In order to improve space distribution, reduce weight and increase aerodynamic performance in a high lift device (20), an actuator device (24) for a fixed leading edge member (26) is proposed. The fixed leading edge member (26) has an inner cavity (48) defined by an outer skin (44) and ribs (46). The actuator device (24) comprises at least one geared rotary actuator (42) that moves along the arcuate section (52) relative to the other portion during extension and retraction of the high lift device (20) between a fully retracted position and a fully extended position. The actuator (40) is movable between a fully retracted position in which the actuator (40) is housed predominantly in the inner cavity (48) and an extended position in which the actuator (40) is located predominantly outside the inner cavity (48), preferably protruding through the D-shaped nasal incision (50).
为了在高升力装置(20)中改善空间分配、减轻重量和增加空气动力学性能,提出了一种用于固定的前缘构件(26)的致动器装置(24)。固定的前缘构件(26)具有由外蒙皮(44)和肋(46)限定的内腔(48)。致动器装置(24)包括至少一个齿轮式旋转致动器(42),所述至少一个齿轮式旋转致动器在高升力装置(20)在完全缩回位置与完全伸出位置之间的伸出和缩回期间沿着圆弧部段(52)相对于其他部分移动。在完全缩回位置中,致动器(40)主要被容纳在内腔(48)中,并且在伸出位置中,致动器(40)主要位于内腔(48)的外部、优选地突出通过D形鼻切口(50)。
Actuator device for fixed leading edge member of aircraft, wing assembly and aircraft equipped with said actuator device
用于飞行器的固定的前缘构件的致动器装置、机翼组件及配备有所述致动器装置的飞行器
11.03.2022
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |
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