| 摘要 |
The invention relates to an energy-absorbing connection arrangement for joining at least two components, in particular a transverse member and a circular frame element, of a fuselage structure of an aircraft, with a multitude of connectors, which in particular are arranged in a matrix-like manner, wherein each connector comprises a head with a shaft, and the shafts reach through associated boreholes in the component, and on the shaft ends facing away from the heads in each case counter-bearings are provided, and a first component comprising a fibre-reinforced plastic material and at least one further component comprising a metallic material and/or comprising a fibre-reinforced plastic material are formed. According to the invention, a head and/or a counter bearing of at least one connector rest/rests against at least one underlay device, and the at least one underlay device is received in at least one guide groove provided at least in the first component, with the guide groove commencing in the region of the boreholes, wherein the at least one underlay device, as a result of exceeding a mechanical threshold load F threshold , is slidable in a direction facing away from the boreholes, and energy absorption essentially takes place along a longitudinal centre axis of the at least one guide groove, in particular as a result of hole-bearing-stress failure and/or the shearing of the at least one component formed with the fibre-reinforced plastic material. Furthermore, the invention relates to a structure. |
