Description of AOSO Mark II configuration which resulted from phase-I design efforts; spacecraft consists of experiment package, spacecraft assembly, and front cover, and can be aimed at sun with precision of plus or minus 5 arc-sec by means of fine sun sensor provided by spacecraft; description of orbital mechanics, experiment integration provisions, stabilization and control subsystem and fine sun sensor, communications and data handling subsystem, and power supply subsystem; tests carried out and development status.


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    Title :

    Development approach for advanced orbiting solar observatory spacecraft


    Additional title:

    J Spacecraft Rockets


    Contributors:
    Evans, W.B. (author)

    Published in:

    Publication date :

    1966


    Size :

    7 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :