The invention belongs to the technical field of aviation structural design, and relates to a structural design method for an internal balance self-adaptation bump air inlet channel. The structural design method comprises the steps that a deformed region is selected on a bump molded surface of the air inlet channel; flexible skin is formed by compositing elastic adhesive films and high-elastic fibers; an outer side sealing cavity is formed between the basic molded surface of the air inlet channel and the outer side flexible skin, and an inner side sealing cavity is formed between the basic molded surface of the air inlet channel and the inner side flexible skin; the initial shape of the flexible skin is consistent with the basic molded surface of the internal balance self-adaptation bump air inlet channel; the air inlet channel is provided with a deformation driving device. Under the control of the deformation driving device, the shape of the flexible skin of the internal balance self-adaptation bump air inlet channel can be changed. According to the structural design method, the problem that the molded surface of a conventional bump air inlet channel cannot be adjusted is solved, the air inlet channel have the best pneumatic performance and the inlet engine compatibility characteristics under different flight states, and the good engineering applicability is achieved.


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    Title :

    Structural design method for internal balance self-adaptation bump air inlet channel


    Contributors:
    QIU TAO (author) / JIN CHENGZHONG (author) / ZHOU YIXUN (author) / WANG YAN (author) / ZHANG YINXUAN (author) / WANG JIANZHI (author)

    Publication date :

    2015-05-06


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



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