Method for spinning up a three-axis controlled spacecraft

Details Method for spinning up a three-axis controlled spacecraft Method for spinning up a three-axis controlled spacecraft

1985-11-15

1988-02-16

Barefoot, Galen

Aeronautics and astronautics

Spacecraft

Attitude control

244165, 244169, B64G 124

Patent

active

047250240

ABSTRACT:
A three-axis controlled spacecraft (1), typically a satellite, is spun up about its roll axis (20) prior to firing a motor (2), i.e., a perigee kick motor, to achieve the requisite degree of angular momentum stiffness. Thrusters (21) for imparting rotation about the roll axis (20) are activated in open-loop fashion, typically at less than full duty cycle. Cross-axis torques induced by this rotational motion are compensated for by means of closed control loops for each of the pitch and yaw axes (30, 40, respectively). Each closed control loop combines a prebias torque (72) with torques (75, 74) representative of position and rate feedback information, respectively. A deadband (52) within each closed control loop can be widened during the spinup, to conserve fuel. Position feedback information (75) in each of the control loops is disabled upon saturation of the gyroscope associated with the roll axis (20).

REFERENCES:
patent: 3158337 (1964-11-01), Lannan
patent: 3758051 (1973-09-01), Williams
patent: 3984071 (1976-10-01), Fleming
patent: 4326684 (1982-04-01), Rosen
patent: 4370716 (1983-01-01), Amieux
patent: 4374579 (1983-02-01), Renner et al.
patent: 4471926 (1984-09-01), Steel, III
patent: 4537375 (1985-08-01), Chan
Defensive Publication T100,604, Crill et al., May 5, 1981.
Wie and Barba, "Quaternion Feedback for Spacecraft Large Angle Maneuvers", Journal of Guidance, Control, and Dynamics, vol. 8, No. 3, May-Jun. 1985, pp. 360-365.

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