B - Operations – Transporting – 64 – C
Patent
B - Operations, Transporting
64
C
26/30, 244/98
B64C 3/18 (2006.01)
Patent
CA 1274075
METHOD FOR FASTENING AIRCRAFT FRAME ELEMENTS TO SANDWICH SKIN PANELS COVERING SAME USING WOVEN FIBER CONNECTORS ABSTRACT OF THE INVENTION 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 for a part of the connector and pass through the spaces between the first-mentioned yarn strands, the strand of yarn contained in the connector that bridges the gap in the skin panel formed by the groove therein functioning to restore the continuity to the inner facesheet interrupted thereby, the web-defining strands of yarn intersecting the aforementioned groove-bridging strand cooperating with one another to establish a redundant double-shear bond joint between the skin panels and frame elements; and still other strands of yarn contained in the connector interwoven among the strands of yarn of all of the previously-mentioned fill strands but extending longitudinally thereof in substantially parallel relation to one another and to the groove, the latter yarn strands forming the warp of the woven connector, and these warp strands being adhesively-bonded to the same surfaces as the fill strands interwoven therewith and functioning to resist the axially-directed spanwise tensile and compressive forces induced in the skin panels as the assembly is bent about a chordwise axis. - 2 -
516114
Beech Aircraft Corporation
Johnson Ernest Peter
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