Abstract: A circumferential skin joint according to the present disclosure may comprise a first composite fuselage member having a first composite skin comprising a first chamfer at least partially defining a first distal end of the first composite fuselage member, the first chamfer defining a first tapered mating surface extending circumferentially around an outer surface of the first composite fuselage member. In some examples, the circumferential skin joint further comprises a second composite fuselage member having a second composite skin, the second composite skin comprising a second chamfer at least partially defining a second distal end of the second composite fuselage member and defining a second tapered mating surface extending circumferentially around an inner surface of the second composite fuselage member. The first tapered mating surface contacts the second tapered mating surface to form a tapered lap joint between the first composite fuselage member and the second composite fuselage member.

Abstract: An aircraft fuselage body is constructed of an upper body section having a curved cross-section configuration and a lower body section having a curved cross-section configuration. The upper body section and the lower body section are joined together to form an aircraft fuselage body by splice straps that are secured, end to end along interior surfaces of the upper body section and the lower body section. The aircraft fuselage body being constructed of an upper body section and a lower body section enables installation of systems separately into the upper body section and the lower body section prior to the upper body section and lower body section being joined together.

Abstract: An aircraft fuselage body is constructed of an upper body section having a curved cross-section configuration and a lower body section having a curved cross-section configuration. The upper body section and the lower body section are joined together to form an aircraft fuselage body by splice straps that are secured, end to end along interior surfaces of the upper body section and the lower body section. The aircraft fuselage body being constructed of an upper body section and a lower body section enables installation of systems separately into the upper body section and the lower body section prior to the upper body section and lower body section being joined together.

Abstract: A method for manufacturing a composite structure. The method includes trimming plies of composite material to a near net-shape, thereby yielding a plurality of net-trimmed plies, wherein each net-trimmed ply of the plurality of net-trimmed plies includes an edge. The method further includes assembling a layup that includes the plurality of net-trimmed plies, wherein the assembling of the layup includes staggering the edges of the plurality of net-trimmed plies such that the edges define a staggered edge structure. The method further includes pressing the layup to form the staggered edge structure into a bevel.