Abstract
AbstractA linear optimal proportional plus integral (PI) controller is designed for a lateral aircraft model such that an approximately decoupled closed‐loop step response is obtained for the roll angle and side‐slip angle while the linear optimal feedback gains are simultaneously minimized. A standard mathematical programming algorithm is employed to calculate the diagonal state weighting matrix Q such that the specifications are satisfied. The synthesis procedure consists of the iterative minimization of a functional where at each iteration step a linear optimal control problem is solved.
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