초록 ▼

This invention relates to improvements in the method by which elongate frame elements such as the spars in aircraft wings are fastened to the skin panels covering same where these skin panels are of the sandwich type having inner and outer facesheets with a core bonded therebetween, such method cons

This invention relates to improvements in the method by which elongate frame elements such as the spars in aircraft wings are fastened to the skin panels covering same where these skin panels are of the sandwich type having inner and outer facesheets with a core bonded therebetween, such method consisting of preparing the panel to receive its frame elements by cutting elongate grooves spanwise through the inner facesheet and the core therebeneath while leaving the outer facesheet intact; bridging the gap thus produced in the inner facesheet with one bundle of filaments adhesively bonded thereto, the latter being contained in a woven connector in the form of a strap or band running lengthwise of the groove, and this filament bundle forming an endless strand of yarn that is laid back and forth transversely across the gap in side-by-side parallel rows but which are parted at intervals for the side-by-side lays of at least one other similar yarn strand to pass therebetween in intersecting relation; adhesively-bonding the skin panel core exposed within the groove to one or both sides of the frame element located proximal thereto using two endless strands of yarn laid back and forth to define a pair of intersecting webs arranged in spaced substantially parallel relation to one another that form a part of the connector and pass through the spaces between the first-mentioned yarn strands.

대표청구항 ▼

The improved method for joining aircraft sandwich skin panels of the type including a core bounded both inside and outside by inner and outer facesheets to a longitudinally-extending frame element which comprises: cutting a longitudinally-extending groove through the inner facesheet and core exposin

The improved method for joining aircraft sandwich skin panels of the type including a core bounded both inside and outside by inner and outer facesheets to a longitudinally-extending frame element which comprises: cutting a longitudinally-extending groove through the inner facesheet and core exposing the edges thereof while leaving the outer facesheet intact; interweaving a first fill set of multiple fiber strands of yarn arranged in transversely-extending side-by-side relation to form a crossbar portion with a second fill set thereof intersecting said first fill set to define an upright portion, said intersecting crossbar and upright portions cooperating to produce a band thereof having a generally cruciform-shaped cross section with four quadrants; interweaving a third warp set of longitudinally-extending multiple fiber yarn strands with the first and second fill set thereof; treating the strands thus interwoven to rigidify same; bonding a structural insert sized for insertion into the skin panel groove to the strands defining one of the quadrants; bridging the gap in the inner facesheet created by the groove with the crossbar portion defined by the first fill set of multiple fiber strands and adhesively-bonding the latter to said facesheet to reestablish its continuity; inserting the structural insert into the groove and adhesively bonding the upright potion defined by the second fill set of strands alongside thereof to the adjacent exposed edge of the core to restore the resistance to bending of the associated skin panel; establishing a continuous load path between said inner and outer facesheets and same frame element by adhesively-bonding the latter to that part of the upright portion comprising those strands of the second fill set thereof lying outside said groove; and adhesively-bonding said third warp set of yarn strands to the surfaces of the inner facesheet and core adjacent the latter so as to resist the axial tensile and compressive forces to which the skin panels are subjected as the assembly bends. A joint between a sandwich skin panel of an aircraft component and an elongate structural frame element wherein the skin panel comprises a core bounded on opposite faces by inner and outer facesheets, said joint comprising: a groove cut through the inner facesheet intact, a woven fabric connector strap extending longitudinally along the groove and formed by a pair of substantially parallel spaced woven fabric webs intersected by a further woven fabric web to provide the strap with a substantially H-shaped cross-section in which the further web forms the cross-bar of the H-section and has portions projecting transversely from opposite sides of the two spaced webs, each of the webs comprising a plurality of multifilament yarn strands extending side-by-side transversely to the longitudinal direction of the strap and passing directly through the intersecting web or webs, the portions of the two spaced webs of the connector strap on one side of the crossing web being received in the groove and adhesively bonded to the exposed edges of the core along the side walls of the groove, and the transversely projecting portions of the crossing web overlying and being adhesively bonded to the inner facesheet on opposite sides of the groove whereby the crossing web bridges the groove and restores the continuity of the inner facesheet, a structural insert filling the void in the groove between the portions of the webs within the groove, and the frame element having a longitudinally extending edge received between the portions of the two spaced webs on the other side of the crossing web from the groove, said web portions overlying and being adhesively bonded to the opposite faces of the frame element whereby the two spaced webs form continuous load paths between the frame element and the inner and outer facesheets.