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
2018-07-11
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
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