Aeronautics and astronautics – Spacecraft – Attitude control
Patent
1997-02-13
1999-11-16
Barefoot, Galen L.
Aeronautics and astronautics
Spacecraft
Attitude control
701 13, B64G 121
Patent
active
059842377
ABSTRACT:
A three-axis stabilized spacecraft is subject to a velocity change in a desired direction by a thruster. Unavoidable alignment errors cause a body torque, which tends to slew the body away from the attitude which orients the thrust axis in the direction. The attitude control system eventually corrects the attitude, but the thrust during the attitude transient results in an error in the direction of the velocity change. This error in the direction accumulates during the attitude transient. When the attitude transient passes, no further pointing error occurs. A control system, operating without an accelerometer, determines the total error accumulated during the attitude transient, and processes the error signal to generate a supplemental torque demand signal, which is added to the torque demand signal produced by the attitude control system, to cause an oppositely-directed attitude transient to thereby cancel the original velocity change direction error.
REFERENCES:
patent: 4927101 (1990-05-01), Blancke
patent: 5058835 (1991-10-01), Goodzeit et al.
patent: 5400252 (1995-03-01), Kazimi et al.
patent: 5646847 (1997-07-01), Rafan et al.
Barefoot Galen L.
Kennedy R. P.
Lockheed Martin Corp.
Meise W. H.
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