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Leading edge flaps placed on the wings of an airplane

A leading edge flap and wing technology, applied in wing adjustment, aircraft parts, aircraft control and other directions, can solve problems such as unfavorable take-off

Active Publication Date: 2016-04-13
AIRBUS OPERATIONS GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

During such slots, which direct high energy air from the underside of the leading edge flap to the upper side of the main wing, it is beneficial for landing due to its effect of increasing lift and delaying boundary layer separation, and is therefore worth pursuing , which on the other hand is detrimental to takeoff due to the increased drag associated with it

Method used

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  • Leading edge flaps placed on the wings of an airplane
  • Leading edge flaps placed on the wings of an airplane
  • Leading edge flaps placed on the wings of an airplane

Examples

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Embodiment Construction

[0028] figure 1 A leading edge flap 12 provided on a wing of an aircraft is shown. The wing comprises a main wing 24 having an upper cladding 21 , a lower cladding 22 and a profile boss 23 . The spar 26 is provided as an internally supported structural member of the main wing 24 . The leading edge flap 12 is arranged on the front side of the main wing 24 and has a forwardly oriented profile bead 10 and a rearwardly oriented end edge 11 facing the main wing 24 .

[0029] Said leading-edge flaps 12 can be extended from a stowed cruising position I in order to increase lift in the chord direction with increased curvature and extension of the airfoil profile, in which leading-edge flaps 12 The center fits closely on the front side of the main wing 24, and its profile complements the shape suitable for cruising. In the partially extended first position II, the leading edge flap 12 rests against the main wing 24 by its terminal edge 11, which position can be referred to as the ta...

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PUM

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Abstract

A leading edge slat arranged on the aerofoil of an aircraft. The leading edge slat is provided on the front of the main wing. The leading edge slat has a partially extended setting, with its trailing edge flat against the wing, and a further extended setting, with its trailing edge spaced apart from the nose of the wing to open a gap feeding high-energy air from the lower surface of the slat to the upper surface of the wing. The leading edge slat includes a body and a trailing edge facing the main wing, which can be bent around the spanwise direction of the slat relative to the body, and on which the trailing edge of the slat is provided, and which by means of a device generating a contact force is loaded for making contact between the trailing edge of the slat and the profile nose of the wing.

Description

technical field [0001] The invention relates to a leading edge flap arranged on the wing of an aircraft. Background technique [0002] In order to improve the lift of the airfoil of an aerodynamically efficient airfoil, a large number of high-lift assemblies are known in the prior art for increasing the curvature and curvature of the airfoil profile in the direction of the chord / or stretch, and thus increase the lift of the wing. In high-lift assemblies, which are arranged on the front side of the airfoil profile with respect to the direction of flow, a distinction is made between the leading-edge flaps, which are connected essentially without interruption On the front side of the original wing or on the main wing, and the leading edge flap, here at least in the extended state, there is a slot between the rear edge of the leading edge flap and the front edge of the main wing, the high-energy , that is, the air flowing at high velocity is guided through the slot from the ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C9/24
CPCB64C9/24B64C2009/143B64C3/50
Inventor 伯恩哈德·施利普夫格扎维埃·于埃
Owner AIRBUS OPERATIONS GMBH
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