This disclosure relates to the manufacturing of a leading edge section with hybrid laminar flow control for an aircraft. A manufacturing method involves: providing an outer hood, a plurality of elongated modules, first and second C-shaped profiles having comprising cavities, and an inner mandrel; assembling an injection moulding tool by placing each profile on each end of the inner mandrel, arranging a first extreme of each elongated module in one cavity of the first profile and a second extreme of the module in another cavity of the second profile, both cavities positioned in the same radial direction; and placing the hood on first and second profiles to close the tool. Further, the injection moulding tool is closed and filled with an injection compound comprising thermoplastic and short-fiber. Finally, the compound is hardened and demoulded.
METHOD, INJECTION MOULDING TOOL FOR MANUFACTURING A LEADING EDGE SECTION WITH HYBRID LAMINAR FLOW CONTROL FOR AN AIRCRAFT, AND LEADING EDGE SECTION WITH HYBRID LAMINAR FLOW CONTROL OBTAINED THEREOF
2017-09-14
Patent
Electronic Resource
English
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