Abstract The paper focuses on the aircraft automatic control in longitudinal plane, during landing, taking into account the sensor errors and disturbances. Aircraft auto-landing is achieved by combining the mixed H 2 / H and the dynamic inversion control techniques and by using an optimal observer, the geometry of landing, and two reference models. The general control law will consist of a guidance component for the commanded landing trajectory (calculated by using the dynamic inversion approach) and an optimal component which will be designed by means of a mixed H 2 / H technique for the cancel of the sensor errors and other disturbances in the system. The theoretical results are validated by numerical simulations for the landing of a Boeing 747; the simulation results are very good, Federal Aviation Administration accuracy requirements for best category being met.


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    Title :

    Application of H2/H∞ and dynamic inversion techniques to aircraft landing control


    Contributors:

    Published in:

    Publication date :

    2015-07-11


    Size :

    13 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





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