| 摘要 |
Fuselage skin lap splice for aircraft formed of metal or composite skin panels. The adjacent skin panels comprise an outer skin and an inner skin, having contacting overlapping longitudinal edge portions, and a plurality of fasteners connecting such overlapping edge portions. A plurality of outwardly extending fingers are integrally connected along the edge portion of the inner skin and at least one longitudinal row of fasteners passes through the fingers and connects the outer skin and the fingers. Preferably the fingers are lollipopped, that is, have one or more protrusions thereon. The fingers at the end of the inner skin are flexible and soften and the load transfer through the fasteners, reducing the peak bearing stress and increasing the fatigue life of the splice. Alternatively, the desired flexibility at the end of the inner skin can be achieved by providing a plurality of large holes near the edge of the inner skin rather than by the provision of the fingers having apertures therebetween. |
