The invention belongs to the technical field of helicopter anti-icing, and relates to a dual-redundancy helicopter air inlet channel hot air anti-icing control system which comprises an air inlet channel, a dual-redundancy electric valve, a main switch, a hot air pipeline, an electromechanical management computer, an auxiliary switch, a temperature sensor and other components. The auxiliary redundancy control unit adopts open-loop control, is simple and reliable and is suitable for emergency control when the main redundancy control unit breaks down, the two control systems are independent of each other, and the reliability of an anti-icing system of the air inlet duct can be effectively improved.

    本发明属于直升机防冰技术领域,涉及一种双余度直升机进气道热气防冰控制系统,包括:进气道、双余度电动阀门、主开关、热空气管路、机电管理计算机、副开关、温度传感器等零组件,系统工作时,通过主余度控制单元进行闭环控制,精确调节进入进气道的热空气流量,副余度控制单元为开环控制,简单可靠,适用于主余度控制单元故障时的应急控制,两个控制系统相互独立,可以有效提高进气道防冰系统的可靠性。


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    Title :

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


    Additional title:

    一种双余度直升机进气道热气防冰控制系统及一种直升机


    Contributors:
    CHEN JIAPENG (author) / XU CHAOLIANG (author) / ZHOU LEE (author) / XIE ZHIPING (author) / SHI JIN (author)

    Publication date :

    2024-02-23


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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