A radiometer-deployment subsystem for the Nimbus E spacecraft was designed, developed, and qualified for space use. The dimensions of the radiometer are 0.9 meter square by 0.1 meter, and its weighs 32 kilograms. Rigidly secured to the spacecraft during launch, the radiometer is deployed when the spacecraft reaches orbit. Deployment is achieved without permitting any portion of the radiometer to intersect the field of view of the infrared horizon scanner. This accomplishment necessitated a nonlinear deployment profile, which was accomplished by using a four-bar linkage composed of arms, cams, pivots, and steel tapes.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Radiometer-deployment subsystem


    Beteiligte:
    Speight, K. M. (Autor:in)


    Erscheinungsdatum :

    01.11.1972


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Thermal Control Subsystem Design for the EOS Thermal Infrared Radiometer

    Drackett, Terry M. / Zaiki, Y. | SAE Technical Papers | 1993


    DEMONSTRATION OF DEPLOYMENT ACCURACY OF THE STARSHADE INNER DISK SUBSYSTEM

    Arya, Manan / Webb, David / Steeves, John et al. | TIBKAT | 2020


    Demonstration of Deployment Accuracy of the Starshade Inner Disk Subsystem

    Turse, Dana / Hepper, David / Adams, Larry et al. | NTRS | 2020


    Demonstration of Deployment Accuracy of the Starshade Inner Disk Subsystem

    Arya, Manan / Webb, David / Steeves, John et al. | AIAA | 2020