Attitude control system for three-axis stabilized satellite in n

Details Attitude control system for three-axis stabilized satellite in n Attitude control system for three-axis stabilized satellite in n

1991-12-12

1993-11-09

Barefoot, Galen

Aeronautics and astronautics

Spacecraft

Attitude control

244165, 244166, B64G 124

Patent

active

052595773

ABSTRACT:
A roll/yaw attitude control system for a three-axis stabilized satellite in an at least approximately Equatorial orbit embodies a processor circuit connected between a roll, yaw and pitch attitude sensing device including a terrestrial sensor and a stellar sensor adapted to detect the Pole Star and an actuator device having a kinetic moment system substantially oriented along the pitch axis and a magnetic dipole generator system disposed at least approximately in a roll/yaw plane. The processor circuit embodies a short-term roll/yaw control loop adapted to estimate the roll and yaw attitude angles and angular speeds and to determine set point signals for some elements of the actuator device and a long-term roll/yaw control loop adapted to estimate roll/yaw attitude angles and external disturbances and to determine a dipole signal to be applied to the magnetic dipole generator system or to backup actuators.

REFERENCES:
patent: 3813067 (1974-05-01), Mork
patent: 4010921 (1977-03-01), Pistiner et al.
patent: 4071211 (1978-01-01), Muhlfelder et al.
patent: 4114841 (1978-09-01), Muhlfelder et al.
patent: 4521855 (1985-06-01), Lehner et al.
patent: 5149022 (1992-09-01), Flament

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