Abstract: A method for manufacturing stringers for aircraft, wherein the stringer comprises two semi-stringers, includes steps of placing tows on a flat surface for forming the semi-stringers independently or at the same time, the placement being made by partially overlapping the tows and orientating the tows on the flat surface according to boundaries of the flat surface, the tows covering the boundaries of the flat surface; and cutting the tows so that a shape of the tows corresponds to the shape of the flat surface defined by boundaries of the flat surface.

Abstract: A composite laminate (2) for an airframe lifting surface comprising a set of stacked plies (10) of pre-preg material, the composite laminate (2) being surrounded by at least an edge (3) following an edge direction E along the composite laminate (2), the set of stacked plies (10) including: a first plurality (4) of plies (4.1) formed by tapes arranged parallel to the edge direction E, and a second plurality (5) of plies (5.1, 5.2, 5.3) formed by tapes arranged in a direction different to the edge direction E, wherein the thickness of at least one ply of the second plurality (5) of plies is lower than the thickness of each ply of the first plurality (4) of plies.

Abstract: A composite laminate for an airframe lifting surface including: at least two sides and one ramp area defined by a decreasing staggered laminate extended along a ramp direction, wherein the composite laminate includes: first plies formed by tapes arranged parallel to the ramp direction, second plies formed by tapes arranged orthogonal to the ramp direction, third plies formed by tapes arranged in a first laying up direction, being the first laying up direction different from the ramp direction and the direction orthogonal to the ramp direction, and fourth plies formed by tapes arranged in a second laying up direction, being the second laying up direction different from the ramp direction, the direction orthogonal to the ramp direction and the first laying up direction; wherein in the ramp area, the tapes forming the third and/or fourth plies are extended from one laminate side to another laminate side.

Abstract: A composite laminate for an airframe lifting surface including: at least two sides and one ramp area defined by a decreasing staggered laminate extended along a ramp direction, wherein the composite laminate includes: first plies formed by tapes arranged parallel to the ramp direction, second plies formed by tapes arranged orthogonal to the ramp direction, third plies formed by tapes arranged in a first laying up direction, being the first laying up direction different from the ramp direction and the direction orthogonal to the ramp direction, and fourth plies formed by tapes arranged in a second laying up direction, being the second laying up direction different from the ramp direction, the direction orthogonal to the ramp direction and the first laying up direction; wherein in the ramp area, the tapes forming the third and/or fourth plies are extended from one laminate side to another laminate side.

Abstract: A composite laminate (2) for an airframe lifting surface comprising a set of stacked plies (10) of pre-preg material, the composite laminate (2) being surrounded by at least an edge (3) following an edge direction E along the composite laminate (2), the set of stacked plies (10) including: a first plurality (4) of plies (4.1) formed by tapes arranged parallel to the edge direction E, and a second plurality (5) of plies (5.1, 5.2, 5.3) formed by tapes arranged in a direction different to the edge direction E, wherein the thickness of at least one ply of the second plurality (5) of plies is lower than the thickness of each ply of the first plurality (4) of plies.