The invention belongs to a servo actuation system for a leading edge flap of a mechanical double-redundancy airplane. The servo actuation system comprises a leading edge flap steering engine (1), a right distributing mechanism (7) and a left distributing mechanism (14), wherein the right distributing mechanism (7) and the left distributing mechanism (14) are connected with the leading edge flap steering engine (1) through hydraulic pipelines via a hydraulic signal; an output rocker arm of the leading edge flap steering engine (1) is connected with a steering engine draw bar (4); and the other end of the steering engine draw bar (4) is connected to a right fan-shaped rocker arm assembly (5). The servo actuation system for the leading edge flap of the mechanical double-redundancy airplane is controlled by double steel cables; meanwhile, certain synchronous adjustment measures are adopted; and the system is good in synchronous property in movement, high in reliability and good in safety.


    Access

    Download


    Export, share and cite



    Title :

    Servo actuation system for leading edge flap of mechanical double-redundancy airplane


    Contributors:
    ZHANG JIAN (author) / SUN YONGHUAN (author) / CHU BING (author) / ZHANG LEI (author)

    Publication date :

    2015-04-29


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge




    Airplane flap redundancy control system and method

    WANG YAPING / WANG XUEPING / FENG SHUJUN et al. | European Patent Office | 2022

    Free access

    Distributed multi-redundancy aircraft control surface servo actuation system

    SUN HUANYU / LUO JIANING / LIU ZHENYU et al. | European Patent Office | 2024

    Free access

    LEADING EDGE FLAP

    COMMIS BEN / LYONS NEIL / KAY EDMUND | European Patent Office | 2023

    Free access

    LEADING EDGE FLAP

    GARVER THEODORE M | European Patent Office | 2017

    Free access