A landing gear system for an aircraft includes a retractable landing gear assembly (12), a hydraulic actuator (20) for actuating movement part, for example a bogie (14) of the landing gear assembly, and an accumulator (40) associated with the actuator. The accumulator (40) comprises a volume of pressurised gas (in chamber 44) separated from hydraulic fluid (45) by a separator piston (42). Travel of the separator piston (42) beyond a certain position (line 33) is indicative of a fault. The accumulator (40) includes a snubbing device (cups 50, 52) that acts to slow movement of the separator piston (42) beyond that position. A monitoring system (60) measures the time taken for the movement of the landing gear part effected by the hydraulic actuator (20). If the measured time is longer than a threshold time, that is indicative of a possible fault in the accumulator (40), that might, without the snubbing, remain undetected and/or hidden from view.


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    Title :

    HYDRAULIC ACTUATOR AND ACCUMULATOR ARRANGEMENT


    Additional title:

    HYDRAULISCHE AKTUATOR- UND SPEICHERANORDNUNG
    ENSEMBLE D'ACTIONNEUR HYDRAULIQUE ET ACCUMULATEUR HYDRAULIQUE


    Contributors:

    Publication date :

    2019-11-20


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen / B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F15B SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL , Druckmittelbetriebene Systeme allgemein



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