Abstract
The decoupled control of an optimally designed space structure is considered. The optimal structure is a derivative of the CSDL I model spacecraft. In particular, the effects of structural perturbations on the optimal design are considered. The stiffness matrix for the structure is perturbed by changing the areas of its rod members. A LQR controller, with modal suppression is designed for the nominal system. The controller is used on the perturbed systems and the effects on modal suppression noted. The spillover into the suppressed modes due to perturbations is also quantified in terms of the change in the row and column space of the control and observation matrices, respectively. The results obtained are compared to those obtained for the nominal CSDL I model.
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