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 |
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.
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