US 12,275,537 B2
Structural part for lightning strike protection
Christian Karch, Taufkirchen (DE); Kay Dittrich, Taufkirchen (DE); Matthias Bleckmann, Taufkirchen (DE); and Thomas Schuster, Taufkirchen (DE)
Assigned to Airbus Defence and Space GmbH, Taufkirchen (DE)
Filed by Airbus Defence and Space GmbH, Taufkirchen (DE)
Filed on Oct. 6, 2022, as Appl. No. 17/961,063.
Claims priority of application No. 21208561 (EP), filed on Nov. 16, 2021.
Prior Publication US 2023/0150689 A1, May 18, 2023
Int. Cl. B64D 45/02 (2006.01); B32B 1/00 (2006.01); B32B 3/08 (2006.01); B32B 5/02 (2006.01); B32B 15/14 (2006.01); H02G 13/00 (2006.01); B32B 15/20 (2006.01)
CPC B64D 45/02 (2013.01) [B32B 1/00 (2013.01); B32B 3/08 (2013.01); B32B 5/02 (2013.01); B32B 15/14 (2013.01); H02G 13/80 (2013.01); B32B 15/20 (2013.01); B32B 2255/06 (2013.01); B32B 2255/205 (2013.01); B32B 2260/021 (2013.01); B32B 2260/046 (2013.01); B32B 2262/101 (2013.01); B32B 2262/106 (2013.01); B32B 2307/202 (2013.01); B32B 2307/212 (2013.01); B32B 2307/712 (2013.01); B32B 2605/18 (2013.01)] 13 Claims
OG exemplary drawing
 
1. An aircraft comprising a structural part for lightning strike protection of the aircraft,
wherein the structural part comprises:
a first structure element, wherein the first structure element comprises a conducting material and is adapted to conduct electric currents into a grounded conducting airframe structure,
a second structure element, wherein the second structure element comprises an outer layer with a first surface, wherein the outer layer comprises a composite; comprising carbon-fibre reinforced plastic, (CFRP) or glass-fibre reinforced plastic (GFRP),
a first elongated, electrical conductor, with a first end and a second end, wherein the first end of the first elongated electrical conductor is connected to the first structure element and extends through the second structure element to the first surface,
so that the second end of the first elongated electrical conductor serves as a lightning receptor without impairing the radar cross section of the aircraft,
wherein the first elongated electrical conductor is arranged in the second structure element in a first orientation, and
wherein the first orientation is adapted to be aligned parallel to the rolling axis of the aircraft.