An attitude control system includes one or more control moment gyro pairs, with gyros of individual of the pairs being counter-rotated to rotate the rotation axes of flywheels of the gyros of a gyro pair in opposite direction. The flywheels of a gyro pair may be in paddle configuration, with the rotation axes of the flywheels rotating in the counter-rotation through separate planes as the gyros are rotated. The rotation of the gyros of a gyro pair may be accomplished by coupling both of the gyros to a servo motor with suitable coupling gears, or by using independent servos for each gyro. The counter-rotation of gyros of an individual pair produces a resultant torque about a fixed global axis, such as the axis of a flight vehicle of which the attitude control system is a part. Further control may be accomplished for example by varying rotation speeds of the flywheels.
GYROSCOPIC ATTITUDE CONTROL SYSTEM
GYROSKOPISCHES LAGEREGELUNGSSYSTEM
SYSTÈME GYROSCOPIQUE DE CONTRÔLE D'ATTITUDE
29.12.2021
Patent
Elektronische Ressource
Englisch
Gyroscopic attitude stabilization
AIAA | 1964
|GYROSCOPIC LOW-POWER ATTITUDE CONTROL - GLOPAC
AIAA | 1963
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