is a realisation of a reliability and performance analysis for FDI in future spacecraft.
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