The invention discloses an aircraft wingtip with a vibration and noise reduction mechanism, and relates to the technical field of aircraft wing structure design. The wingtip comprises a wingtip base plate, a connecting framework, a supporting plate and a balance weight mechanism, the balance weight mechanism comprises a front driving cylinder and a rear driving cylinder which are electric hydraulic cylinders, and the wingtip further comprises an adjusting motor, an adjusting lead screw, a front balance weight block and a rear balance weight block. According to the invention, the gravity center of the wing is changed by adding a counterweight structure, so that the vibration and noise reduction function is realized through stress balance; in actual assembly, the wing or the wingtip is divided into the front wing area and the rear wing area according to the specific structure and the stress condition of the wing or the wingtip, the front wing area is large in stress and amplitude, and therefore a balancing weight used for vibration reduction is large; besides, a front driving cylinder, a rear driving cylinder, an adjusting motor and an adjusting lead screw are arranged and serve as mechanisms for longitudinally and transversely moving the front balancing weight and the rear balancing weight respectively, the front balancing weight and the rear balancing weight can be matched with each other to act on a high-frequency vibration site, and the damping effect on the site is achieved.

    本发明公开了带有减振降噪机构的飞机翼尖,涉及飞机机翼构造设计技术领域。本发明包括翼尖基板、连接骨架、支撑板和配重机构,其中配重机构包括前驱动缸和后驱动缸,两者均为电动液压缸,还包括调节电机、调节丝杆、前配重块和后配重块。本发明采用的增加配重结构来改变机翼重心从而以受力平衡实现减振降噪功能的方式;在实际装配中,根据机翼或翼尖具体结构和受力情况分为前翼区和后翼区,前翼区受压大,振幅大,因此用于减振的配重块就较大;另外,通过设置前驱动缸、后驱动缸、调节电机和调节丝杆,分别作为前后两个配重块进行纵向和横向的位置移动机构,能够使前后两个配重块相互配合作用在高频振动位点,实现对该位点的减震效果。


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    Titel :

    Aircraft wingtip with vibration and noise reduction mechanism


    Weitere Titelangaben:

    带有减振降噪机构的飞机翼尖


    Beteiligte:
    YOU YUNHONG (Autor:in) / YOU XIA (Autor:in) / WANG YONG (Autor:in) / LIU WEIJUN (Autor:in) / ZHU RONGWEN (Autor:in)

    Erscheinungsdatum :

    2022-12-30


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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