초록 ▼

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 invention includes a first panel portion positioned adjacent to a second panel portion. The first pa

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 invention 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 further 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.

대표청구항 ▼

We claim: 1. A shell structure comprising: a first panel portion, the first panel portion including: a first skin; and a first stiffener attached to the first skin, wherein the first stiffener includes a first flange portion attached to the first skin and a first raised portion projecting away from

We claim: 1. A shell structure comprising: a first panel portion, the first panel portion including: a first skin; and a first stiffener attached to the first skin, wherein the first stiffener includes a first flange portion attached to the first skin and a first raised portion projecting away from the first skin; a second panel portion positioned adjacent to the first panel portion, the second panel portion including: a second skin; and a second stiffener attached to the second skin, wherein the second stiffener includes a second flange portion attached to the second skin and a second raised portion projecting away from the second skin; and a fitting extending across a first edge region of the first panel portion and a second edge region of the second panel portion, wherein a first end portion of the fitting overlies and is attached to the first flange portion of the first stiffener and the first skin, and wherein a second end portion of the fitting overlies and is attached to the second flange portion of the second stiffener and the second skin to join the first panel portion to the second panel portion. 2. The shell structure of claim 1 wherein the first stiffener is longitudinally aligned with the second stiffener. 3. The shell structure of claim 1 wherein the first skin is positioned in edgewise alignment with the second skin. 4. The shell structure of claim 1, further comprising a strap attached to a first edge region of the first skin and a second edge region of the second skin to splice the first skin to the second skin. 5. The shell structure of claim 1, further comprising a strap attached to a first edge region of the first skin and a second edge region of the second skin to splice the first skin to the second skin, wherein at least a portion of the strap is sandwiched between the fitting and the first edge region of the first skin and the second edge region of the second skin. 6. The shell structure of claim 1 wherein the first skin is a first composite skin of an aircraft fuselage, and wherein the second skin is a second composite skin of the aircraft fuselage. 7. A shell structure comprising: a first panel portion, the first panel portion including: a first skin having a first edge cut-out portion; and a first stiffener attached to the first skin; a second panel portion, the second panel portion including: a second skin having a second edge cut-out portion, wherein the second panel portion is positioned adjacent to the first panel portion so that the first edge cut-out portion is aligned with the second edge cut-out portion; and a second stiffener attached to the second skin; and a fitting extending across a first edge region of the first panel portion and a second edge region of the second panel portion, wherein a first end portion of the fitting is attached to the first stiffener and the first skin and a second end portion of the fitting is attached to the second stiffener and the second skin to join the first panel portion to the second panel portion. 8. The shell structure of claim 7, further comprising a strap attached to a first edge region of the first skin and a second edge region of the second skin to splice the first skin to the second skin, wherein the strap includes an aperture aligned with the first edge portion cut-out and the second edge portion cut-out. 9. The shell structure of claim 7, further comprising a strap attached to a first edge region of the first skin and a second edge region of the second skin to splice the first skin to the second skin, wherein the strap includes an aperture aligned with the first edge portion cut-out and the second edge portion cut-out, and wherein at least a portion of the strap is sandwiched between the filling and the first edge region of the first skin and the second edge region of the second skin. 10. The shell structure of claim 7 wherein the first skin is a first composite skin of an aircraft fuselage, wherein the second skin is a second composite skin of the aircraft fuselage, and wherein the first and second edge cut-out portions form a window cutout in the aircraft fuselage.