| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide a structure and a method for joining a composite fuselage section and other panel assemblies together. <P>SOLUTION: A shell structure includes a first panel portion 210a positioned adjacent to a second panel portion 210b. The first panel portion includes a first stiffener 214 attached to a first composite covering member 112a, and the second panel portion includes a second stiffener 214 attached to a second composite covering member 112b. The shell structure further includes a fitting 220 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 may be attached to the first stiffener and the first composite covering member, and a second end portion of the fitting may be attached to a second stiffener and a second composite covering member, to join the first panel portion to the second panel portion. <P>COPYRIGHT: (C)2012,JPO&INPIT |
