| 摘要 |
The present invention relates to a leading edge ( 1 ) for aircraft made of composite material, characterized in that it comprises on its inner face a metallic-type reinforcement ( 2 ) firmly adhered to the mentioned inner face of the leading edge ( 1 ) arranged such that it confers the leading edge ( 1 ) with better capacity to adapt to deformability and greater absorption of energy due to impacts. The invention also relates to a method of manufacturing a leading edge ( 1 ) with a metallic reinforcement ( 2 ) for aircraft made of composite material.
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