Design of Magnetorquer-Based Attitude Control Subsystem for FORESAIL-1 Satellite

dc.contributorAalto-yliopistofi
dc.contributorAalto Universityen
dc.contributor.authorJovanovic, N.
dc.contributor.authorRiwanto, B.
dc.contributor.authorNiemelä, P.
dc.contributor.authorMughal, M. Rizwan
dc.contributor.authorPraks, J.
dc.contributor.departmentDepartment of Electronics and Nanoengineering
dc.contributor.departmentJaan Praks Group
dc.date.accessioned2022-09-28T06:28:38Z
dc.date.available2022-09-28T06:28:38Z
dc.date.issued2021-12-01
dc.description.abstractThe magnetorquer-based attitude control system capable of attaining high spin rates and precise pointing control is required for a 3U CubeSat satellite FORESAIL-1. The satellite, developed by the Finnish Centre of Excellence, needs to maintain a spin rate of 24°/s and precise pointing of the spin axis toward the Sun for the particle telescope instrument, as well as to reach 130°/s spin rate for the deployment of the plasma brake. Mission requirements analysis and attitude system requirements derivation are presented, followed by actuator tradeoff and selection, with a detailed design of the complete attitude control system, including the air-cored type of magnetorquer actuators and their drivers, made of H-bridge and filtering components. The design is based on several theoretical and practical considerations with emphasis on the high-power efficiency, such as effects of parallel and serial magnetorquer connections, modeling the magnetorquers with equivalent circuit models for finding a suitable driving frequency and extrapolation methods for efficient dipole moment usage. The in-house manufacturing process of magnetorquers, using a custom 3-D-printer setup, is described. Finally, the testing and verification are performed, by measuring the performance of the manufactured hardware, circuit simulations, and attitude control simulations. It is shown that the manufactured attitude control system fulfills all system requirements. Simulations also confirm the capability to satisfy mission requirements.en
dc.description.versionPeer revieweden
dc.format.extent16
dc.format.extent220-235
dc.format.mimetypeapplication/pdf
dc.identifier.citationJovanovic , N , Riwanto , B , Niemelä , P , Mughal , M R & Praks , J 2021 , ' Design of Magnetorquer-Based Attitude Control Subsystem for FORESAIL-1 Satellite ' , IEEE Journal on Miniaturization for Air and Space Systems , vol. 2 , no. 4 , 9468712 , pp. 220-235 . https://doi.org/10.1109/JMASS.2021.3093695en
dc.identifier.doi10.1109/JMASS.2021.3093695
dc.identifier.issn2576-3164
dc.identifier.otherPURE UUID: 8479efa1-9604-4f20-952d-b7275edee338
dc.identifier.otherPURE ITEMURL: https://research.aalto.fi/en/publications/8479efa1-9604-4f20-952d-b7275edee338
dc.identifier.otherPURE LINK: https://ieeexplore.ieee.org/document/9468712/
dc.identifier.otherPURE FILEURL: https://research.aalto.fi/files/88686047/Design_of_Magnetorquer_Based_Attitude_Control_Subsystem_for_FORESAIL_1_Satellite.pdf
dc.identifier.urihttps://aaltodoc.aalto.fi/handle/123456789/116980
dc.identifier.urnURN:NBN:fi:aalto-202209285776
dc.language.isoenen
dc.publisherIEEE
dc.relation.ispartofseriesIEEE Journal on Miniaturization for Air and Space Systemsen
dc.relation.ispartofseriesVolume 2, issue 4en
dc.rightsopenAccessen
dc.subject.keywordAttitude control
dc.subject.keywordAngular velocity
dc.subject.keywordPower control
dc.subject.keywordCubeSat
dc.titleDesign of Magnetorquer-Based Attitude Control Subsystem for FORESAIL-1 Satelliteen
dc.typeA1 Alkuperäisartikkeli tieteellisessä aikakauslehdessäfi
dc.type.versionpublishedVersion
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