By Jens Eickhoff
This publication represents the Flight Operations guide for a reusable microsatellite platform – the “Future inexpensive Platform” (FLP), constructed on the collage of Stuttgart, Germany. It presents a uncomplicated perception at the onboard software program features, the middle facts dealing with approach and at the energy, communications, perspective regulate and thermal subsystem of the platform. Onboard failure detection, isolation and restoration features are handled intimately. The platform is suited to satellites within the 50-150 kg type and is baseline of the microsatellite “Flying machine” from the University.
The booklet covers the fundamental details for floor operators to controls an FLP-based satellite tv for pc employing foreign command and keep an eye on criteria (CCSDS and ECSS PUS).
Furthermore it presents an summary at the Flight regulate heart in Stuttgart and at the hyperlink to the German area supplier DLR flooring Station that is used for early venture levels. Flight method and undertaking making plans chapters supplement the booklet.
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Extra info for The FLP Microsatellite Platform: Flight Operations Manual
11). At launch, no component should be defective, so all flags are set to “HEALTHY”. These can be changed automatically to “FAULTY” by the FDIR upon a detection of an error or by a telecommand from ground. However, to change the status of a device back to “HEALTHY”, this is only possible by telecommand from ground—see also Sect. 16. 12 Mode Tables and Sequences Control Service The satellite modes are deﬁned in the OBSW by tables which contain mode/ submode combinations and by sequences which contain sets of tables.
1 also is no real mode but just an operational transition. It can however be commanded in case where a reboot of the satellite system becomes necessary. As soon as the PCDU’s launcher separation circuit detects separation, the PCDU boots and thereafter initiates power-up of diverse equipment for the Safe Mode, namely OBC and Transceivers. The OBC/OBSW then perform the ﬁnal steps to reach Detumble/Safe Mode. The overall satellite system boot at launcher separation is explained in more detail later in Sect.
3 The Power Control and Distribution Unit The power subsystem is controlled by a Power Control and Distribution Unit (PCDU), which includes the Battery Charge Regulators, provides an unregulated bus voltage to the satellite platform and instrument units. 0 V. In a conﬁguration with larger panels the usually applied 28 V bus voltage can be achieved for future FLP spacecraft. The PCDU is custom designed and is manufactured by Vectronic Aerospace, Berlin, Germany. It is controlled by the OBC and is able to switch the individual platform and payload equipment power lines.