An electro-hydrostatic actuator system (1) for raising/lowering a landing gear (11) of an aircraft includes: at least one hydraulic actuator (21, 22) configured to retract and extend the landing gear (11); a hydraulic circuit (33); a hydraulic pump (32); an electric motor (31); a controller (4) configured to control the operation of the electric motor at receiving a command to retract or extend the landing gear; and a sensor (34) detecting the discharge pressure of the hydraulic pump. The controller, when receiving the command, feeds back the discharge pressure detected by the sensor, and controls the operation of the electric motor such that the discharge pressure of the hydraulic pump reaches a target discharge pressure.


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    Title :

    ELECTRO-HYDROSTATIC ACTUATOR SYSTEM FOR RAISING AND LOWERING AIRCRAFT LANDING GEAR


    Additional title:

    ELEKTROHYDROSTATISCHES AKTUATORSYSTEM ZUM HEBEN UND SENKEN EINES FLUGZEUGFAHRWERKS
    SYSTÈME D'ACTIONNEUR ÉLECTRO-HYDROSTATIQUE DESTINÉ À LEVER ET ABAISSER UN TRAIN D'ATTERRISSAGE D'AÉRONEF


    Contributors:

    Publication date :

    2018-12-19


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / F15B SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL , Druckmittelbetriebene Systeme allgemein



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