Minimization of spacecraft attitude error due to wheel speed rev

Details Minimization of spacecraft attitude error due to wheel speed rev Minimization of spacecraft attitude error due to wheel speed rev

1975-03-11

1976-12-21

Kunin, Stephen G.

Aeronautics and astronautics

Spacecraft

Attitude control

2351502, 244 321, 318489, 318610, B64G 120

Patent

active

039984095

ABSTRACT:
An attitude control system for a substantially zero momentum spacecraft is arranged to minimize the attitude errors during periods of reaction wheel speed reversals. Wheel speed is sensed by a suitable device such as a tachometer or Hall elements. Spacecraft three axis attitude is sensed by suitable sensors such as sun sensors, star sensors, gyroscopes or earth horizon sensors. A control network is provided to generate the wheel torque commands necessary to maintain proper three axis attitude. During periods of wheel speed reversal, the control network includes appropriate compensation terms and corrections to the wheel torque command.

REFERENCES:
patent: 3350033 (1967-10-01), Goldberg
patent: 3424401 (1969-01-01), Maurer
patent: 3493194 (1970-02-01), Kurzhals
patent: 3591108 (1971-07-01), Perkel et al.
patent: 3696282 (1972-10-01), Hirokawa et al.
Cummings, J. A. et al., Skewed Versus Orthogonal Reaction Wheels for Outer Planet Exploration, AAS Conference, Seattle, Washington, 6-1971, AAS 71-157.

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