Dry fiber construction of a blended wing body aircraft and method of manufacture

A method of manufacture of a blended wing body aircraft, the method comprising:

• producing a first composite part comprising:
• forming a first dry carbon fiber sheet having a first width comprising:
• placing a first layer comprising a first plurality of dry carbon fibers in a first orientation, wherein the first plurality of dry carbon fibers comprises multiple layers laid onto one another to form the first layer with a first overall thickness, wherein the first orientation comprises a bidirectional layup orientation;
• and
• placing a second layer comprising a second plurality of dry carbon fibers comprising a differing material than the first layer positioned in a second orientation offset from the first orientation, wherein the second layer is disposed on top of the first layer in the second orientation and has a second overall thickness differing from the first overall thickness, wherein the second orientation comprises a unidirectional layup orientation, wherein:
• the first dry carbon fiber sheet includes a first portion of the aircraft;
• binding the first dry carbon fiber sheet together with at least one stitching, wherein the at least one stitching extends through the first dry carbon fiber sheet and wherein the first plurality of dry carbon fibers and the second plurality of dry carbon fibers are in direct contact with each other;
• stitching a second dry carbon fiber sheet stitched to the first dry carbon fiber sheet, wherein the second dry carbon fiber sheet comprises a second portion of the aircraft;
• wherein the second dry carbon fiber sheet comprises a second width;
• and
• molding, using a resin, the first dry carbon fiber sheet and the second dry carbon fiber sheet, wherein the at least one stitching, the first dry carbon fiber sheet and the second dry carbon fiber sheet are embedded within the resin to create a single unified structure;
• wherein the first composite part has a third width;
• and the third width comprises a sum of the first width and the second width;
• and
• receiving a blended wing body, wherein the blended wing body has no clear demarcation along a leading edge of the blended wing body aircraft from a wing to a nose of the blended wing body, and wherein the first composite part comprises a portion of the blended wing body.