A structure formed from composite material and method of forming a composite structure, in which several metal layers are disposed on a composite structural member. This structure is intended to be used as structural element (e.g. 113, figure 1) in wing or fuselage of an aircraft; the metal being integrated into the structural member in order to dissipate electrical charges (e.g. static or lightning). The composite structural member 201 is preferably a carbon fibre reinforced polymer (CFRP) made of carbon fibre layers 203 bound in a matrix 205. A plurality of metallic layers 207a/b (e.g. foramenous metal layers 209 of expanded copper foil (ECF) or bronze gauge (BG)) are disposed on the structural member, and they may be incorporated into a matrix 211. A further metallic layer 217 (galvanically compatible with 209, e.g. aluminium, copper, zinc, silver, nickel) is disposed on top of the junction of two metal layers 207a/b thereby at least partially overlapping the joint, which may be a butt joint or a lap joint. Layer 217 may be a thermally applied metal film of a thickness less than 15 µm. A paint coat may be applied on top of composite structural member and layer 217.
A structure formed from composite material
2017-06-28
Patent
Electronic Resource
English
IPC: | B32B LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM , Schichtkörper, d.h. aus Ebenen oder gewölbten Schichten, z.B. mit zell- oder wabenförmiger Form, aufgebaute Erzeugnisse / B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |