Minimization of residual spacecraft nutation due to disturbing t

Details Minimization of residual spacecraft nutation due to disturbing t Minimization of residual spacecraft nutation due to disturbing t

1978-12-12

1980-11-04

Barefoot, Galen L.

Aeronautics and astronautics

Spacecraft

Attitude control

244 322, B64G 126

Patent

active

RE0304298

ABSTRACT:
Spacecraft nutation caused by applying attitude and/or orbit control forces to a spacecraft along an axis which does not pass through the spacecraft's center of gravity is minimized by a signal responsive control system which first operates the attitude and/or orbit control forces for a predetermined time period and automatically after an appropriate non-operating time period, the attitude and/or orbit control forces are again operated for the same predetermined time period.

REFERENCES:
patent: 2974594 (1961-03-01), Boehm
patent: 3135479 (1964-06-01), Badewitz
patent: 3384323 (1968-05-01), Gilbert et al.
patent: 3414214 (1968-12-01), Robinson et al.
patent: 3437288 (1969-04-01), Lam
patent: 3643897 (1972-02-01), Johnson
patent: 3695554 (1972-10-01), Phillips
patent: 3937423 (1976-02-01), Johansen
patent: 3977633 (1976-08-01), Keigler
patent: 3984071 (1976-10-01), Fleming
patent: 4023752 (1977-05-01), Pistiner et al.
P. C. Wheeler, "Two-Pulse Attitude Control of an Asymmetric Spinning Satellite" AIAA Guidance and Control Conference, 8-12-63.

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