The invention belongs to an electric heating deicing technology, and particularly relates to a self-control anti-icing system and method for an engine lip. Comprising a lip anti-icing heating assembly and a lip anti-icing controller. The lip anti-icing heating assembly comprises a rubber sheet, a heating belt is laid on the rubber sheet, and a temperature sensor is integrated in the heating belt; the lip anti-icing controller comprises a control circuit module, a temperature acquisition module and a power circuit module; the heating belt is connected with the power circuit module through an electrode, and the temperature sensor is connected with the temperature acquisition module. The device has the advantages of being simple and reliable in structure, small in size, light in weight, resistant to salt mist and acid corrosion, capable of being applied to anti-icing and deicing operation of aircraft engine lips and similar parts with narrow space, important functions and complex structures, and high in practical application value.

    本发明属于电热除冰技术,具体涉及一种发动机唇口自控防冰系统及方法。包括唇口防冰加热组件和唇口防冰控制器;唇口防冰加热组件包括胶片,胶片上铺设有加热带,加热带内集成有温度传感器;唇口防冰控制器包括控制电路模块、温度采集模块及功率电路模块组成;加热带经电极与功率电路模块连接,温度传感器与温度采集模块连接。本发明具有结构简单可靠、体积小、重量轻、耐盐雾酸蚀,能够应用于飞机发动机唇口及类似空间狭小、功能重要、结构复杂部位的防除冰作业,具有较大的实际应用价值。


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    Titel :

    Engine lip self-control anti-icing system and method


    Weitere Titelangaben:

    一种发动机唇口自控防冰系统及方法


    Beteiligte:
    LI PEILIN (Autor:in) / LI HAIHONG (Autor:in) / LI PAN (Autor:in) / DU FUQIANG (Autor:in)

    Erscheinungsdatum :

    2024-03-08


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT




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