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.
Development approach for advanced orbiting solar observatory spacecraft
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 3 , n 1
1966
7 pages
Article (Journal)
English
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