Abstract A control technique is proposed for satellite attitude slew maneuvers, where the reference trajectory is specified as a function of time. A feedforward steering law, capable of avoiding singular states, is generated by a local optimization technique where, in the framework of integration methods, an inverse simulation problem is solved. A novel tracking controller is developed to account for model uncertainties and external disturbances. Physical limitations of the system in terms of maximum command rates and angles of gimbals and/or maximum command torque can be precisely accounted for in the determination of the control profile. Finally, the inverse simulation algorithm appears highly efficient in terms of computational time.
A Local Optimization Technique for Attitude Motion Tracking Using Control Moment Gyroscopes
2002
Article (Journal)
English
A Local Optimization Technique for Attitude Motion Tracking Using Control Moment Gyroscopes
Online Contents | 2002
|A Local Optimization Technique for Attitude Motion Tracking Using Control Moment Gyroscopes
Springer Verlag | 2002
|British Library Conference Proceedings | 2001
|British Library Conference Proceedings | 2001
|Controllability of spacecraft attitude using control moment gyroscopes
Tema Archive | 2009
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