Airplane wingtip device with aligned back edges

A wing tip and aircraft technology, applied in the wing shape, heat reduction structure and other directions, can solve the problems of aircraft flutter characteristics, large bending moment, increase structural weight and other problems, achieve small flutter characteristics, weaken eddy current strength, reduce The effect of structural weight

Active Publication Date: 2011-08-31
COMAC +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0009] Although the up-trans winglets and wingtip sails have obvious drag reduction effects, both the winglets and the wingtip sails have relatively large be

Method used

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  • Airplane wingtip device with aligned back edges
  • Airplane wingtip device with aligned back edges
  • Airplane wingtip device with aligned back edges

Examples

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Embodiment Construction

[0045] Such as figure 1 with figure 2 As shown, in one embodiment of the present invention, the aircraft wingtip device is in a multi-step shape, which includes a transition portion 1 and a wingtip portion 2, and the inner end of the transition portion 1 is connected to the far end of the aircraft wing 6 , the connection between the outer end of the transition portion 1 and the wing tip 2, wherein the wing tip includes a plurality of wing tip segments 3 n , each wingtip segment includes wingtip 4 n and wing root 5 n , the first wingtip segment 3 1 wing root 5 1 Connected to the outer end of the transition portion 1 and aligned with the trailing edge of the outer end of the transition portion 1, the n+1th wing tip segment 3 n+1 wing root 5 1 Located at the nth wingtip segment 3 n Wingtip 4 n on, and the n+1th wingtip segment 3 n+1 wing root 5 1 The chord length is less than the nth wingtip segment3 n Wingtip 4 n Chord length, where n>0. Additionally, if figure 1 ...

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PUM

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Abstract

The invention discloses an airplane wingtip device, which comprises a transition part and a wingtip part, wherein the end part of the inner side of the transition part is connected with the far end of an airplane wing; the end part of the outer side of the transition part is connected with the wingtip part; the wingtip part comprises a plurality of wingtip sections; each wingtip section comprises a wingtip and a wing root respectively; the wing root of the first wingtip section is connected with the end part of the outer side of the transition part, and is aligned with the back edge of the end part of the outer side of the transition part; the wing root of the (n+1)th wingtip section is positioned on the wingtip of the nth wingtip section; the chord length of the wing root of the (n+1)th wingtip section is smaller than or equal to that of the wingtip of the nth wingtip section; and n is more than 0. The wingtip device disclosed by the invention is arranged in a step form, and each wingtip is provided with more than one discontinuity surface, so that wingtip vortexes induced from the wingtips suppress one another, the vortex intensity is weakened, and the resistance reducing effect is achieved; moreover, the bending moment increment of the wing roots is smaller, so that the structural weight of the airplane is lightened, and the influence on flutter characteristic is smaller.

Description

technical field [0001] The invention relates to a wingtip device of an aircraft wing. Background technique [0002] The lift required for the aircraft to maintain normal flight is generated by the pressure difference between the upper and lower surfaces of the wing. Due to the existence of the pressure difference between the upper and lower surfaces, the air on the lower surface of the wing near the wingtip will flow around to the upper surface, forming a wingtip vortex, causing the wing The pressure difference between the upper and lower surfaces of the wing in the area near the tip is reduced, resulting in a decrease in the lift generated in this area. [0003] In view of the above problems, winglets (winglets) are usually arranged on the wingtips of the aircraft wings. The main function of the winglets is to increase the effective aspect ratio without increasing the span length of the aircraft. In this way, the two-dimensional effect of the wing is enhanced, the induced ...

Claims

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Application Information

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IPC IPC(8): B64C3/10B64C3/36
Inventor 陈迎春张淼薛飞刘铁军张美红汪君红于哲慧周峰张冬云马涂亮
Owner COMAC
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