The invention belongs to the technical field of helicopter hydraulic systems, and particularly relates to a dual-redundancy helicopter hydraulic system and a control method. The first hydraulic subsystem is used for supplying pressure to the first main propeller steering engine cavity and the first tail propeller steering engine cavity so as to drive the main propeller steering engine and the tail propeller steering engine to work. The second hydraulic subsystem is used for supplying pressure to a main oar steering engine cavity II and a tail oar steering engine cavity II so as to drive a main oar steering engine and a tail oar steering engine to work; the first hydraulic subsystem comprises a hydraulic oil tank, a hydraulic pump, a first pressure sensor, a first pressure switch, a first main rudder stop valve, a first tail rudder stop valve, an oil return filter and a first multi-stage low oil level switch; the hydraulic pump is driven by the main speed reducer, sucks low-pressure oil from the hydraulic oil tank, converts the low-pressure oil into high-pressure oil, and supplies pressure to the main rotor steering engine and the tail rotor steering engine through the first main rotor stop valve and the first tail rotor stop valve respectively; the second hydraulic subsystem and the first hydraulic subsystem are the same in structure.

    本发明属于直升机液压系统技术领域,具体涉及一种双余度直升机液压系统及控制方法,系统包括:第一液压子系统和第二液压子系统;第一液压子系统用于为主桨舵机一腔和尾桨舵机一腔供压以驱动主桨舵机和尾桨舵机工作;第二液压子系统用于为主桨舵机二腔和尾桨舵机二腔供压以驱动主桨舵机和尾桨舵机工作;第一液压子系统包括:液压油箱、液压泵、第一压力传感器、第一压力开关、第一主舵切断阀、第一尾舵切断阀、回油滤、第一多级低油面开关;液压泵由主减速器驱动,从液压油箱中吸入低压油,转换为高压油后经过第一主桨切断阀和第一尾桨切断阀分别为主桨舵机和尾桨舵机供压;所述第二液压子系统与第一液压子系统结构相同。


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Dual-redundancy helicopter hydraulic system and control method


    Weitere Titelangaben:

    一种双余度直升机液压系统及控制方法


    Beteiligte:
    YANG SIRUI (Autor:in) / HUANG SHENG (Autor:in) / XU FENG (Autor:in) / WANG YE (Autor:in) / BAO JIAFENG (Autor:in) / HUANG YONGPING (Autor:in)

    Erscheinungsdatum :

    26.11.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



    Dual-redundancy helicopter air inlet channel hot air anti-icing control system and helicopter

    CHEN JIAPENG / XU CHAOLIANG / ZHOU LEE et al. | Europäisches Patentamt | 2024

    Freier Zugriff

    Dual-redundancy hydraulic rotor tilting mechanism control system

    SU QI / LIU JINYUAN / ZONG HUAIZHI et al. | Europäisches Patentamt | 2024

    Freier Zugriff

    Helicopter tail cabin door folding and unfolding dual-redundancy control system and method

    XI JIASHENG / YANG SIRUI / SHAO JIAQING et al. | Europäisches Patentamt | 2025

    Freier Zugriff

    Crossed dual-rotor unmanned helicopter and dual-power redundancy switching system

    YIN MINGWEI / ZENG FACAI / BAO CHANGCHUN et al. | Europäisches Patentamt | 2024

    Freier Zugriff

    Dual-redundancy electric power system suitable for light electric helicopter

    WANG SHULI / LI ZI'ANG / YANG FENGTIAN et al. | Europäisches Patentamt | 2023

    Freier Zugriff