Lightning protection for vehicles
A vehicle ( 2 ) comprising a vehicle part ( 4 ), the vehicle part ( 4 ) comprising: an electrically conductive core ( 6 ); a non-electrically conductive outer skin ( 8 ) made of a radar-absorbent material which surrounds, at least to some extent, the core ( 6 ) such that the core ( 6 ) is not visible from outside the vehicle ( 2 ); and one or more electrically conductive members ( 10 ) electrically connected to the core ( 6 ); each of the one or more members ( 10 ) is a tapered member having a relatively large cross sectional area where that member ( 10 ) is electrically connected to the core ( 6 ), and tapers from its end that is connected to the core ( 6 ) to a point; and the point of each member ( 10 ) is located at an outer surface of the external skin ( 8 ) such that the point of each of the members ( 10 ) is exposed.
1. A vehicle ( 2 ) comprising a vehicle part ( 4 ), the vehicle part ( 4 ) comprising:
an electrically conductive core ( 6 );
a non-electrically conductive outer skin ( 8 ), the outer skin ( 8 ) being made of a radar-absorbent material, the outer skin ( 8 ) surrounding, at least to some extent, the core ( 6 ) such that the core ( 6 ) is not visible from outside the vehicle ( 2 ); and
one or more electrically conductive members ( 10 ); wherein
each of the one or more members ( 10 ) is electrically connected to a surface of the core ( 6 ) adjacent to the outer skin ( 8 );
each of the one or more members ( 10 ) is a tapered member having a larger cross sectional area where that member ( 10 ) is electrically connected to the surface of the core ( 6 ), than a cross sectional area of opposite end of the member ( 10 ), and tapers from its end that is electrically connected to the surface of the core ( 6 ) to a point; and
the point of each member ( 10 ) is located at an outer surface of the external skin ( 8 ) such that the point of each of the members ( 10 ) is exposed
wherein at least one of the members ( 10 ) comprises a braid of electrical conductors, thereby providing conductivity greater than a solid member due to a conductivity skin effect.
2. The vehicle ( 2 ) according to claim 1 , wherein the vehicle ( 2 ) is a low observable aircraft.
3. The vehicle ( 2 ) according to claim 2 , wherein the vehicle part ( 4 ) is an aircraft wing.
4. The vehicle ( 2 ) according to claim 3 , wherein the one or more members are positioned along a leading edge of the aircraft wing.
5. The vehicle ( 2 ) according to claim 1 , wherein, for a member ( 10 ), a point on the outer surface of the external skin ( 8 ) at which that member ( 10 ) is exposed is the point on the outer surface of the external skin ( 8 ) that is closest to the point on the core ( 6 ) at which that member ( 10 ) is electrically connected to the core ( 6 ).
6. The vehicle ( 2 ) according to claim 1 , wherein, for a member ( 10 ), that member ( 10 ) electrically connects a first point to a second point via the shortest route between those points, the first point being a point on the outer surface of the external skin ( 8 ) at which that member ( 10 ) is exposed, the second point being a point on the core ( 6 ) at which that member ( 10 ) is electrically connected to the core ( 6 ).
7. The vehicle ( 2 ) according to claim 1 , wherein the vehicle ( 2 ) comprises a plurality of members ( 10 ) and the members ( 10 ) are arranged at irregular intervals over the vehicle part ( 4 ).
8. The vehicle ( 2 ) according to claim 1 , wherein only the points of each of the members ( 10 ) are exposed.
9. A fleet comprising a plurality of vehicles ( 2 ), each vehicle ( 2 ) being a vehicle ( 2 ) in accordance with claim 1 , wherein a distribution pattern of electrically conductive members ( 10 ) within a vehicle ( 2 ) of the fleet is different to a distribution pattern of electrically conductive members within each other vehicle ( 2 ) of the fleet.
10. An aircraft panel ( 20 ) comprising:
an electrically conductive first layer ( 22 );
a non-electrically conductive second layer ( 24 , 26 ), the second layer ( 26 ) including a radar-absorbent material, the second layer ( 24 , 26 ) being disposed on the first layer ( 22 ); and
one or more electrically conductive members ( 10 ); wherein
each of the one or more members ( 10 ) is attached to a surface of the first layer ( 22 ) adjacent to the second layer ( 24 , 26 );
each of the one or more members ( 10 ) is a tapered member having a larger cross sectional area where that member ( 10 ) is attached to the surface of the first layer ( 22 ) than a cross sectional area of opposite end of the member ( 10 ), and wherein the member tapers from its end that is electrically connected to the surface of the first layer ( 22 ) to a point; and
the point of each member ( 10 ) is located at a surface of the second layer ( 24 , 26 ) that is not in contact with the first layer ( 22 ) such that the point of each of the members ( 10 ) is exposed;
wherein edges of the first layer ( 22 ), in regions of the first layer ( 22 ) proximate to a periphery of the panel ( 20 ), are thicker than other regions of the first layer ( 22 ).
11. The method according to claim 9 , wherein the vehicle ( 2 ) is a low observable aircraft.
12. The method according to claim 10 , wherein the vehicle part ( 4 ) is an aircraft wing.
13. The method according to claim 12 , wherein the step of arranging the members comprises positioning the members ( 10 ) along a leading edge of the aircraft wing.
14. A method of producing an aircraft panel ( 20 ), the method comprising:
providing an electrically conductive first layer ( 22 );
disposing, onto the first layer ( 22 ), a non-electrically conductive second layer ( 24 , 26 ), the second layer ( 24 , 26 ) being made of a radar-absorbent material;
providing one or more electrically conductive members ( 10 ), each member ( 10 ) being a tapered member having a first end having a larger cross sectional area than a cross sectional area of a second end, and the second end that is a point; and
arranging the members such that:
each of the one or more members ( 10 ) is electrically connected to the surface of the first layer ( 22 ) at its first end; and
the point of each member ( 10 ) is located at a surface of the second layer ( 24 , 26 ) that is not in contact with the first layer ( 22 ) such that the point of each of the members ( 10 ) is exposed;
wherein edges of the first layer ( 22 ), in regions of the first layer ( 22 ) proximate to a periphery of the panel ( 20 ), are thicker than other regions of the first layer ( 22 ).
15. The method of claim 14 , wherein at least one of the members ( 10 ) is a pin, each pin having a cylindrical body portion between the first end and the point of the second end, wherein the cylindrical body tapers near the second end to a sharp point at the second end.
16. The method of claim 14 , wherein the first layer ( 22 ) is a mesh layer bonded to the underside of the second layer ( 24 ).
17. The method of claim 14 , wherein the second layer ( 24 ) comprises a carbon fibre composite.