Abstract Articulated landing gears have relatively lower stowage volume and provide better taxiing characteristics when compared to telescopic gears. Unlike telescopic configuration, the articulated configurations do not have the same stroke for wheel axle and shock absorber travel. The objective of this work is to study and compare the dynamics of the articulated main landing gear, during level and tail-down landing conditions, using MSC/ADAMS software. The results are compared with the available landing gear analysis program, which has been experimentally validated by the drop tests. A 12.3% reduction in total vertical wheel axle travel is observed in tail-down condition when compared to level landing, due to the kinematic configuration. It results in 18.9% and 14.8% increase in dynamic load in limit and reserve landing respectively for tail-down condition. Also, the tire deflections are relatively higher and the shock absorber travel is relatively lower, in tail-down landing for both limit and reserve conditions.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Dynamics of Articulated Landing Gear in Tail-Down Landing Condition


    Contributors:


    Publication date :

    2018-08-29


    Size :

    12 pages





    Type of media :

    Article/Chapter (Book)


    Type of material :

    Electronic Resource


    Language :

    English




    Routings for articulated landing gear

    REBER KOREY M / MILSOM DEREK C | European Patent Office | 2019

    Free access

    Routings for articulated landing gear

    REBER KOREY M / MILSOM DEREK C | European Patent Office | 2016

    Free access

    SEMI-LEVERED ARTICULATED LANDING GEAR SYSTEM

    WILSON PHILLIP K | European Patent Office | 2016

    Free access

    Rotorcraft Slope Landings with Articulated Landing Gear

    Manivannan, Vasudevan / Langley, Jared P. / Costello, Mark et al. | AIAA | 2013


    Landing gear tail wheel lock

    WANG LE / FANG JIANYI | European Patent Office | 2023

    Free access