An attitude control system for a flight vehicle, the system comprising: a control moment gyro pair (20, 22, 24) that includes: a first control moment gyro (30, 34, 38) that includes a first flywheel rotatably mounted to a first frame, wherein the first flywheel rotates relative to the first frame about a first flywheel rotation axis that is perpendicular to the first flywheel; a second control moment gyro (32, 36, 40) that includes a second flywheel rotatably mounted to a second frame, wherein the second flywheel rotates relative to the second frame about a second flywheel rotation axis that is perpendicular to the second flywheel; and an actuator that selectively counter-rotates the first control moment gyro, and the second control moment gyro, so as to rotate the first flywheel rotation axis and the second flywheel rotation axis in opposite directions to cant the first control movement gyro relative to the second control movement gyro; wherein the actuator rotates the first flywheel and the first frame, and the second flywheel and the second frame, so as to rotate the first flywheel rotation axis and the second flywheel rotation axis within respective offset parallel planes; and wherein the first control moment gyro and the second control moment gyro are both rotated by the actuator about a common gyro pair rotation axis. a control moment gyro pair (20, 22, 24) that includes: a first control moment gyro (30, 34, 38) that includes a first flywheel rotatably mounted to a first frame, wherein the first flywheel rotates relative to the first frame about a first flywheel rotation axis that is perpendicular to the first flywheel; a second control moment gyro (32, 36, 40) that includes a second flywheel rotatably mounted to a second frame, wherein the second flywheel rotates relative to the second frame about a second flywheel rotation axis that is perpendicular to the second flywheel; and an actuator that selectively counter-rotates the first control moment gyro, and the second control moment gyro, so as to rotate the first flywheel rotation axis and the second flywheel rotation axis in opposite directions to cant the first control movement gyro relative to the second control movement gyro; wherein the actuator rotates the first flywheel and the first frame, and the second flywheel and the second frame, so as to rotate the first flywheel rotation axis and the second flywheel rotation axis within respective offset parallel planes; and a first control moment gyro (30, 34, 38) that includes a first flywheel rotatably mounted to a first frame, wherein the first flywheel rotates relative to the first frame about a first flywheel rotation axis that is perpendicular to the first flywheel; a second control moment gyro (32, 36, 40) that includes a second flywheel rotatably mounted to a second frame, wherein the second flywheel rotates relative to the second frame about a second flywheel rotation axis that is perpendicular to the second flywheel; and an actuator that selectively counter-rotates the first control moment gyro, and the second control moment gyro, so as to rotate the first flywheel rotation axis and the second flywheel rotation axis in opposite directions to cant the first control movement gyro relative to the second control movement gyro; wherein the actuator rotates the first flywheel and the first frame, and the second flywheel and the second frame, so as to rotate the first flywheel rotation axis and the second flywheel rotation axis within respective offset parallel planes; wherein the first control moment gyro and the second control moment gyro are both rotated by the actuator about a common gyro pair rotation axis.