Net edge composite core splices for aircraft wing

A method of assembling a core structure assembly, the method comprising:

• providing a first composite core structure having a first plurality of cells and a first cell size, and a second composite core structure having a second plurality of cells and a second cell size, the second cell size being greater than the first cell size, wherein the first plurality of cells and the second plurality of cells each have a hexagonal cross-sectional shape and a centerline, wherein the first and second composite core structures are formed from a plurality of interconnected ribbons of composite material, wherein the plurality of interconnected ribbons are arranged in a length direction and a width direction;
• arranging facets of some of the first plurality of cells in alignment with facets of some of the second plurality of cells to create facet interfaces that maximize surface contact between the first and second composite core structures, wherein an interconnected ribbon of composite material of the plurality of interconnected ribbons of composite material forms an end facet of the second plurality of cells and has a modified shape such that a plurality of cells of the second plurality of cells have additional end facets that maximize surface contact between the first and second composite core structures and do not have the hexagonal cross-sectional shape;
• and
• connecting the first and second composite core structures together at the facet interfaces.