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Robust attitude control of a spacecraft with flexible dynamics
KTH, School of Electrical Engineering and Computer Science (EECS).
2019 (English)Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
Abstract [en]

The employment of Electrical Propulsion, to reduce the cost of satellites, has also increasedthe use of large solar arrays. Such solar panels are associated with low-frequency resonantmodes, and to ensure fine pointing of the satellite, the attitude control should not excitethese modes. This is a difficult task in such complex systems, whose exact a prioriknowledge is largely unavailable during the early design phase.The primary scope of this thesis is to synthesize a robust algorithm for attitude controlthat deals with modeling errors.The first part is dedicated to understanding the principal causes of uncertainty thatwill inevitably limit the design. Once a description of the uncertainty has been obtained,two different approaches to robust control algorithms have been investigated. The outcomeis the syntheses of two multivariable controllers with different performance and stabilitymargins. Since this project has been carried out during the development of a new fullelectric spacecraft concept by OHB, it has been possible to validate the two controllersin the on-board software simulator of the spacecraft. The results confirm the robustcontrollers as possible alternatives to the current design.

Abstract [sv]

Införandet av Elektrisk Framdrivning för att reducera kostnaden för satelliter har ocksåökat användningen av stora solpaneler. Sådana stora solpaneler är associerade medlågfrekventa resonanta moder och för att säkerställa satellitens prestanda får attitydkontrolleninte exitera dessa moder. Detta är en svår uppgift i sådana komplicerade systemför vilka exakt a priori kunskap till stora delar inte finns tillgänglig under projektets tidigadesignfas.Det här examensarbetet handlar i första hand om att syntetisera en robust algoritmför attitydkontroll vilken hanterar modelleringsfel. Första delen av arbetet avser attförstå vilka de primära osäkerhetskällor som begränsar systemets prestanda. Efter att enosäkerhetsbeskrivning har tagits fram undersöks två olika tillvägagångssätt för att ta framrobusta styralgoritmer. Resultatet är synteser av två olika multivariabla regulatorer medolika prestanda och stabilitetsmarginaler. Eftersom projektet har genomförts samtidigtsom OHB har utvecklat en satellitplattform baserad helt på Elektrisk Framdrivning, hardet varit möjligt att validera de två regulatorerna i ombordmjukvarans simulatormiljö.Resultaten bekräftar att de robusta regulatorerna är möjliga alternativ till nuvarandedesign.

Place, publisher, year, edition, pages
2019. , p. 124
Series
TRITA-EECS-EX ; 2019:297
National Category
Engineering and Technology
Identifiers
URN: urn:nbn:se:kth:diva-254418OAI: oai:DiVA.org:kth-254418DiVA, id: diva2:1332049
External cooperation
OHB Sweden
Educational program
Master of Science - Aerospace Engineering
Examiners
Available from: 2019-06-27 Created: 2019-06-27 Last updated: 2019-06-27Bibliographically approved

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CiteExportLink to record
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