A method for the design of attitude control systems for flexible spacecraft is presented. The design procedure employs input-output linearization and stabilization techniques; computation of the sampled-data control laws, and compensation techniques are applied to reduce the influence of the flexible part on the control system design. An idealized test vehicle subject to a variety of control laws was simulated. The improvements obtained by using a sampled-data scheme with an extended control are evident from the results of the simulations.
Sampled Nonlinear Control for Large Angle Maneuvers of Flexible Spacecraft
1986
8 pages
Report
No indication
English
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