Raytheon Company

Eero H Ala

Christopher P Owan

James P Mills

Nicholas D Trail

Michael P Schaub

Gregory P Hanauska

Clifton J Charlow

Anthony Vinson Damommio

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

Growing community of inventors

Tucson, AZ, United States of America

Eero H Ala