LATERAL BUTT LAYOUT, AND ALSO A METHOD FOR CONNECTING TWO FIRST OF ALL FUSELED SECTION FROM CARBON FIBER REINFORCED MATERIAL ANALYZER FOR SULFUR

摘要

1. A transverse butt plate (1, 19, 37) for creating an aircraft fuselage cell by connecting several sections (5, 26, 27, 43) of the fuselage, which are primarily made by winding in the form of sections of carbon fiber reinforced composite material, with the formation of a transverse seam, respectively (14, 28, 48),! characterized in that! the transverse butt plate (1, 19, 37) has at least two segments (7-9, 20-23, 38-40) of the plate radially located one above the other, and in each of the segments (7-9, 20-23, 38-40) overlays, primarily for radial compensation of tolerances between sections (5, 26, 27, 43) of the fuselage, a lot of longitudinal slots (10, 11, 44, 45), and longitudinal slots (10, 11, 44, 45 ) in the segments (7-9, 20-23, 38-40), the pads in each case are located with a tangential displacement relative to each other. ! 2. The transverse butt plate (1, 19, 37) according to claim 1, characterized in that the thickness of the material of at least two segments (7-9, 20-23, 38-40) of the plate is preferably greater than the thickness of the material of each from the skins (4, 30, 31, 42) of the sections (5, 26, 27, 43) of the fuselage. ! 3. The transverse butt plate (1, 19, 37) according to claim 1, characterized in that the longitudinal slots (10, 11, 44, 45) are preferably evenly spaced apart from each other to form a plurality of partial plates (17, 18 , 50, 51). ! 4. The transverse butt plate (1, 19, 37) according to claim 1, characterized in that the segments (7-9, 20-23, 38-40) of the plate are formed from the same material as the skin (4, 30, 31, 42) of the fuselage sections (5, 26, 27, 43) to be connected, primarily from composite material or aluminum alloy. ! 5. The transverse butt plate (1, 19, 37) according to claim 1, characterized in that the transverse butt plate