| 摘要 |
The invention relates to an aerofoil connection 12, 15 on a fuselage airframe 1, 14 of an aircraft, in particular a high-wing aircraft, comprising a plurality of double-jointed coupling members 8-11, 16-21. According to the invention, in each case at least two z-coupling members 8, 11, 16, 17 extending substantially parallel to a vertical axis of the aircraft and in each case at least two xz-coupling members 9, 10, 20, 21 are arranged in the region of two longitudinal edges 4, 5 of a fuselage airframe recess 3, wherein the xz-coupling members 9, 10, 20, 21 are configured in each case for a first maximum of a load in the event of a crash and of a load in normal flight operation parallel to a longitudinal axis (x) of the aircraft, and for a second maximum of a load in the event of a crash and of a load in normal flight operation parallel to the vertical axis (z). The xz-coupling members are capable of absorbing force components parallel to the x-axis, i.e. parallel to the longitudinal axis of the aircraft, as well as force components which arise parallel to the z-axis, so that separate z-coupling members are not required for force components in the z-direction and weight is reduced. Furthermore, in an alternative embodiment, predefined weakened zones 59 are provided in the straps 51, 52, 53 of the front xz-coupling members 9, 10, 20, 21, 40 which, in the event of a crash, allow force to be transferred via the xz-fuselage airframe bearing 26, 41 and the xz-aerofoil bearing by positive locking, at least in regions, between the two xz-bearings 26, 27, 41, 42. In this case, it is possible to achieve a further weight reduction as a result of a lighter configuration of the xz-bearings 26, 27, 41, 42 and of the bolts.
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