Patent ID: 9371125
Filing Date: 2016-06-21
CPC Classification: B64C

Claim Text:
1. A fuselage element of a fuselage comprising: a fuselage section including a skin, the fuselage section extending along a central longitudinal axis of the fuselage; a stiffener frame; an adjacent section; and a junction member, the junction member including an inner surface and an outer surface, wherein the skin includes a first part at at least one end of the fuselage section, the first part of the skin including an inner surface and an outer surface, wherein the fuselage section includes at least one longitudinal stiffener element for the fuselage element, wherein the junction member connects the fuselage section to the adjacent section, the inner surface of the junction member being placed in contact with both the stiffener frame and the outer surface of the first part of the skin, wherein a part of the at least one longitudinal stiffener element extends to the junction member along the longitudinal axis such that said part of the at least one longitudinal stiffener element abuts the inner surface of the first part of the skin, and wherein the junction member contacting the outer surface of the first part of the skin overlaps with the part of the at least one longitudinal stiffener element extending to the junction member and abutting the inner surface of the first part of the skin.