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An aircraft structure component for laminar flow

A technology for structural components and aircraft, applied to aircraft parts, affecting the air flow passing through the surface of the aircraft, coatings, etc., can solve problems such as increasing the aerodynamic resistance of aircraft structural components

Active Publication Date: 2018-05-25
AIRBUS OPERATIONS GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, this process leaves an edge line in the form of a thickness jump at the aerodynamic surface between the unpainted leading edge portion and the painted downstream portion
such a jump in thickness increases the aerodynamic drag of the structural components of the aircraft, as it negatively affects the laminar flow that exists in the leading edge section

Method used

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  • An aircraft structure component for laminar flow
  • An aircraft structure component for laminar flow
  • An aircraft structure component for laminar flow

Examples

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Embodiment Construction

[0023] figure 1 A first embodiment of an aircraft structural component 1 for laminar flow, in this case a slat, is shown in . The aircraft structural part 1 has a skin 3 with an aerodynamic surface 5 adapted to come into contact with an aerodynamic flow. Said aerodynamic surface 5 has a leading edge portion 7 which is directed towards the incoming airflow 9 of the aircraft concerned during flight and is therefore suitable for laminar flow. The aerodynamic surface 5 also has a downstream portion 11 adjacent downstream of the leading edge portion 7 with respect to the incoming airflow 9 . The downstream part 11 of said aerodynamic surface 5 comprises a paint layer 13 which is absent in the leading edge part 7 without paint, so that there is a line between the leading edge part 7 and the downstream part 11 through the initial paint layer 13. An edge line 15 in the form of a thickness jump, wherein the edge line 15 extends across the incoming air flow 9 . Such as figure 2 As ...

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PUM

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Abstract

An aircraft structure component (1) for laminar flow, the aircraft structure component (1) having an outer skin (3) with an aerodynamic surface (5), wherein the aerodynamic surface (5) has a leading edge portion (7) and a downstream portion (11) adjacently downstream from the leading edge portion (7), and wherein the downstream portion (11) of the aerodynamic surface (5) comprises a paint layer (13) that is not present in the leading edge portion (7), so that an edge line (15) is formed between the leading edge portion (7) and the downstream portion (11) by the beginning paint layer (13). Theobject, to provide an aircraft structure component that allows for a reduced aerodynamic drag, is achieved in that the edge line (15) has a ramp-shaped cross section (17), wherein the thickness of thepaint layer (13) increases from a starting point (19) over a predetermined ramp length (21) to a saturation point (23) where the full thickness (25) of the paint layer (13) is reached.

Description

technical field [0001] The invention relates to an aircraft structural component for laminar flow, such as a wing, a slat, a drooping nose, a horizontal or vertical tail surface or parts thereof. The aircraft structural component has a skin with an aerodynamic surface. An aerodynamic surface is referred to as the outer surface of said aircraft structural component that is in contact with the aerodynamic air flow circulating around the aircraft structural component. [0002] The aerodynamic surface has a leading edge portion and a downstream portion. The leading edge portion is directed in the direction of the incoming airflow during flight of the aircraft concerned and is adapted to a laminar flow circulating along the leading edge portion. The downstream portion is positioned adjacently downstream of the leading edge portion relative to the incoming airflow. The downstream portion of the aerodynamic surface comprises a paint layer which is absent in the leading edge portio...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C1/38B64C1/00
CPCB64C1/00B64C1/38B64C23/005B64C2230/00Y02T50/10B64C21/10B05D3/007B64C3/26B05D5/00B64C5/02B05D3/12B05B12/28
Inventor 伯恩哈德·施利普夫多特·丹德尔斯
Owner AIRBUS OPERATIONS GMBH
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