A review is given of limitations on approach flight paths of V/STOL aircraft, including limits on descent angle due to maximum drag/lift ratio. A method of calculating maximum drag/lift ratio of tilt-wing and deflected slipstream aircraft is presented. Derivatives and transfer functions for the CL-84 tilt-wing and X-22A tilt-duct aircraft are presented. For the unaugmented CL-84 in steep descents the transfer function relating descent angle to thrust contains a right-half plane zero. Using optimal control theory, it is shown that this zero causes a serious degradation in the accuracy with which steep flight paths can be followed in the presence of gusts.


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    Title :

    Fundamental limitations on V/STOL terminal guidance due to aircraft characteristics


    Contributors:

    Publication date :

    1971-12-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :


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