| 主权项 |
1. A method of assembling a fuselage, said method comprising:
providing a first barrel section including a body that extends from a first end to a second end, wherein a thickness of the first barrel section second end is greater than a thickness of the first barrel section body, and the first barrel section has an inner surface that at least partially defines a cavity and an outer surface opposite the inner surface; providing a second barrel section including a body that extends from a first end to a second end, wherein a thickness of the second barrel section second end is greater than a thickness of the second barrel section body, and the second barrel section has an inner surface that at least partially defines the cavity and an outer surface opposite the inner surface; coupling the first barrel section second end to the second barrel section second end at a joint; positioning a compression member adjacent to the joint within the cavity, wherein a cross-sectional shape of the compression member includes a surface configured to substantially conform to the first barrel section second end and the second barrel section second end; and securing the compression member circumferentially against the inner surface of at least one of the first barrel section and the second barrel section to induce a compressive force from the compression member to the at least one of the first barrel section and the second barrel section to maintain the coupling therebetween. |
