Method of laying up composite aircraft component comprising opening

Comprising an opening, the method comprising the step of laying up composite tows (5) oriented at 0 DEG, 90 DEG or +/-45 DEG, the composite tows forming plies, which in turn form a composite laminate, in which at least each tow (5) oriented at 0 DEG and within a perimeter (10) of the opening comprises: a first gap (4) in which at least one of the tows (5) is spaced apart from the first gap (4), and a second gap (5) in which at least one of the tows (5) is spaced apart from the first gap (4); the first gap (4) is located at about 3/5 of the length of the first semi-major axis (9) from the center (3), the first gap (4) is configured to be a first elongated gap longitudinally perpendicular to the orientation of the tow (5), and the second gap (7) is located at about 3/5 of the length of the second semi-major axis (9) from the center (3), the second gap (7) is configured to be a second elongated gap longitudinally perpendicular to the orientation of the tow (5). 包括开口的复合飞行器部件的铺叠方法，该方法包括铺叠取向为0°、90°或+/-45°的复合丝束(5)的步