Shielding arrangement for lines, in particular electrical lines, in aircraft
View Patent ↗A shielding arrangement for the lightning protection of electrical lines and components in an aircraft includes a protected installation space for receiving the lines that is arranged in the region of a floor framework, at least one delimiting surface of the installation space being provided at least in certain regions with an electrically conductive shielding, the at least one delimiting surface of the installation space being formed with at least one floor panel and a further delimiting surface of the installation space being formed with at least one ceiling panel.
1. An electromagnetic shielding arrangement for the lightning protection of electrical lines and components in an aircraft, the electromagnetic shielding arrangement comprising:
a protected installation space for receiving the lines, that is arranged in the region of a floor framework, and
at least one delimiting surface of the protected installation space being provided at least in regions with an electrically conductive shielding,
wherein the at least one delimiting surface of the protected installation space is formed with at least one floor panel and a further delimiting surface of the protected installation space is formed with at least one ceiling panel, and
wherein the floor panels and the ceiling panels are configured as sandwich panels, comprising electrical conductive shielding over their full surface area, and on both sides.
2. The shielding arrangement according to claim 1 , wherein the least one delimiting surface is formed in a planar manner, and curved at least in one direction of the space.
3. The shielding arrangement according to claim 1 , wherein the at least one delimiting surface encloses the installation space completely.
4. The shielding arrangement according to claim 1 , wherein the electrical conductivity of the shielding varies from region to region.
5. The shielding arrangement according to claim 1 , wherein electrically conductive shielding is insulated at least in certain regions.
6. The shielding arrangement according to claim 1 , wherein the electrically conductive shielding is connected to a central earthing system of the aircraft.
7. The shielding arrangement according to claim 1 , wherein the electrically conductive shielding serves as a return conductor for onboard electrical systems.
8. The shielding arrangement according to claim 1 , wherein the floor panels are fixed on transverse beams of the floor framework and the ceiling panels are fixed under the transverse beams by fastening elements.
9. The shielding arrangement according to claim 8 , wherein the fastening elements are electrically conductive fastening screws.
10. The shielding arrangement according to claim 1 , wherein the electrically conductive shielding is formed with a metal foil, metallic vapour deposition, metallization, a woven metal fabric, a nonwoven metal fabric, an electrically conductive plastics material, and any combination thereof.
11. The shielding arrangement according to claim 8 , wherein the transverse beams are formed with an electrically conductive material.
12. The shielding arrangement according to claim 11 , wherein the transverse beams are formed with at least one of an aluminum alloy material and a CRP material.
13. The shielding arrangement according to claim 1 , wherein seat rails formed with an electrically conductive material are arranged on the transverse beams.
14. The shielding arrangement according to claim 13 , wherein the seat rails are formed of at least one of an aluminum alloy material and a titanium alloy material.
15. The shielding arrangement according to claim 1 , wherein the electrically conductive shielding of the floor panels and the ceiling panels is debossed through, at least on one side, in the region of fastening bores, to create an electrically conductive connection between transverse beams, floor panels, ceiling panels and seat rails.