Airbus Operations Sl

Airbus Operations Gmbh

Antonio Torres Esteban

Pedro Nogueroles Viñes

Manuel Recio Melero

Jose-Maria Blanco-Saiz

Yolanda Miguez Charines

Elena Arevalo Rodriguez

Ignacio Outon Hernández

Oscar Miguel Macías Jareño

Juan José Pastrana Bermejo

Jose Maria Blanco Sainz

Elena ARÉVALO RODRÍGUEZ

Juan Jose Pastrana Bermejo

A composite laminate () for an airframe lifting surface comprising a set of stacked plies () of pre-preg material, the composite laminate () being surrounded by at least an edge () following an edge direction E along the composite laminate (), the set of stacked plies () including: a first plurality () of plies () formed by tapes arranged parallel to the edge direction E, and a second plurality () of plies () 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 () of plies is lower than the thickness of each ply of the first plurality () of plies.

Composite laminate for an airframe lifting surface and method for manufacturing thereof

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.

A frame () for fuselage shells of an aircraft, the fuselage comprising a skin () and stringers (), the frame () including: a plurality of sections (), the sections () being separated by intermediate gaps corresponding to the position of the stringers () in the fuselage, each section () having a multi-cell configuration constituted by several modular elements () of composite material arranged in longitudinal direction, and a continuous inner cap () on top of the sections () and the intermediate gaps.

Frame for fuselage shells of an aircraft and fuselage shell

The present invention relates to a stringer, particularly to a stiffening and structural longitudinal element for skin of aircraft airfoil surfaces, characterized in that it incorporates two separate and independent reinforcement areas, one in the foot and the other at the end of the web (head) of the stringer, where the reinforcement areas are obtained by a widening of the section of the stringer, the widening being formed by a localized stack of reinforcing plies of composite material which are embedded within the stringer. The invention also relates to the method of manufacture and is particularly applicable to stringers having an L-shaped or T-shaped section.

Reinforced stringer and method of manufacture thereof

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Madrid, Spain

Antonio Torres Esteban