Abstract: A lay-up method of composite aircraft parts with an opening. Composite tows having an orientation of 0°, 90° or +/?45° are laid up forming plies which form a composite laminate. Each tow having an orientation of 0° and being within the perimeter of the opening comprises: a first gap located at approximately ? of the length of the first semi-major axis from the center, the first gap being configured as a first elongated gap longitudinally perpendicular to the orientation of the tow, and a second gap located at approximately ? of the length of the second semi-major axis from the center, the second gap being configured as a second elongated gap longitudinally perpendicular to the orientation of the tow.

Abstract: The invention provides an integrated aircraft structure, such as a fuselage, with reinforcing elements in areas of the structure that need them because they have openings or are subjected to high loads. The structure comprises a skin, a plurality of stringers and a plurality of frames with mouseholes for the passage of stringers at their crossing zones. The reinforcing elements are configured with a suitable shape to be superimposed to the stringers in said areas. A manufacturing processes of said integrated aircraft structure is also provided.

Abstract: The invention provides an integrated aircraft structure, such as a fuselage, with reinforcing elements in areas of the structure that need them because they have openings or are subjected to high loads. The structure comprises a skin, a plurality of stringers and a plurality of frames with mouseholes for the passage of stringers at their crossing zones. The reinforcing elements are configured with a suitable shape to be superimposed to the stringers in said areas.