The invention refers to a leading edge section (1) with laminar flow control, which comprises: a perforated outer skin (2), a perforated inner skin (3), and a plurality of suction chambers (4) formed between the outer skin and the inner skin. The leading edge section comprises a plurality of stringers (5) span-wise arranged at the leading edge section, and integrally formed with the outer skin, such as the inner skin is joined to the stringers. The invention also refers to a method for manufacturing a leading edge section integrating a laminar flow control system, wherein a perforated inner skin is joined with a perforated outer skin having a plurality of stringers (5) integrally formed with the outer skin, such as suction chambers (4) are defined by a part of the outer skin, a part of the inner skin and a pair of stringers.
A LEADING EDGE WITH LAMINAR FLOW CONTROL AND MANUFACTURING METHOD THEREOF
VORDERKANTE MIT LAMINARER STRÖMUNGSKONTROLLE UND HERSTELLUNGSVERFAHREN DAFÜR
BORD D'ATTAQUE AVEC CONTRÔLE D'ÉCOULEMENT LAMINAIRE ET SON PROCÉDÉ DE FABRICATION
11.07.2018
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
Leading edge with laminar flow control and manufacturing method thereof
Europäisches Patentamt | 2020
|LEADING EDGE WITH LAMINAR FLOW CONTROL AND MANUFACTURING METHOD THEREOF
Europäisches Patentamt | 2017
|LEADING EDGE WITH LAMINAR FLOW CONTROL AND MANUFACTURING METHOD THEREOF
Europäisches Patentamt | 2019
|