Splice joints for composite aircraft fuselages and other structures

摘要

Structures and methods for joining composite fuselage sections and other panel assemblies together are disclosed herein. In one embodiment, a shell structure configured in accordance with the present disclosure includes a first panel portion positioned adjacent to a second panel portion. The first panel portion can include a first stiffener attached to a first composite skin, and the second panel portion can include a second stiffener attached to a second composite skin. The shell structure can include a fitting extending across a first edge region of the first panel portion and a second edge region of the second panel portion. A first end portion of the fitting can be attached to the first stiffener and the first composite skin, and a second end portion of the fitting can be attached to a second stiffener and a second composite skin, to join the first panel portion to the second panel portion.

主权项

1. A method for manufacturing a shell structure, the method comprising:
attaching at least a first stiffener to a first skin having a first edge cut-out portion; attaching at least a second stiffener to a second skin having a second edge cut-out portion; positioning the first skin in edgewise alignment with the second skin whereby the first edge cut-out portion is at least approximately aligned with the second edge cut-out portion; and attaching a first end of a fitting to the first stiffener and the first skin and a second end of the fitting to the second stiffener and the second skin attaching a strap to a first edge region of the first skin and a second edge region of the second skin to splice the first and second skins together, wherein the strap includes an aperture at least approximately aligned with the first and second edge cut-out portions of the first and second skins.