Pivot actuated nutation damping for a dual-spin spacecraft

Aeronautics and astronautics – Spacecraft – Attitude control

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244165, B64G 138

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active

047280620

ABSTRACT:
A nutation damping control for a dual-spin satellite is provided by tilting the axis of the rotor relative to the normal spin axis of the satellite and back a half nutation period later. The tilting is in the direction of the angular momentum vector component that is transverse to the rotor's spin axis.

REFERENCES:
patent: 3591108 (1971-07-01), Perkel
patent: 3638883 (1972-02-01), Lanzaro
patent: 3685770 (1972-08-01), Tomkin
patent: 3695554 (1972-10-01), Phillips
patent: 3830447 (1974-08-01), Philips
patent: 3937423 (1976-02-01), Johansen
patent: 3984071 (1976-10-01), Fleming
patent: 4096427 (1978-06-01), Rosen et al.
patent: 4193570 (1980-03-01), Hoffman et al.
patent: 4272045 (1981-06-01), Phillips
patent: 4370716 (1983-01-01), Amieux
patent: 4386750 (1983-06-01), Hoffman
patent: 4504032 (1985-03-01), Phillips et al.
AIAA Paper No. 70-456 of the 3rd Communications Satellite Systems Conference of Apr. 6-8, 1970; "Three Axis Attitude Control of a Synchronous Communications Satellite" by J. U. Beusch et al.
"Satellite Attitude Control with a Gimbaled Reaction Wheel Digital Control System" by C. H. Much et al., Automatica, vol. 8, pp. 9-21, Pergamon Press, 1972.

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