Derivation of an automatic aircraft elevator controller
derivationofauto00niel.pdf (2.610Mb)Abstract
An automatic elevator controller for the final phase of an Instrument Landing System approach is designed using optimization theory and the practicality of the controller investigated. The problem is discussed and the assumptions stated. Then a mathe- matical model for the aircraft and a desired flare-out approach path are derived. The aircraft and approach limitations are established and the model is tested.
Dynamic programming and the Parametric Expansion Method provide the optimal control from which the controller is designed. A computer program is developed to investigate the controller. The results are inconclusive and a recommendation for further study is made.
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