A leading edge for an aircraft designed for active laminar flow control comprising a removable microperforated skin (10) for boundary layer suction, such microperforated skin comprising stiffeners (20) on its inner face that also act as spacers when the skin is installed on the supporting structure of the leading edge to form suction chambers, characterized in that the microperforated skin with its associated stiffeners is joined to the supporting structure (1) by means of non-permanent fasteners (30) attaching the stiffeners to the supporting structure and not visible on the outer surface of the skin, and the leading edge includes access to its interior through its lower surface that allows the installation of the non-permanent fasteners joining the skin to the leading edge structure.The invention also includes the process and the tool for an efficient and easy installation of the microperforated skin on the leading edge structure.
LEADING EDGE FOR LAMINAR FLOW WITH A REMOVABLE MICROPERFORATED SKIN
VORDERKANTE FÜR LAMINARSTRÖMUNG MIT ENTFERNBARER MIKROPERFORIERTER HAUT
BORD D'ATTAQUE POUR FLUX LAMINAIRE AVEC UNE PEAU MICROPERFORÉE AMOVIBLE
17.07.2024
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge / B25B TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING, OR HOLDING , Werkzeuge oder Werkbankvorrichtungen zum Befestigen, Verbinden, Lösen oder Halten, soweit nicht anderweitig vorgesehen / B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen |
Investigation of a Laminar Flow Leading Edge
British Library Conference Proceedings | 1994
|Investigation of a Laminar Flow Leading Edge
NTRS | 1994
|Wing leading edge architecture suitable for laminar flow
Europäisches Patentamt | 2018
|