Attitude control system is investigated assuming that satellite can be analyzed as thin circular plate; certain types of orbiting telescopes fall in this category; modes of vibration of system are determined and their influence on performance quality of three-axis control system is studied; it is shown that elastic motions are reflected on only one axis of vehicle with proper location of sensors, and that control system can be made insensitive to two lowest vibration modes; interaxis coupling has negligible influence on system stability if control system for each axis is properly designed.
Attitude control problem for flexible satellites
SAE-NASA -- Proc
Proceedings of Society of Automotive Engineers, National Aeronautics and Space Administration -- Aerospace Vehicle Flight Control Conference ; 1965 Control
1965
11 pages
Conference paper
English
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The Attitude Control Problem for Flexible Satellites
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