Patent ID: 8210062
Filing Date: 2012-07-03
Classification: B64G,Y10T

Abstract:
1. A directional control array for a spacecraft comprising: a) a first control moment gyroscope having a first rotor, a first spin motor to spin the first rotor about a first rotor axis, and a first gimbal motor to rotate the first rotor about a first gimbal axis that is normal to the first rotor axis; b) a first spin motor/generator driver adapted to extract stored kinetic energy from the first rotor as the first rotor is decelerated during a period of peak spacecraft torquing; c) a first gimbal motor driver adapted to receive extracted energy delivered directly from the first spin motor/generator driver to power the first gimbal motor; d) a second control moment gyroscope having a second rotor, a second spin motor to spin the second rotor about a second rotor axis, a second gimbal motor to rotate the second rotor about a second gimbal axis that is normal to the second rotor axis; e) a second spin motor/generator driver adapted to extract stored kinetic energy from the second rotor as the second rotor is decelerated during said period of peak spacecraft torquing; and f) a second gimbal motor driver adapted to receive extracted energy delivered directly from the second spin motor/generator driver to power the second gimbal motor.