A backup system is provided that has a local electric motor (42) and pump (41) for some or all of the hydraulic actuators on an aircraft. A local backup hydraulic actuator (27) has two power sources, hydraulic as primary and electrical as backup. During normal operation, the hydraulic actuator receives pressurized fluid from a hydraulic system (45) and the fluid flow to the chambers is controlled by a servo valve (44). If the hydraulic system fails, the electronic controller (55) detects the failure by observing the signal indicative of the pressure from the pressure sensor (48), and the controller powers the local hydraulic pump (41) to provide high pressure hydraulic fluid to the hydraulic actuator via the servo valve (44).


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    Title :

    LOCAL BACKUP HYDRAULIC ACTUATOR FOR AIRCRAFT CONTROL SYSTEMS


    Additional title:

    HYDRAULIKANTRIEB MIT LOKALER UNTERSTÜTZUNG FÜR FLUGZEUGSTEUERUNGSSYSTEME
    ACTIONNEUR HYDRAULIQUE DE SAUVEGARDE LOCAL POUR SYSTÈMES DE COMMANDE D'AÉRONEF


    Contributors:
    MATSUI GEN (author)

    Publication date :

    2020-03-11


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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