Composite stringer beam joint structure of an aircraft

An aircraft wing assembly comprising:

• a central wing box including a lower skin and a number of stringers coupled to the lower skin of the central wing box, the stringers are all made from fiber-reinforced composites;
• a first wing and a second wing, where the first and second wings each includes a lower skin and a number of stringers coupled to the lower skin of each of the wings, the stringers of the first wing and the second wing all made from fiber-reinforced composites;
• and
• a number of splice chords for joining the first and second wings to opposite sides of the central wing box;
• wherein:
• each of the stringers has a first end and a second end, where the first and second ends extend in a spanwise direction, and each stringer comprises a cap flange, a base flange, and a web between the cap flange and the base flange;
• the cap flange, the base flange, and the web are elongate in each respective stringer's spanwise direction;
• the first end of at least one of the stringers from each of central wing box, the first wing, and the second wing comprises a web cutout with a taper, formed in the base flange along the respective stringer, the taper located at the first end of each respective stringer, where the taper runs from a knife edge distal end of the base flange to a proximal end that coincides with a full height of the base flange, the taper oriented at an angle between 10 and 15 degrees;
• the taper of the base flange is contiguous with an edge of the web cutout;
• the base flange comprises an overwrap layer on the taper of the base flange;
• the overwrap layer is made of sheet metal or plies of reinforcing fibers that are pre-impregnated with resin;
• and
• the overwrap layer is bonded to the taper of the base flange and configured to contrain an end of the base flange from peeling off a mated skin.