The landing gear systems, methods and apparatuses disclosed herein may comprise a shrink pump and an unshrink valve that are capable of shrinking a landing gear shock strut up to about 40% of its available stroke. The shrink pump may be configured to pump fluid (e.g., a hydraulic fluid) between an oil chamber, where hydraulic fluid is likely present and a shrink chamber to shrink the landing gear. Moreover, the shrink pump and unshrink valve may be part of a strut shrink system.


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    Titel :

    Shrink strut landing gear system, method, and apparatus


    Beteiligte:
    LUCE WILLIAM E (Autor:in)

    Erscheinungsdatum :

    26.04.2016


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / F16F SPRINGS , Federn



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