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.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Thermal Design


    Contributors:


    Publication date :

    2018-01-01


    Size :

    15 pages




    Type of media :

    Article/Chapter (Book)


    Type of material :

    Electronic Resource


    Language :

    English




    Thermal design

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


    Pegasus Thermal Design

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


    Thermal design considerations

    Heller, G. B. | NTRS | 1966


    Pegasus thermal design

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


    Pegasus thermal design

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