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Aircraft structural components for laminar flow

A technology for structural parts and aircraft, applied in aircraft parts, affecting the air flow and coating on the surface of the aircraft, etc., can solve problems such as increasing the aerodynamic resistance of aircraft structural parts, reduce aerodynamic resistance, and be easy to manufacture. Effect

Active Publication Date: 2021-10-01
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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  • Aircraft structural components for laminar flow
  • Aircraft structural components for laminar flow
  • Aircraft structural components 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 . like figure 2 As sho...

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PUM

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Abstract

An aircraft structural component (1) for laminar flow, the aircraft structural component (1) having a skin (3) with an aerodynamic surface (5), wherein the aerodynamic surface (5) has a front edge portion (7) and a downstream portion (11) adjacently located downstream of said leading edge portion (7), and wherein the downstream portion (11) of the aerodynamic surface (5) includes The coating layer (13) of the coating layer (13), thereby forming an edge line (15) between the leading edge part (7) and the downstream part (11) through the initial coating layer (13). The invention achieves the object of providing a structural part of an aircraft allowing a reduced aerodynamic drag, since said edge line (15) has a ramp-shaped cross-section (17), wherein the thickness of the paint layer (13) is within a predetermined ramp length (21 ) from a starting point (19) to a saturation point (23), wherein the full thickness (25) of the paint layer (13) is reached at said saturation point.

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 Patents(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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