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

A leading edge section with hybrid laminar flow control for an aircraft, the leading edge section comprising an outer surface, an inner surface, and obtained by injecting a compound comprising thermoplastic and short-fiber in a closed injection moulding tool, and said injection moulding tool comprising:

• an inner mandrel shaped with an inner surface of an aerodynamic leading edge profile and having first and second ends;
• an outer hood shaped with an outer surface of an aerodynamic leading edge profile;
• a plurality of elongated modules having a first and second extremes;
• and
• first and second C-shaped profiles comprising a plurality of passing-through cavities configured to receive the modules;
• wherein the first profile is placed on the first end of the inner mandrel, and the second profile is placed on the second end of the inner mandrel;
• wherein the first extreme of each elongated module is arranged in one cavity of the first profile, and the second extreme of the module in another cavity of the second profile, both cavities positioned in a same radial direction;
• wherein a lower gap is formed between both first and second profiles and the inner mandrel, said lower gap defining the thickness of the inner surface of the leading edge section;
• and
• wherein the outer hood is placed on the first and second profiles forming an upper gap between said first and second profiles and the outer hood, said upper gap defining the thickness of the outer surface of the leading edge section.

An injection moulding tool for manufacturing a leading edge section with hybrid laminar flow control for an aircraft, comprising:

• an inner mandrel having a first and second ends, and being shaped with an inner surface of an aerodynamic leading edge profile;
• an outer hood shaped with an outer surface of an aerodynamic leading edge profile;
• a plurality of elongated modules having a first and second extremes;
• and
• first and second C-shaped profiles comprising a plurality of passing-through cavities configured to receive the modules;
• wherein the first profile is placed on the first end of the inner mandrel, and the second profile on the second end of the inner mandrel;
• wherein the first extreme of each elongated module is arranged in one cavity of the first profile, and the second extreme of the module in another cavity of the second profile, wherein both cavities are positioned in the same radial direction, and wherein a lower gap between both the first and second profiles and the inner mandrel is formed, said lower gap defining the thickness of the inner surface of the leading edge section;
• and
• wherein the outer hood is placed on the first and second profiles forming an upper gap between both first and second profiles and the outer hood, said upper gap defining the thickness of the outer surface of the leading edge section.