| Control moment gyroscope is applied in agilely control of middle-scale and large-scale spacecraft due to its large moment output.This subject researched three-axis attitude agile control of large-scale flexible satellites which is in argumentation and use the control moment gyroscope as implement machine.This paper mainly researched on singularity elusion of control moment gyroscope,vibration suppressing of flexible appendages and clipping stabilization after attitude maneuver.Firstly,the structure,singularity and manipulation of control moment gyroscope was analyzed.A control method of manipulation which rely on real time determinant of singularity value was indexed.Secondly,the method of path planning based on the feedback of quaternion was described.A cosine transition acceleration path was advanced in orser to supress the vibration flexible appendages.The capability and superiority of the path planning algorithm was testfied through the simulation.Finally,in order to search advanced control arithmetic,error attitude dynamics and kinematics of satellites based on path planning was inferred.A “feed forward with PD” controller based on inertia identify,variable structure of output feedback controller.,and through the air bearing table test verified. |
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