Spacecraft roll-yaw compensator with orbit-rate and harmonic ban

Details Spacecraft roll-yaw compensator with orbit-rate and harmonic ban Spacecraft roll-yaw compensator with orbit-rate and harmonic ban

1992-04-23

1994-08-30

Black, Thomas G.

Boots, shoes, and leggings

364459, 244164, G06F 1550, B64G 136

Patent

active

053433980

ABSTRACT:
A pitch momentum stabilized spacecraft includes an earth sensor for generating roll signals. The roll signals are applied to torquers for proportional (P) or proportional-integral PI control of roll and yaw. According to the invention, the sensed roll signals are bandpass filtered at the orbit rate, phase adjusted and applied to the roll and yaw torquers for closing a high gain degenerative feedback loop at the orbit rate, which reduces orbit-rate components of roll and yaw. A second bandpass filter at the second harmonic of the orbit rate is also connected to the earth sensor, for producing second harmonic signals, which are phase controlled and summed with the fundamental orbit rate signals, for degeneration of attitude perturbations occurring at twice the orbit frequency.

REFERENCES:
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patent: 4521855 (1985-06-01), Lehner et al.
patent: 4791573 (1988-12-01), Zemany et al.
patent: 4911385 (1990-03-01), Agrawal et al.
patent: 5025381 (1991-06-01), Goodzeit et al.
patent: 5100084 (1992-03-01), Rahn et al.
"High Pointing Accuracy with a Momentum Bias Attitude Control System", Journal of Guidance and Control, vol. 3, No. 3, May-Jun. 1980.
"The Synthesis of Regulator Logic Using State-Variable Concepts," Bryson et al, Proceedings of the IEEE, vol. 58, No. 11, Nov. 1970.
"Attitude Control of a Communication Satellite During Stationkeeping Using a Yaw Estimator," Spector et al, pp. 125-134 ca. 1980, American Institute of Aeronautics and Astronautics.

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