The invention belongs to airplane ice preventing and removing design, and particularly relates to an electric heating and self-lubricating composite ice preventing and removing functional structure. The structure comprises a self-lubricating coating, a protective layer and an electric heating layer from outside to inside, the protective layer, the electric heating layer and a machine body structure are jointly cured and formed, and the self-lubricating coating is sprayed to the surface of the protective layer. According to the structure provided by the invention, in terms of a working mode, alarge-area anti-icing and deicing design area can be intermittently electrified and heated in a partitioned manner, a single area is allowed to be iced to a certain degree in a cooling period, and anice layer area is electrified and heated after entering a heating period, so that the energy consumption is further reduced. Compared with a pure electric heating anti-icing and deicing method and anelectric heating and super-hydrophobic coating composite anti-icing and deicing method, the energy consumption is greatly reduced, and the ice preventing requirement of a large-area area can be met.
本发明属于飞机防除冰设计,具体涉及一种电加热和自润滑复合防除冰功能结构;其结构形式由外至内包含自润滑涂层、保护层、电热层;所述保护层、电热层与机体结构共同固化成形,自润滑涂层喷涂于保护层表面。本发明所提出的结构在工作方式上,可对大面积防除冰设计区域分区间断通电加热,允许单个区域在冷却周期结一定程度的冰,进入加热周期后,通电加热将冰层区域,从而进一步降低能耗。相比与单纯的电加热防除冰方法,以及电加热与超疏水涂层复合防除冰的方法,能耗大大降低,能够满足较大面积区域的防冰需求。
Electric heating and self-lubricating composite ice preventing and removing functional structure
一种电加热和自润滑复合防除冰功能结构
2021-04-02
Patent
Elektronische Ressource
Chinesisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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