| 摘要 |
An aircraft fuselage assembly comprises first and second skin sections each further comprising a plurality of plies of composite materials and having a mating edge, with the mating edges disposed in edgewise alignment with each other, and a plurality of tabs each extending longitudinally from the mating edge of the first skin section along an interior surface of the second skin section. Each tab includes an exterior surface in facing registration with a corresponding portion of the interior surface of the second skin section. Each of the tabs further includes at least one injection hole formed therethrough for injection of bonding material between the exterior surface and the corresponding portion for attaching the first and second skin sections, wherein at least one of the corresponding portions includes a recessed area adapted to matingly receive the exterior surface of at least one of the plurality of tabs, wherein at least one of the plurality of tabs includes a protrusion extending substantially orthogonally from the exterior surface thereof, and wherein the protrusion interfits with the recessed area disposed on the interior surface of the second skin section in facing registration with the exterior surface. |
