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

摘要

The invention refers to the manufacturing of a leading edge section (1) with hybrid laminar flow control for an aircraft comprising providing an outer hood (4), a plurality of elongated modules (2), first and second C-shaped profiles (5, 7) comprising cavities (10), and an inner mandrel (3); assembling an injection moulding tool by placing each profile (5, 7) on each end of the inner mandrel (3), arranging a first extreme of each elongated module (2) in one cavity (10) of the first profile (5) and a second extreme of the module (2) in another cavity (10) of the second profile (7), both cavities (10) positioned in the same radial direction; and placing the hood (4) on first and second profiles (5, 7) 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.