When a control surface fails during aircraft flying, reconfigurable control system with new configuration aims to use the other available control surfaces and attempts to preserve the design properties of the original system. Restoring transient response is particularly important when transition from damaged to healthy configuration takes place. In this article, a new design procedure for robust transient response of the reconfigured system is presented. A linear algebraic formulation for right eigenstructure assignment in state feedback format is derived. A system of linear equations for the controller is solved. Reconfigurable control using an F-18 model is illustrated.
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