A flight control law based on partial inversion of the longitudinal dynamics of a twin-jet transport aircraft is presented. The controller is partitioned into a slow-time-scale and a fast-time scale to simplify its design. Three types of controllers are developed: airspeed/climb rate, ground-speed/climb rate, and throttle/climb rate. For microburst encounters during approach to landing, it is found that a combination of airspeed and groundspeed regulation is quite effective for controlling the flight path to touchdown. Regulation of groundspeed to a nominal value in the performance-increasing region of the microburst prevents an inadvertent reduction in thrust, while regulation of airspeed to a nominal value in the performance-decreasing area of the microburst prevents excessive airspeed loss. The throttle/climb rate controller is used for aborted-landing encounters. The combination of groundspeed and airspeed control is used until the decision is made to abort the landing, at which point maximum throttle and a specified positive climb rate are commanded.


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    Title :

    Aircraft Flight Control in Wind Shear Using Partial Dynamic Inversion


    Contributors:

    Published in:

    Publication date :

    1993-06-01


    Size :

    591148 byte



    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English



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