Research On Fast Attitude Maneuver Of Reconnaissance Satellites Based On Control Moment Gyros

The article chooses the large and very high-resolution reconnaissance satellitesfor study. We choose the control moment gyroscope control scheme as the mainimplementing agency considering the limit of the other implementing agencies inthe output torque and service life, with the purpose of large-scale reconnaissancesatellites can achieve fast, stable and long-life maneuver control.In this paper we described the model of spy satellite model with the controlmoment gyroscope system based on the Lagrange equation. The singularity problemwhich is impact on the control moment gyroscope serious is explored. We analyzeand simulate the common types of steering law and get practical effect to overcomethe singular.Considering of the situation of this paper, a method based on the robust inversecontrol law is used and a Multi-mode switching control algorithm based on thevariable speed control moment gyros (VSCMG) is presented. In the effective andreasonable avoid gyro output torque saturated singular, under the premise ofguarantee gyroscope can be variable speed rotor energy, rotational speed can be in astable state balance, so that the whole framework configuration envelope isreasonable, facilitate accurate output torque, so as to realize the rapid satelliteattitude maneuver control.Traditional controllers have the advantages of easy to implement, stable and soon, but advantage of limit to the fast maneuver of the large spacecraft. This paperdesigns a sliding mode variable structure controller which is based on the variablestructure theory and combines with the large spacecraft model to control the attitudedeviation, and further improve the attitude maneuver speed. In this article, thedistributed piezoelectric elements were used as actuators considering of theinfluence of satellite’s large size wing in the process of the maneuvers. According tothe vibration equation we use the strain rate feedback controller to make vibrationattenuate fast. At last, with the help of Matlab simulation experiments we indicatethat: This control scheme can meet the need of rapid attitude maneuver for largespacecraft.