Efficient power generation is crucial to the design of spacecraft. Mass, volume, and other limitations prevent the use of traditional spacecraft support structures from being suitable for the size of solar array required for some missions. Folding solar panel / panel array systems, however, present a number of design challenges. This paper considers the electrical design of an origami system. Specifically, it considers how to provide low impedance, durable channels for the generated power and the electrical aspects of the deployment system and procedure. The ability to dynamically reconfigure the electrical configuration of the solar cells is also discussed. Finally, a small satellite test mission to demonstrate the technology is proposed, before concluding.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Electrical design for origami solar panels and a small spacecraft test mission


    Beteiligte:
    Drewelow, James (Autor:in) / Straub, Jeremy (Autor:in)

    Kongress:

    Sensors and Systems for Space Applications X ; 2017 ; Anaheim,California,United States


    Erschienen in:

    Proc. SPIE ; 10196


    Erscheinungsdatum :

    05.05.2017





    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




    Use of Solar Panels in the Design of Small CubeSat Spacecraft

    Selivanov Kirill V. / Vasiliev Igor A. / Yakovenko Arina A. | DOAJ | 2021

    Freier Zugriff

    Small Spacecraft Design for the GRAIL Mission

    Spath, S. / Utah State University; American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2012



    Spacecraft mission design

    Brown, Charles D. | TIBKAT | 1998