Much more functions and higher quick maneuver were required with the development of aerospace technology. Thus the development of large currently

quick small satellites with high precision and stabilization has been one of the key trends. And from the comprehensive survey of satellite development in foreign countries

the Single Gimbal Control Moment Gyroscope (SGCMG) is a commonly used controller in the control system of large satellites. The SGCMG is excelled from traditional flywheel systems from the performance

but existed singularity problems. Especially used SGCMG in the small satellite

the singularity problems is all the more prominence. Therefore

the research on SGCMG is concentrate don’t he steering law study for avoiding singularity. This paper

aimed at crucial problems in the application of SGCMG to quick small satellites

is studied to afford basis for the application of moment gyroscope in aerospace engineering. Used model of small satellites with rigid bodies

Educed switch control for with reason adjust toques of small satellite with SGCMG

and avoided saturation singularity. Used pseudo-inverse steer lay with zero-motion control SGCMGs. As a result of the simulation

small satellite has been all right capability of large angle maneuver

rotated 45° at 14s

average rate achieve 3.2°/s. Proved out this switch Arithmetic has meet need of quick small satellite.