Abstract
Control algorithms needed for an optimal automated aircraft guidance during the final landing phase are studied. A nominal landing trajectory is obtained by means of a nonlinean aircraft model. A feedback controller is designed using a linearized time-varying aircraft and a deterministic Markovian wind model. It minimizes the deviations between the nominal and the real trajectories (follow-up control) and warrants the fulfilment of soft and hard final conditions (final-value control). Both algorithms are tested in simulation studies using a nonlinear aircraft and a stochastic windmodel.
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