US 11,752,704 B2
Composite laminate for an airframe lifting surface and method for manufacturing thereof
Antonio Torres Esteban, Madrid (ES); Jose-Maria Blanco-Saiz, Madrid (ES); Manuel Recio Melero, Madrid (ES); and Pedro Nogueroles Viñes, Toled (ES)
Assigned to AIRBUS OPERATIONS S.L., Madrid (ES)
Filed by AIRBUS OPERATIONS S.L., Madrid (ES)
Filed on Oct. 20, 2020, as Appl. No. 17/75,211.
Claims priority of application No. 19382922 (EP), filed on Oct. 23, 2019.
Prior Publication US 2021/0122454 A1, Apr. 29, 2021
Int. Cl. B29C 70/20 (2006.01); B29C 65/48 (2006.01); B29C 65/00 (2006.01); B29C 70/30 (2006.01); B64C 1/00 (2006.01); B32B 5/12 (2006.01); B32B 5/26 (2006.01); B29L 31/30 (2006.01)
CPC B29C 70/202 (2013.01) [B29C 65/48 (2013.01); B29C 66/721 (2013.01); B29C 70/30 (2013.01); B32B 5/12 (2013.01); B32B 5/26 (2013.01); B64C 1/00 (2013.01); B29L 2031/3076 (2013.01); B64C 2001/0072 (2013.01)] 15 Claims
OG exemplary drawing
 
1. A method for manufacturing a composite laminate for an airframe lifting surface, the method comprising:
laying up pre-preg material to form a set of stacked plies, wherein the set of stacked plies has an edge following an edge direction, and wherein the laying up includes:
laying up a plurality of first plies one ply on another by arranging tapes of the pre-preg material parallel to the edge direction to form a first layer of a first plurality of the first plies, a second layer of a second plurality of the first plies, and a third layer of a third plurality of the first plies, and
laying up a plurality of second plies by arranging tapes of the pre-preg material in one or more directions which are non-parallel to the edge direction, wherein a thickness of each of the second plurality plies is smaller than a thicknesses of each of the first plies, and wherein one ply of the second plies is sandwiched between the first and second layers, and another one ply of the second plies is sandwiched between the second and third layers;
curing the set of stacked plies, and
forming the composite laminate for the airframe lifting surface from the cured composite laminate.