| 摘要 |
A joint 22 between a sandwich skin panel 20 and an elongate structural frame element 16 of an aircraft is formed using a woven fabric connector strap of substantially H shaped cross-section formed by intersecting woven fabric webs 38,40,42 in which each of the webs comprises a plurality of multifilament yarn strands F extending side-by-side transversely to the longitudinal direction of the strap and passing directly through the intersecting web or webs, the crossing web 38 having portions 44F and 44R projecting transversely from opposite sides of the two spaced upright webs 40,42 of the connector H. A groove 56 is cut through the inner face-sheet 32 and core 36 of the skin panel 20 leaving the outer face-sheet 34 intact, and the connector H is fitted into the groove with the lower portions 40L,42L of the spaced webs overlying and adhesively bonded to the exposed edges of the core 36 along the side walls of the groove, and the transversely projecting portions 44F,44R of the crossing web 38 overlying and adhesively bonded to the inner face-sheet 32 on opposite sides of the groove whereby the yarn strands F of the crossing web 38 bridge the groove 56 and restore the continuity of the inner face-sheet. A foam insert 54 fills the void in the groove 56 between the web portions 40L,42L bonded therein. The frame element 16 is received between the upper portions 40U,42U of the upright connector webs on the other side of the crossing web 38 from the groove, and these upper web portions 40U,42U are adhesively bonded to the opposite faces 26,28 of the frame element thereby completing a double shear bond between the frame element and the skin panel. |
