AIRPLANE WINGTIP DEVICE

• Main Authors: LIU, Tiejun, ZHANG, Miao, ZHOU, Feng, CHEN, Yingchun, YU, Zhehui, ZHANG, Dongyun, ZHANG, Meihong, MA, Tuliang, WANG, Junhong
• Format: Patent
• Language: English; French; German
• Published: 26.06.2019
• Subjects: AEROPLANES; AIRCRAFT; AVIATION; COSMONAUTICS; HELICOPTERS; PERFORMING OPERATIONS; TRANSPORTING

An aircraft wingtip device, comprising a transition part (1) and a wingtip part (2); the inner end of the transition part (1) is connected to the far end of an aircraft wing, and the outer end of the transition part is connected to the wingtip part (2); the wingtip part comprises a plurality of wingtip sections (3 n ), and each wingtip section (3 n ) comprises a wingtip (4 n ) and a wing root (5 n ) respectively; the wing root (5 1 ) of the first wingtip section (3 1 ) is connected to the outer end of the transition part (1), the wing root (5 n+1 ) of the n+1 wingtip section (3 n+1 ) is located on the wingtip (4 n ) of the n wingtip section (3 n ), and the chord length of the wing root (5 n+1 ) of the n+1 wingtip section (3 n+1 ) is smaller than or equal to the chord length of the wingtip (4 n ) of the nth wingtip section (3 n ), where n > 0. Because the wingtip device of the present invention is disposed in a stepped fashion, more than one discontinuity surface is added to the wingtip thereof, so that the wingtip vortices induced by the wingtip suppress each other, thereby reducing the strength of the vortices, and thus achieving drag reduction effect. In addition, the wing root of the present invention has a smaller bending moment increment, thus reducing the structural weight of the airplane and having less effect on the flutter properties.