The project Flexible LEO Platform (FLP2) is originally related to the project ”Future Low-cost Platform”, or FLP Gen. 1, born at the University of Stuttgart and developed in collaboration with Airbus DS. This was foreseen as test-bench for the space mission of a small Sat called Flying Laptop which has been successfully launched on July 14, 2017. The test-bed configuration for the FLP in Stuttgart was equipped with a real On-Board Computer (OBC) provided with redundant processor boards Cobham Aeroflex UT699. The satellite mission was fully simulated in the simulation environment connected directly to the OBC, in order to have a real response from the system. The final satellite, the Flying Laptop, was commanded from a Ground Control Center (GCC). The main idea behind the creation of the project FLP was to give birth to an effective and highly autonomous low-cost small Sat. Starting from the already existing technologies in Stuttgart, Airbus DS started its own internal project, with the related test-bench where all the new technologies will be developed. The new objective of the project is then to realize a reliable but low-cost satellite platform that would fit different payload configurations and interface architectures. The key-point of the project is then to create a satellite platform modular hardware and software, making it suitable for several ”LEO” (Low Earth Orbit) missions. In this scenario, a very important feature is to guarantee a reliable and robust interconnection between two essential components of the satellite: The Power Control and Distribution Unit (PCDU) and the OBC. Along with a new architecture, all the hardware and software components have to be properly designed accordingly. The scope of the thesis is then to define the new interconnection architecture, the software logic to be implemented for the failure management, and the final test procedure to be performed in order to check the correct behavior of the system in case a failure in the data communication lines occurs.
Il progetto Flexible LEO Platform (FLP2) è originariamente correlato al progetto "Future Low-cost Platform", o FLP Gen. 1, nato presso l'Università di Stoccarda e sviluppato in collaborazione con Airbus DS. Questo è stato previsto come banco di prova per la missione spaziale di un piccolo Sat chiamato Flying Laptop che è stato lanciato con successo il 14 luglio 2017. La configurazione del banco di prova per il FLP di Stoccarda era dotata di un vero Computer di bordo (OBC) dotato di schede processore ridondanti Cobham Aeroflex UT699. La missione satellitare è stata completamente simulata nell'ambiente di simulazione collegato direttamente all'OBC, in modo da avere una risposta reale da parte del sistema. Il satellite in questione, il Flying Laptop, era comandato dal Centro di controllo (GCC). L'idea principale alla base della creazione del progetto FLP è stata quella di far nascere un piccolo Sat efficace e altamente autonomo a basso costo. Partendo dalle tecnologie già esistenti a Stoccarda, Airbus DS ha iniziato un proprio progetto interno, con relativo banco prova dove verranno sviluppate tutte le nuove tecnologie. Il nuovo obiettivo del progetto è quindi quello di realizzare una piattaforma satellitare affidabile ma a basso costo che si adatterebbe a diverse configurazioni e missioni. Il punto chiave del progetto è quindi appunto la creazione di una piattaforma satellitare hardware e software modulare, rendendola adatto a diverse missioni “LEO” (Low Earth Orbit). In questo scenario, una caratteristica molto importante è garantire un'interconnessione affidabile e robusta tra due componenti essenziali del satellite: L'Unità di Controllo e Distribuzione di Potenza (PCDU) e l'OBC. Insieme a una nuova architettura, tutti i componenti hardware e software devono essere progettati correttamente di conseguenza. Lo scopo della tesi è quindi definire la nuova architettura di interconnessione, la logica del software da implementare per la gestione dei guasti e la procedura finale per il test da eseguire al fine di verificare il corretto comportamento del sistema nel caso in cui si verifichi un guasto nelle linee di trasmissione dati.
FLP2 power FDIR design and reconfiguration test
PASTORE, FEDERICO
2020/2021
Abstract
The project Flexible LEO Platform (FLP2) is originally related to the project ”Future Low-cost Platform”, or FLP Gen. 1, born at the University of Stuttgart and developed in collaboration with Airbus DS. This was foreseen as test-bench for the space mission of a small Sat called Flying Laptop which has been successfully launched on July 14, 2017. The test-bed configuration for the FLP in Stuttgart was equipped with a real On-Board Computer (OBC) provided with redundant processor boards Cobham Aeroflex UT699. The satellite mission was fully simulated in the simulation environment connected directly to the OBC, in order to have a real response from the system. The final satellite, the Flying Laptop, was commanded from a Ground Control Center (GCC). The main idea behind the creation of the project FLP was to give birth to an effective and highly autonomous low-cost small Sat. Starting from the already existing technologies in Stuttgart, Airbus DS started its own internal project, with the related test-bench where all the new technologies will be developed. The new objective of the project is then to realize a reliable but low-cost satellite platform that would fit different payload configurations and interface architectures. The key-point of the project is then to create a satellite platform modular hardware and software, making it suitable for several ”LEO” (Low Earth Orbit) missions. In this scenario, a very important feature is to guarantee a reliable and robust interconnection between two essential components of the satellite: The Power Control and Distribution Unit (PCDU) and the OBC. Along with a new architecture, all the hardware and software components have to be properly designed accordingly. The scope of the thesis is then to define the new interconnection architecture, the software logic to be implemented for the failure management, and the final test procedure to be performed in order to check the correct behavior of the system in case a failure in the data communication lines occurs.| File | Dimensione | Formato | |
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https://hdl.handle.net/10589/170999