US 11,745,445 B2
Method of designing anisotropic composite laminate structure
Kensuke Yoshimura, Tokyo (JP)
Assigned to SUBARU CORPORATION, Tokyo (JP)
Filed by SUBARU CORPORATION, Tokyo (JP)
Filed on Mar. 15, 2022, as Appl. No. 17/695,669.
Claims priority of application No. 2021-053288 (JP), filed on Mar. 26, 2021.
Prior Publication US 2022/0305744 A1, Sep. 29, 2022
Int. Cl. B32B 41/00 (2006.01); B29C 70/54 (2006.01); B32B 5/12 (2006.01); B29C 70/30 (2006.01); B29L 31/30 (2006.01)
CPC B29C 70/54 (2013.01) [B29C 70/30 (2013.01); B32B 5/12 (2013.01); B29L 2031/3076 (2013.01); B32B 2605/18 (2013.01)] 21 Claims
OG exemplary drawing
 
1. A method of designing an anisotropic composite laminate structure to constitute a predetermined member of an airframe structure of an aircraft, the anisotropic composite laminate structure including a plurality of types of composite layers, each of the plurality of types of composite layers containing reinforcing fibers with different fiber orientations and defined by a unidirectional fiber orientation of the different fiber orientation, the method comprising:
dividing the anisotropic composite laminate structure in the predetermined member into a plurality of regions in a thickness direction where the composite layers are stacked, with each region comprising a plurality of region specific associated composite layers; and
determining, for each of the regions, at least a stacking sequence of the plurality of types of composite layers in accordance with a direction of stress acting on the predetermined member, and such that, over an entirety of the thickness direction, each pair of adjacent regions has a different stacking sequence in the region specific associated composite layers.