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Aircraft structure for flow control

A technology for airflow control and aircraft, applied in the field of aircraft structure, can solve the problems of increasing the weight of the aircraft structure and reducing the fatigue strength of the perforated panel

Pending Publication Date: 2020-09-04
AIRBUS OPERATIONS GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the micropores reduce the fatigue strength of the perforated panel because the micropores required to suck in or blow out air tend to initiate and propagate cracks through the perforated panel
Therefore, to achieve the required fatigue strength, higher panel thicknesses are required, however this increases the weight of the aircraft structure

Method used

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  • Aircraft structure for flow control
  • Aircraft structure for flow control
  • Aircraft structure for flow control

Examples

Experimental program
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Embodiment Construction

[0029] exist figure 1 In , an embodiment of an aircraft 1 according to the invention is shown. The aircraft 1 includes a fuselage 3 , wings 5 ​​, a vertical tail 7 and a horizontal tail 9 . At the wings 5 ​​, the vertical tail 7 and the horizontal tail 9 , the aircraft 1 comprises an aircraft structure 11 according to any one of the embodiments described below.

[0030] exist figure 2 In , a first embodiment of an aircraft structure 11 according to the invention is shown. The aircraft structure 11 comprises a perforated panel 13 having an inner surface 15 directed toward the interior 17 of the structure; an outer surface 19 in contact with the surrounding airflow 21; micropore23. The perforated panel 13 is formed of titanium material. A plurality of elongate crack arrest elements 25 are attached to the inner surface 15 of the perforated panel 13 parallel to each other. Crack arrest element 25 is configured to inhibit propagation of cracks within perforated panel 13 past...

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PUM

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Abstract

Disclosed is an aircraft structure (11) for flow control, comprising a perforated panel (13) having an inner surface (15) directed to a structure interior (17), an outer surface (19) in contact with an ambient flow (21), and a plurality of micro pores (23) connecting the inner and outer surfaces (15, 19). The object to reduce the weight of the aircraft structure while maintaining the required fatigue strength, is achieved in that one or more elongate crack stopper elements (25) are attached to the inner surface (15) of the perforated panel (13), and the crack stopper elements (25) are configured to inhibit crack propagation within the perforated panel (13).

Description

technical field [0001] The invention relates to an aircraft structure configured for air flow control, preferably for hybrid laminar flow control (HLFC). Another aspect of the invention relates to an aircraft comprising such an aircraft structure. Background technique [0002] The aircraft structure includes a perforated panel having an inner surface directed toward the interior of the structure; an outer surface in contact with the surrounding airflow; and a plurality of microperforations distributed over the perforated panel and connecting the inner surface and the outer surface. The perforated panels are preferably formed from a metallic material such as titanium. [0003] Such aircraft structures are known to be associated with HLFC systems in which air is drawn or blown through microscopic holes in perforated panels to favorably affect ambient airflow along the aircraft structure to increase lift and reduce drag, And thus reducing fuel consumption. However, the micro...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C9/22B64C21/02
CPCB64C9/22B64C21/02B64C1/12B64C2230/22B64C3/26Y02T50/10B64C21/04B64C21/06B64F5/40B64C2001/0072
Inventor 多特·丹德尔斯伯恩哈德·施利普夫克里斯蒂安·哈克
Owner AIRBUS OPERATIONS GMBH