CPC B64C 1/061 (2013.01) [B29D 99/0014 (2013.01); B64F 5/10 (2017.01); B64C 2001/0072 (2013.01)] | 17 Claims |
1. An internal structural reinforcement element for fuselages, where the internal structural reinforcement element has a longitudinal direction adapted for its location in the longitudinal direction of the fuselage and a transverse direction perpendicular to its longitudinal direction, comprising:
an external reinforcement element,
an internal reinforcement element, located internally to the external reinforcement element in the transverse direction of the structural element,
where both reinforcement elements are manufactured from resin-impregnated fibre, and
an intermediate element, located between the external reinforcement element and the internal reinforcement element in the transverse direction of the structural element, the intermediate element being manufactured from pre-impregnated composite material, and the intermediate element comprising an H-shaped cross-section with flanges in the transverse direction of the structural element, in such a way that in the longitudinal direction of the structural element, the external and internal reinforcement elements are located between the flanges of the intermediate element.
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