초록 ▼

Currently, piping tapes are used as elastic masking elements of joints between lateral panels in an aircraft. According to one embodiment, a gap covering for cabin panels in an aircraft is provided, where the gap covering comprises a flexible cover region that is arranged between the cabin panels an

Currently, piping tapes are used as elastic masking elements of joints between lateral panels in an aircraft. According to one embodiment, a gap covering for cabin panels in an aircraft is provided, where the gap covering comprises a flexible cover region that is arranged between the cabin panels and finishes off so as to be substantially flush with surfaces of the panels. In this way, a lightweight economical gap covering which covers gaps in an effective and attractive manner and provides protection against injury is provided.

대표청구항 ▼

What is claimed is: 1. A gap covering for filling a gap having a varying gap width along the length of the gap, the gap being defined by the space between a first panelling element and a second panelling element in an aircraft, the gap covering comprising: a cover region comprised of a front surfac

What is claimed is: 1. A gap covering for filling a gap having a varying gap width along the length of the gap, the gap being defined by the space between a first panelling element and a second panelling element in an aircraft, the gap covering comprising: a cover region comprised of a front surface varying in width and forming a substantially flush continuation to front surfaces of the first panelling element and the second panelling element for covering the varying gap width of the gap between the first panelling element and the second panelling element; a first fastening region extending from a first side portion of the cover region and being adapted for fastening the cover region to the first panelling element and the first fastening region comprises a first profile that is designed to lock into a first counter profile of the first panelling element; and a second fastening region extending from a second side portion of the cover region and being adapted for fastening the cover region to the second panelling element and the second fastening region comprises a second profile that is designed to lock into a second counter profile of the second panelling element; wherein the cover region is affixed between the first panelling element and the second panelling element, and the cover region arcuately bends when subjected to movement of the first panelling element relative to the second panelling element, such that the front surface of the cover region substantially fills the gap compensatingly filling the varying gap width of the gap between the first panelling element and the second panelling element. 2. The gap covering of claim 1, wherein the first fastening region and the second fastening region are designed to attach the cover region to the first panelling element and the second panelling element by clipping in. 3. The gap covering of claim 1, wherein the cover region comprises an elastic material. 4. The gap covering of claim 1, wherein the cover region comprises a rear of the gap covering that comprises insulation material. 5. The gap covering of claim 1, wherein the first fastening region and the second fastening region each include a stiffening device. 6. The gap covering of claim 1, further comprising fastening regions, wherein the cover region comprises a foil, and the first fastening region, and the second fastening region each comprise a groove to protect an edge of the foil. 7. The gap covering of claim 1, wherein the first fastening region and the second fastening region each comprises a profile having an inclined surface for fastening the first fastening region and the second fastening region each to slide on the first panelling element and the second panelling element, respectively. 8. A method for installing three or more panelling elements in an aircraft with the gap covering of claim 1, comprising the steps of: aligning and affixing a first panelling element; hanging a second panelling element and a third panelling element into a supporting structure of the aircraft; attaching a first gap covering according to claim 1 between the first panelling element and the second panelling element by locking the first profile and the second profile of the first gap covering into the first counter profile of the first panelling element and the second counter profile of the second panelling element, respectively; attaching a second gap covering according to claim 1 between the second panelling element and the third panelling element by locking a third profile and a fourth profile of the second gap covering into a third counter profile of the second panelling element and a fourth counter profile of the third panelling element, respectively; aligning the third panelling element, such that the second panelling element automatically aligns due to a first spring force between the first panelling element, aligned and fixed in the step of aligning and affixing, and the second panelling element, and a second spring force between the second panelling element and the third panelling element, aligned during the step of aligning the third panelling element. 9. An aircraft using the gap covering of claim 1. 10. An aircraft comprising a gap covering of claim 1.