The invention relates to an aircraft wing trailing edge arrangement and an aircraft wing (4). The aircraft wing comprises a trailing edge system (12) comprising a pivotable spoiler (8) and a movable flap (6). The flap has a pivotable trailing edge device (e.g., a complementary wing 14) that can, for example, rotate up to +/-20 degrees independently of the flap. The flap can translate and rotate relative to the wing independently of the movement of the spoiler. In use, the trailing edge system is configured to employ one of several different configurations or modes of operation to facilitate cruise mode, high speed roll control mode and low speed roll control mode, enhanced high lift, and all camber and/or wing chord changes during load mitigation. Thus, the wing may not require any separate aileron or other trailing edge control surface, and may also provide improved aerodynamics, reduced drag, and other improved efficiency benefits.

    本发明涉及一种飞行器机翼后缘装置和一种飞行器机翼(4)。飞行器机翼包括后缘系统(12),该后缘系统包括可枢转的扰流器(8)和可移动的襟翼(6)。襟翼具有可枢转的后缘装置(例如,补翼14),该后缘装置例如能够独立于襟翼旋转高达+/‑20度。襟翼能够独立于扰流器的运动而相对于机翼平移和旋转。在使用中,后缘系统被构造成采用几种不同的构型或操作模式中的一种构型或操作模式,以有利于巡航模式、高速侧倾控制模式和低速侧倾控制模式、增强的高升力以及载荷减缓期间的所有的弯度和/或机翼翼弦变化。因此,机翼可能不需要任何单独的副翼或其他后缘控制表面,并且还可以提供改进的空气动力学、减小的阻力和其他效率提高的益处。


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    Title :

    Aircraft wing trailing edge device


    Additional title:

    飞行器机翼后缘装置


    Contributors:

    Publication date :

    2024-01-16


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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