This study is to explore the application of electrorheology (ER) to the real-time control of damping forces that are transmitted through the nose landing gear for an F-106B aircraft. The main part of the landing gear is a strut that consists of a pneumatic spring and an ER controlled damper that is situatted on the strut centerline and applies a force directly opposing the vertical displacement of the nose wheel. The damping element rotates in response to strut displacement, employing a co-axial arrangement of stator and rotor plates connected to the opposing electrodes in the control circuit. The vertical displacement is conveted into rotation of the damper through a screw-nut mechanism. The ER fluid between the electrodes is thus engaged in shear along circumferential lines of action. This design results in a fast time response and a high ratio of strut forces achieved under Er-vs. zero-field control. Compact size and simplicity in fabrication are also attained. The analysis shows that when using an ER fluid of a yield stress of 7kPa, the energy absorption efficiency of the landing gear can reach almost 100% at various sink rates.


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    Title :

    An electrorheologically controlled semi-active landing gear


    Contributors:

    Conference:

    SAE, Aerospace Atlantic Conference & Exposition ; 1993 ; Dayton, OH, United States


    Publication date :

    1993-01-01



    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    An Electrorheologically Controlled Semi-Active Landing Gear

    Winkler, Christopher B. / Filisko, Frank E. / Ervin, Robert D. et al. | SAE | 1993


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