Minimization of residual spacecraft nutation due to...

Details Minimization of residual spacecraft nutation due to... Minimization of residual spacecraft nutation due to...

G - Physics

05

D

342/2, 325/78, 2

G05D 1/08 (2006.01)

Patent

CA 1041608

Abstract of the Disclosure 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.

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