Attitude Control System for the Extreme Ultraviolet Explorer SatelliteThe requirements, design, and expected performance of the Attitude Control Subsystem for the spin-stabilized Extreme Ultraviolet Explorer Satellite are presented. In the sky-mapping phase, closed-loop magnetic control keeps the spin axis pointed toward the sun. In the spectroscopy phase, the attitude control loop is closed via the ground. The satellite's attitude and spin rate are determined using periodically downlinked star data. An attitude control algorithm generates commands to be uplinked to the satellite for spin axis precession and spin rate control. Computer simulations of the satellite dynamic response, pointing error, and stability during spin axis precession are presented, and parameters that affect the pointing performance are evaluated.
Document ID
19840047791
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Wong, E. C. (California Institute of Technology, Jet Propulsion Laboratory, Pasadena CA, United States)