The 2001 University of Washington Space Design class designed and developed a CubeSat platform to accomplish science objectives related to ionospheric modeling. Small satellites (between 1 and 15 kg) show great promise as a low-cost option to perform limited LEO science missions. This paper describes a CubeSat bus that supports two mission architectures based on two instrument packages. Both architectures involve multiple CubeSats separated from each other to gather spatially and temporally distributed data. The first is a combined plasma impedance probe/DC probe system on two satellites, separated by a tether. The second is two separate CubeSats that perform GPS scintillation measurements. In addition to the common bus structure, unique design traits (such as tethered gravity gradient control) and extensive hardware and software prototyping are discussed in the paper.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    CubeSat design for LEO-based Earth science missions


    Beteiligte:
    Waydo, S. (Autor:in) / Henry, D. (Autor:in) / Campbell, M. (Autor:in)


    Erscheinungsdatum :

    01.01.2002


    Format / Umfang :

    2022803 byte




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



    2.0802 CubeSat Design for LEO-Based Earth Science Missions

    Institute of Electrical and Electronics Engineers | British Library Conference Proceedings | 2002


    Deployable CubeSat Antennas for Deep Space and Earth Science Missions

    Cwik, Tom / Gonzalez, David / Decrossas, Emmanuel et al. | NTRS | 2019



    Deployable CubeSat Antennas for Deep Space and Earth Science Missions

    Cwik, Tom / Gonzalez, David / Decrossas, Emmanuel et al. | NTRS | 2019