| 摘要 |
The invention relates to a fastening arrangement (4, 72, 76, 84) for fastening components on a fuselage of an aircraft, comprising at least one base element (6), at least one mounting rail (8, 74, 78) and connecting elements (10), wherein the base element (6) is adapted for being disposed on the fuselage of the aircraft, wherein the mounting rail (8, 74, 78) is adapted for fastening the components, and wherein the base element (6) and the mounting rail (8, 74, 78) are connected in a mutually spaced manner by means of the connecting elements (10). Thus, conducting different thermal expansions of the components to be fastened, or mechanical loads, primarily to a separate element in the form of the mounting rail (8, 74, 78) is enabled, such that said loads can be extensively mechanically uncoupled from the primary structure. At the same time, by providing a mounting rail (8, 74, 78), a fully variable possibility exists, independent of the position of reinforcement elements, to fasten components inside the vehicle cabin. |
