Method for controlling the attitude of a three-axis stabilized, earth oriented bias momentum spacecraft
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United States of America Patent
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Dec 7, 1999
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N/A
app pub date -
Jun 17, 1997
filing date -
Aug 11, 1995
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Expired
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Abstract
An attitude controller for a 3-axis stabilized, Earth oriented bias momentum spacecraft is described, where only 2-axis attitude measurements from the Earth sensor are available. In contrast to the classical spacecrafts that are controlled w.r.t. a fixed orbital Earth pointing reference frame, (possibly large angle) time varying reference signals are considered here, i.e. the control task consists of a tracking problem. The controller design consists of a decoupling controller and axis-related PID controllers based on yaw observer estimates.
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