Abstract
This chapter is one of the most complex ones and covers the platform Failure Detection, Isolation and Recovery (FDIR). It starts with explaining the FDIR concept and the system redundancies. Next FDIR Events, their flow in the onboard software and their management are explained. The spacecraft reconfiguration functionalities are treated in detail, in particular the reconfiguration of the onboard computer elements and the power subsystem as well as the mode fallback hierarchy for the diverse failure types. The FDIR specifics for each subsystem are explained and also the handling of device hardware failures. Software constants and FDIR limits are provided in the book’s annexes.
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- 1.
For the FLP Generation 2 the ACS can be upgraded to a full AOCS with a propulsion module (see Sect. 7.10) which however is not treated here in the FDIR chapter as no such spacecraft/mission is implemented yet at time of publishing.
- 2.
For the detailed explanation of the method please refer to [136].
- 3.
The FOGs were procured in a far too early phase of the satellite project and were stored several years until integration and environmental tests were completed.
- 4.
It has to be noted that despite all careful design, implementation and testing, the OBSW is an academic product that is implemented with limited resources and experience.
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© 2016 Springer International Publishing Switzerland
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Witt, R., Eickhoff, J. (2016). Failure Detection, Isolation and Recovery Concept. In: Eickhoff, J. (eds) The FLP Microsatellite Platform. Springer Aerospace Technology. Springer, Cham. https://doi.org/10.1007/978-3-319-23503-5_10
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DOI: https://doi.org/10.1007/978-3-319-23503-5_10
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