Attitude control for small satellites using control moment gyros

In this paper a new Attitude Control System is proposed, based on Control Moment Gyroscopes (CMG). These actuators can provide unique torque, angular momentum and slew rate capabilities to small satellites without any increase in power, mass or volume. This will help small satellites become more agile. Agility considerably increases the operational envelope and efficiency of spacecraft and substantially increases the return of earth and science mission data. In the proceeding sections the fundamental features of CMGs are presented. A low cost, miniature SGCMG designed for an enhanced microsatellite is analysed. Sizing of a proposed SGCMG indicates the advantages of using CMGs. The SGCMG is able to produce a torque of 9.82 mNm and this is confirmed through experiments performed on an air-bearing table. A comparison between the SGCMG and a RW demonstrates the mass and power savings that can be gained by using CMGs.