Electric propulsion systems meant an important improvement in the space sector ever since it was invented. Lately, it has been tested in different applications and it holds capital advantages over the conventional propulsion systems. On the other hand, low-thrust transfers performed with electric propulsion require large times of flight. A major drawback comes along with this fact: high exposure to trapped energized particles in Van Allen Belts. This radiation environment becomes a considerable issue for electronic systems and satellite onboard equipment, as well as a relevant solar array degradation, which implies a significant loss of power capability during the mission. The current thesis focuses on the implementation of a fast and reliable radiation model that is meant to be incorporated into an optimization framework in order to minimize the above-mentioned deterioration of the photovoltaic cells along an Earth-centered trajectory. The developed model has been validated with the AE9/AP9/SPM tool and SPENVIS, and the basis for the aforementioned optimal control has been stated.
I sistemi di propulsione elettrica hanno significato un importante miglioramento nel settore spaziale. Recentemente, la propulsione elettrica è stata utilizzata per diverse applicazioni ed offre sostanziali vantaggi rispetto ai convenzionali sistemi di propulsione. D’altra parte, i trasferimenti a bassa spinta, tipici degli attuali sistemi propulsivi elettrici, richiedono alti tempi di volo. Di conseguenza, un inconveniente rilevante è dovuto all’esposizione del satellite alle particelle ad alta energia all’interno delle fasce di Van Allen. Il passaggio all’interno di questo ambiente diventa un considerevole problema per quanto riguarda i sistemi e le apparecchiature all’interno del satellite; inoltre, può portare ad una rilevante degradazione dei pannelli solari che a sua volta implica una significativa perdita di generazione di potenza durante la missione. La presente tesi si concentra sullo sviluppo di un modello veloce e rappresentativo per quantificare l’esposizione alle suddette radiazioni, in modo tale da poter essere utilizzato in un processo di minimizzazione del deterioramento delle celle solari lungo una traiettoria in un sistema centrato nella Terra. Il modello prodotto è stato validato attraverso il software AE9/AP9/SPM e con SPENVIS; al contempo, le basi per sviluppare il suddetto controllo ottimo sono state derivate.
A radiation model for power degradation estimation in earth centered satellites
MAÑERO CONTRERAS, ALBERTO
2017/2018
Abstract
Electric propulsion systems meant an important improvement in the space sector ever since it was invented. Lately, it has been tested in different applications and it holds capital advantages over the conventional propulsion systems. On the other hand, low-thrust transfers performed with electric propulsion require large times of flight. A major drawback comes along with this fact: high exposure to trapped energized particles in Van Allen Belts. This radiation environment becomes a considerable issue for electronic systems and satellite onboard equipment, as well as a relevant solar array degradation, which implies a significant loss of power capability during the mission. The current thesis focuses on the implementation of a fast and reliable radiation model that is meant to be incorporated into an optimization framework in order to minimize the above-mentioned deterioration of the photovoltaic cells along an Earth-centered trajectory. The developed model has been validated with the AE9/AP9/SPM tool and SPENVIS, and the basis for the aforementioned optimal control has been stated.File | Dimensione | Formato | |
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AlbertoManeroContreras_Thesis.pdf
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https://hdl.handle.net/10589/141463