Two control systems are assessed and tested over a range of incidence values, in order to evaluate the effectiveness of the designs. A suitable aircraft model is developed and aerodynamic data for the F16 fighter aircraft are used to ensure that the resulting longitudinal behavior of the model is unsatisfactory. The stability criteria are established and the existing defense standard criteria for the short period oscillation are selected. Both control systems produce better results when the designs are based on the fourth order model. The performance of a digital compensator is studied. The quantization and discretization errors are evaluated. An optimum sampling rate is selected. The effects of system delays on aircraft handling qualities are considered.


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    Title :

    Longitudinal Stability Augmentation of a Lightweight Fighter Aircraft Model


    Contributors:

    Publication date :

    1989


    Size :

    161 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English