Abstract The altitude, inclination, epoch and angle of the orbit plane to the Sun (the Beta angle) determine the thermal environment of a spacecraft. In the direction of the Sun, the heat incident on a spacecraft can be huge, while on the side opposite the Sun, the spacecraft faces cold space. The objective of the thermal design is to bring these temperatures into a range where the spacecraft components can safely operate, and to ensure that internally generated heat from the spacecraft components is conducted or radiated out to maintain all spacecraft temperatures within the operating temperature ranges of its components. Typical component temperature operating ranges are given in Fig. 12.1. The goal is to design for component temperatures in the 10°–20 °C range.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Thermal Design


    Beteiligte:
    Sebestyen, George (Autor:in) / Fujikawa, Steve (Autor:in) / Galassi, Nicholas (Autor:in) / Chuchra, Alex (Autor:in)


    Erscheinungsdatum :

    2018-01-01


    Format / Umfang :

    15 pages




    Medientyp :

    Aufsatz/Kapitel (Buch)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




    Thermal design

    Hastings, E. C., Jr. / Smith, G. L. / Turner, R. E. | NTRS | 1964


    Pegasus thermal design

    Bannister, T. C. | NTRS | 1965


    Pegasus thermal design

    Bannister, T. C. / Eby, R. J. | NTRS | 1966


    Pegasus thermal design

    Bannister, Tommy C. / Eby, Robert J. | TIBKAT | 1966


    Pegasus Thermal Design

    T. C. Bannister / R. J. Eby | NTIS | 1966