An aircraft taxi control system may include a left main gear (MG) drive motor, a right MG motor, a first motor drive controller configured to produce a left motor torque signal responsively to nose gear angle (NGA) and nose wheel speed (NGS), and a second motor drive controller configured to produce a right motor toque signal responsively to the NGA and the NGS. The left motor torque signal and the right motor torque signal may be coordinated to reduce lateral loading of the nose wheel during a turning maneuver.


    Access

    Download


    Export, share and cite



    Title :

    DIFFERENTIAL STEERING CONTROL OF ELECTRIC TAXI LANDING GEAR


    Contributors:

    Publication date :

    2015-12-31


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / G05D SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES , Systeme zum Steuern oder Regeln nichtelektrischer veränderlicher Größen



    Landing Gear (Engine Off) Taxi System

    SAE Technical Papers | 2021


    Adaptive Landing Gear for Improved Taxi Performance

    P. T. Somm / H. H. Straub / J. R. Kilner | NTIS | 1977


    Landing gear steering system

    TIAN YU / DAI CHUNXU | European Patent Office | 2024

    Free access

    AIRCRAFT LANDING GEAR STEERING SYSTEM

    HUMPHREY RICHARD | European Patent Office | 2016

    Free access

    Landing taxi lamp

    WANG LIEYONG / LU QINGQING / WANG HAOYING | European Patent Office | 2022

    Free access